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Welcome to the 10th Australian Space Science Conference

and to St Leo’s College, University of Queensland! This will be the fourth ASSC jointly sponsored and organised by the National Committee for Space Science (NCSS) and the National Space Society of Australia (NSSA). The ASSC is intended to be the primary annual meeting for Australian research relating to space science. It welcomes space scientists, engineers, educators, and workers in Industry and Government. The launch of the first Decadal Plan for Australian Space Science on 27 September is a historic and crucial event for this ASSC, and for the development of Australia’s space science community. Multiple workshops on implementing the Plan will take place. This year are working for the first time with the Australian Space Research Institute (ASRI). We will also hear more about the successful projects from the first two rounds of the “Australian Space Research Program” (ASRP) – an initiative managed by the newly formed Space Policy Unit.

We look forward to an excellent meeting!

Iver Cairns Wayne Short Co Chair ASSC 2010 Co Chair ASSC 2010 Chair, NCSS President, NSSA

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Contents About the NSSA 5 About the NCSS 6 Decadal Plan 7 Program Committee & Organisers 8 Program Overview 10 Venue Details 11 Detailed Program 13 Invited Speakers 23 Oral Presentations 33 Poster Presentations 42 Collection of Abstracts 44

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The National Space Society of Australia is the coming together of like-minded space enthusiasts who share a vision for the future in which there is an ambitious and

vigorous space program leading to eventual space settlement. To this end the National Space Society (worldwide) promotes interest in space exploration, research, development and habitation through events such as science and business conferences, speaking to the press, public outreach events, speaking engagements with community groups and schools, and other pro-active events. We do this to stimulate advancement and development of space and related applications and technologies and by bringing together people from government, industry and all walks of life for the free exchange of information. As a non-profit organisation, the National Space Society of Australia draws its strength from an enthusiastic membership who contributes their time and effort to assist the Society in pursuit of its goals. For more information, and to become a member: www.nssa.com.au Ad Astra! Wayne Short NSSA President 2010

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The National Committee for Space Science (NCSS) is chartered by the Australian Academy of Science to foster space science, to link Australian space scientists together and to their international colleagues, and to advise the Academy’s Council on policy for science in general and space science in particular. The associated web page can be reached at http://www.science.org.au/natcoms/index.htm . NCSS believes that ASSC meetings provide a natural venue to link Australian space scientists and foster the associated science, two of its core goals. As well as ASSC, NCSS is also sponsoring the VSSEC – NASA Australian Space Prize. The first Decadal Plan for Australian Space Science will be launched at this ASSC. Driven primarily by NCSS, the Plan is supported by the Academy of Science, the Australian Academy of Technological Sciences and Engineering, and many other Australian stakeholders in Space. NCSS encourages all those interested in space science to support the Plan and take it forward. Wishing you an excellent conference, Russell Boyce (UQ), Iver Cairns (U. Sydney, Chair), Graziella Caprarelli (UTS), Alex Held (CSIRO, COSSA), Fred Menk (U. Newcastle), David Neudegg (IPS), Bob Vincent (Uni. Adelaide), Malcolm Walter (UNSW).

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Decadal Plan: Launch & Workshops on Monday 27 September The launch of the first Decadal Plan for Australian Space Science, almost 5 years in development, is a major priority for Australia’s space scientists and for ASSC. Additional priorities are to bring together and educate the scientific community and associated stakeholders in Government and industry, and to hold workshops that start implementing the Plan. The first morning session addresses the interests in Space of existing Government units. Presentations will be made by Space Policy Unit, IPS Radio & Space Services, the Bureau of Meteorology, and the Space Innovation Industry Council, among others. The Decadal Plan will be launched in the second morning session. The detailed program is subject to change. It is expected that NCSS and the Academy of Science will set the stage for the launch by either Professor Margaret Sheil, CEO of the Australian Research Council, or by the Minister for Innovation, Industry, Science, and Research (or delegate). An opportunity for questions will follow a short summary of the Plan’s most important elements. The afternoon sessions will start with the talk “Pathways to Space” on the successful ASRP grant, followed by Workshops on the Decadal Plan’s Flagship projects “Spaceship Australis” and Marabibi “Constellation” and associated linkages, both international and domestic. Additional Plan Workshops will be held 28-30 September, as in the Program Book.

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2010 ASSC Program Committee

Bill Barrett (Asia Pacific Aerospace Consultants)

Mark Blair (ASRI)

Iver Cairns (Chair, University of Sydney)

Jon Clarke (Mars Society of Australia)

Roger Franzen (Earthspace)

Brian Fraser (University of Newcastle)

Trevor Harris (DSTO)

Trevor Ireland (Australian National University)

Roman Makarevich (La Trobe University)

David Neudegg (IPS Radio Services)

Carol Oliver (University of New South Wales)

Michael Smart (University of Queensland)

Paul Tregoning (Australian National University)

Bruce Warrington (National Measurement Institute)

Colin Waters (University of Newcastle)

Xiaofeng Wu (University of Sydney)

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2010 Organising Committee

Mark Blair ASRI

Iver Cairns

Co Chair ASSC 2010 Chair, ASSC Program Committee

Sophia Casanova Secretariat

Stuart Kearney Australian Youth Aerospace Forum

Eloise Matheson Secretariat

Wayne Short Co Chair ASSC 2010

Project Manager, Operations

Michael Smart University of Queensland

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All proceedings will take place at St Leo’s College at the University of Queensland.

Conference

The conference will be held at ST LEO’S College at the University of Queensland – St. Lucia Campus.

Registration and secretariat will be available in the foyer. Stream 1 and Plenary sessions are in the BOARDROOM. Stream 2 sessions are in the Leonian Room.

Teas and lunches will be served on THE DECK. Poster sessions will be held in the READING room. Gala Dinner Tuesday 28 September 6:30 for 7:00pm start Cost: $65 / person Dress: Smart casual Location: UQ Staff Club

University of Queensland (5 min walk)

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Floor plan of conference facilities

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Monday - Decadal Plan and Workshop (Boardroom)

Time Speaker's Name Title

7:30-9:00 Registration

9:00-9:05 I. Cairns, W. Short Welcome

9:05-9:15 Opening the Conference Government Space

9:20-9:40 Joe Andrews The Space Policy Unit

9:40-10:00 Dave Neudegg IPS Radio and Space Services - The Bureau of Meteorology space weather capability.

10:00-10:20 Anthony Rea The Bureau of Meteorology‘s interests in space 10:20-10:40 TBA 10:40-11:00 Brett Biddington The Space Industry Innovation Council: Opportunity and Challenge

Tea Launch of the Decadal Plan Session Chair: Malcolm Walter

11:30-11:40 Iver Cairns Introduction by the National Committee for Space Science 11:40-11:50 Peter Hall Introduction by the Australian Academy of Science 11:50-12:10 Professor Sheil Official Launch 12:10-12:40 Iver Cairns Summary of the first Decadal Plan for Australian Space Science 12:40-13:00 Questions, media etc.

13:00-14:00 Lunch / Champagne

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Toast Workshop Sessions

14:00-14:30 Brett Biddington Pathways to Space 14:30 16:00 Chair: Iver Cairns Spaceship Australis & Coordinated Linkage & Medium projects 16:00-16:30 Tea 16:30-18:00 Chair: Iver Cairns Coordinated Linkage projects & Marabibi Constellation

Monday - ASRI / Student Stream (Leonian Room)

Time Speaker's Name Title

14:40-15:00 Austyn Luke HiGlide Project - Rocket Deployment of UAVs

15:00-15:20 Andew Winstanley Hybrid Rocket Autonomous Fly Home Recovery System

15:20-15:40 Sudantha Balage Near-Body Asymptotic Similarity of Hypersonic Bluff Body Flows – Gas Dynamics of Planetary Entry Capsules

15:40-16:00 Chontisa Kalyanamitra An AUSROC NANO

16:00-16:30 Tea 16:30-16:50 Steven Talevski Completion of the AUSROC Nano gimballing system

16:50-17:10 Thomas Fahey Ausroc Nano Intertank Fairing Structural Analysis and Design

17:10-17:30 Drew Ravalico The Challenges in the Design and Build of the University of Adelaide CubeSat

17:30-17:50 Jed Andrei Guinto Artificial Muscles for EVA Space Glove Design

17:50-18:10 Cameron Sinclair Sensitivity and single failure mode analyses of a six degree of freedom

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model for a multi-stage launch vehicle

18:15-19:15 Cocktail Reception

Tuesday – Stream1 (Boardroom)

Time Speaker's Name Title 9:00-9:10 Jeff Candiloro 10 years of the ASSC

Plenary 9:10-9:40 Mike Terkildsen Australian research on space weather 9:40-10:10 Robert Vincent Australian Research in the Middle Atmosphere and Lower Ionosphere

10:10-10:40 Anthony Rea Remote Sensing in the Bureau of Meteorology’s Composite Observing System

10:40-11:10 Sam Reisenfeld Satellite Modems and Communications Technology 11:10-11:30 Tea Plenary 11:30-12:00 Oscar Moze Space science in Italy 12:00-12:30 Christine Charles Australian research on plasma thrusters for spacecraft propulsion 12:30-13:00 Paul Tregoning Science Results from Australian Geodesy 13:00-14:00 Lunch

ASRP Grants 1 14:00-14:25 Andrew Parfitt The UniSA – ISU ASRO project

14:25-14:50 Kefei Zhang The Australian Space Research Program: Platform Technologies for Space, Atmosphere and Climate project

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14:50-15:15 Chris Rizos Australia & Future Satellite Navigation Systems – the “Lucky Country”

15:15-15:40 Cameron Boyd Antarctic Broadband

15:40-16:05 Russell Boyce The ASRP-funded project “Scramjet-based Access-to-Space Systems” 16:05-16:30 Tea

16:05-18:00

Posters

Various Presenters

19:00-22:00

Gala Dinner

UQ Staff Club

Tuesday – Stream 2 (Leonian Room)

Time Speaker's Name Title

8:00-9:00 Space science principals

Closed Workshop (Decadal Plan) - Setting up Coordination Structures Session Chair: Iver Cairns

Planetary & Astrobiology 1

14:00-14:15 Yuri Amelin Sequencing the early Solar System 14:15-14:30 Robert Pidgeon The Early Heavy Bombardment of the Moon at 4.34 Ga 14:30-14:45 Aditya Chopra Stars to Planets to Life: An Elemental Scheme 14:45-15:00 Eriita Jones Planetary Phase Models - Searching For Life

15:00-15:15 Charles Lineweaver

Earliest Divergences in the Tree of Life and Constraints on the Earliest Terrestrial Environments

15:15-15:30 Rasit Baykara Innovative approach for NEA Exploration 15:30-15:45 Razmi Khan Automated Visual Tracking and Spectral Analysis of the Hayabusa Re-entry

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15:45-16:00 Michael Jokic Temperature Estimation of the Hayabusa Capsule during Re-entry via direct Near Infrared Imaging

Wednesday - Stream 1 (Boardroom)

Time Speaker's Name Title Plenary

9:00-9:30 Allen Paul Hypersonics 9:30-10:00 Trevor Ireland Hayabusa returns 10:00-10:30 Mark Blair ASRI Programs in Space Education 10:30-11:00 Alina Donea Australian Research on Solar Physics 11:00-11:30 Tea 11:30-12:00 Miriam Baltuck CSIRO CASS 12:00-12:30 Robert Pidgeon Planetary Science in Australia 12:30-13:00 Brendan Burns From early life on Earth to microgravity - astrobiology research at the ACA 13:00-14:00 Lunch

ASRP Grants 2 14:00-14:30 Paul Tregoning The GRACE Follow On mission 14:30-15:00 Yue Gao Laser Tracking of Space Debris 15:00-15:30 Chris Rizos SAR Formation Flying – a Second Round ASRP Project 15:30-16:00 Tea

Space Technology & Engineering 1 16:00-16:15 Sandy Tirtey The SCRAMSPACE I Hypersonic Flight Experiment Feasibility Study

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16:15-16:30 Thomas Fergusson Rocket Booster Design for Scramjet-Assisted Access-to-Space Vehicles

16:30-16:45 Sarah Razzaqi Optimisation of Scramjet-Assisted Access-to-Space Vehicles Using Oxygen Enrichment

16:45-17:00 Obaid ur Rehman Nonlinear Robust Control design for Hypersonic Flight Vehicles

17:00-17:15 Hideaki Ogawa Physical Insight into Nozzle Flow Behaviour of Axisymmetric Scramjets for Access-to-Space via Design Optimisation

17:15-17:30 Laurie Brown Numerical Considerations for the Simulation of Supersonic Combustion Ramjet Intakes

17:30-17:45 David Petty Numerical Simulations of Hypervelocity Scramjet Combustion Flows 17:45-18:00 Dillon Hunt Computational Investigation Of An Axisymmetric Scramjet Configuration 18:00-18:15 Sean O'Byrne Embedded Data Acquisition System for Hypersonic Heat Flux Measurements 18:30-22:00 Student’s BBQ The RED-Room at UQ Wednesday - Stream 2 (Leonian room)

Time Speaker's Name Title

8:00-9:00 All interested people

Closed Workshop (Decadal Plan) - ICFO, Medium projects, Sundiver, esp. for Planetary and EOS Session Chair: Iver Cairns

Space Physics & Education

14:00-14:15 Yonghua Liu Pc2 waves observed by Cluster and Antarctic ground stations in dayside outer magnetosphere

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14:15-14:30 Andrew Layden Changes in mode properties versus mode conversion for waves in Earth's auroral ionosphere

14:30-14:45 Brett Layden Thermal Correction to the Rate of Second Harmonic Plasma Emission

14:45-15:00 Timothy Kauffman

The Mobile Space Academy (MSA) Concept: Practical Hands-on Science & Engineering Generates Enthusiasm for Space

15:00-15:15 Hannah Young From the backyard to beyond: investigating the cultural significance of amateur satellites

15:15-15:30 David Cooper Spaceward Bound Australia – Pilbara 2011 – and it’s predecessors 15:30-16:00 Tea

Earth Observation from Space & Planetary

16:00-16:15 Yuanyuan Zhang Comparison of HPF fusion and Wavelet fusion approaches on Image Fusion of Hyperspectral image and Multispectral image

16:15-16:30 Xin Wang Detection of Pastures in Southern Western Australia based on ENVISAT ASAR Dual Polarimetric Data

16:30-16:45 Ann Guo Integration of remotely sensed indices for land cover changes caused by the 2009 Victorian bushfires using Landsat TM imagery

16:45-17:00 Yingxin Zuo Evaluation of ALOS PALSAR Applicability to Generate Bushfires Scars Map

17:00-17:15 Rattanasuda Cholathat Monitoring Geologic Sequestration with Radar Remote Sensing

17:15-17:30 Xin Wang Using dual polarized L band SAR and optical satellite imagery for land cover classification in Southern Vietnam: Comparison and Combination

17:30-17:45 Eriita Jones Land Cover Map of Mars (a GIS-based study)

17:45-18:00 Mark Bishop Linear Dune Spacing and the Influence of Topography, Simpson Desert: An Analogue for the Understanding of Dune Formation on Earth and Titan

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Thursday – Stream 1 (Boardroom)

Time Speaker's Name Title

Space Technology & Engineering II

9:00-9:20 Ted Steinberg Queensland University of Technology Reduced Gravity Drop Tower Facility and Research

9:20-9:40 Jason Held The Operationally Responsive Space Project 9:40-9:55 Daniel Bunker An Electrodynamic Tether System for Picosatellites

9:55-10:10 Jonn Olsen Simulations of the effect of electrode geometry on the performance of an electric ion rocket.

10:10-10:25 Franziska Ullrich Design Optimization of a Mars Rover Rocker-Bogie Mechanism using Genetic Algorithms

10:25-10:40 Marco Ostini Lunar Numbat - Open Source Space technologies

10:40-10:55 David Buttsworth Beagle 2 Mars Lander Flight Dynamics Investigation via Experiment and Simulation

11:00-11:30 Tea Space Technology & Engineering III 11:30-11:45 Bernard Davison ASRI Small Sounding Rocket Program Activities and Developments

11:45-12:00 Nicholas Lawrance Autonomous soaring for atmospheric exploration

12:00-12:15 Jen Jen Chung High Level Risk Analysis and Decision Making for an Autonomous Mars Glider

12:15-12:30 Jason Held Estimating Spacecraft Structural Health Impacts Using Hybrid State Space Models

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12:30-12:45 Alan Harrland Hypersonic Inlet for a Laser Powered Propulsion System and its Interaction with an Idealized Laser Induced Detonation Wave

12:30-12:45 Stefan Würgler Path Planning for a Planetary Rover 13:00-14:00 Lunch

14:00-14:30 Closing & Feedback All interested people

14:30-16:00 Closed Workshop Decadal Plan implementation - Principals only 15:30-16:00 Tea Thursday - stream 2 (Leonian room)

Time Speaker's Name Title Space Physics & Weather

9:00-9:15 Elizabeth Smith A Risk Assessment of Space Weather Effects on the Australian Power Network

9:15-9:30 Myrtille Laas-Bourez

Tracking Australian Quasi-Geosynchronous Space Debris with the Zadko Telescope

9:30-9:45 Trevor Harris SpICE: A Program to Study Small-Scale Disturbances in the Ionosphere

9:45-10:00 Manuel Cervera Modelling of the effects of ionospheric disturbances using 3D magneto-ionic raytracing techniques

10:00-10:15 Kenneth Lynn VLF Gravity Wave Observations 10:15-10:30 Colin Waters Properties of ULF waves observed by TIGER SuperDARN radars

10:30-10:45 Chandrakant More

Field strength measurement of VLF radio wave propagation at 19.8 KHz between Australia and India

10:45-11:00 Hongang Yang Wave induced particle precipitation using test-particle simulations

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11:00-11:30 Tea Astrobiology II

11:30-11:45 Mark Bishop Quantifying Crescentic Dunefield Development Utilizing Spatial Statistics, North Polar Plains, Mars

11:45-12:00 Joseph Leach A late flood event in the formation of the Warrego Valles system on Mars

12:00-12:15 Elyse Schinella Constraints on crustal rheology from the evolution of Venus' geological landforms

12:15-12:30 Lucyna Kedziora-Chudczer VSTAR modelling of the Jupiter clouds.

12:30-12:45 Franklin Mills Analytic modeling of SOx in Venus’ mesosphere

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Invited Speakers Brett BIDDINGTON Space Industry Innovation Council “The Space Industry Innovation Council: Opportunity and Challenge” Brett Biddington is a consultant to government and the private sector. He provides advice on space matters and has more general interests in community resilience and risk management, notably in the electronic and information systems domains. He also addresses broader

questions of institutional behaviour including leadership, strategy, culture, organisational design and technology adoption against backgrounds of uncertainty and change. Between 2002 and 2009 he was a member of Cisco Systems’ global space team performing a very long term market creation role. The team’s principal focus was to encourage all involved in space activities to move to open data and communications standards and to take advantage of internet technologies wherever possible. The team was responsible for developing the Internet Router In Space (IRIS) program and a software router was launch on a commercial satellite, as a secondary payload, in November 2009. Brett chairs the Australian Space Industry Chamber of Commerce. He also sits on several boards and a number of national and industry advisory and committees. These include:

• Australian Space Industry Innovation Council • The Kokoda Foundation • ·Giant Magellan Telescope Project Oversight Committee • Advisory Board of the Institute for Telecommunications

Research at the University of South Australia. Brett left the Royal Australian Air Force (RAAF) in 2002 on completion of almost 23 years of service. He was an intelligence and security specialist before moving into the capability development arena where he sponsored a wide range of command and control, intelligence, surveillance, reconnaissance and electronic warfare projects. These included the Jindalee Over the Horizon Radar project and a number of classified and unclassified space initiatives. He also sponsored a substantial portfolio of research within the Defence Science and Technology Organisation. Recently, he

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completed a second report for the Kokoda Foundation about space policy options for Australia. Brett graduated from LaTrobe University Melbourne in 1974 with a BA(Hons) degree, majoring in politics. He was a member of the Australian Diplomatic Service and a lecturer in politics and public administration at the Canberra College of Advanced Education before joining the RAAF.

Mark BLAIR Australian Space Research Institute “ASRI Programs in Space Education” Mark began his professional career as a missile propulsion engineer at the Defence Science and Technology Organisation (DSTO) in 1990, working on a number of service-life extension and propulsion technology demonstration projects.

From 1996 to 1998, Mark was posted to the Defence Department in Canberra as a missile analyst, representing Australia at numerous international working groups and conferences.

On returning to DSTO, Mark led the advanced missile propulsion task, with particular responsibility for setting up the early phases of the scramjet propulsion collaborative effort with the University of Queensland.

In 2000, Mark joined Optus Pty. Ltd. as a satellite engineer and was posted to Space Systems Loral (SSL) in Palo Alto, CA, as part of the Resident Program Office (RPO) for the joint Optus/Defence C1 satellite acquisition project.

On return from the USA in 2003, Mark formed part of the Optus D series satellite tender evaluation team and was subsequently posted to Orbital Sciences Corp (OSC) as the lead RPO for the 5 yr duration of the program to acquire 3 geostationary communications satellites. Mark’s principle responsibilities were for the satellite bus, launch vehicle, and contractor management.

Mark is now based at the Optus headquarters in Sydney, working satellite bus, launch vehicle and project management aspects of the Singtel/Chunghwa ST-2 satellite acquisition project.

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Mark is a director and the current CEO of the Australian Space Research Institute Ltd (ASRI) and the current Chair of the Engineers Australia National Committee on Space Engineering.

In his ASRI role, Mark manages the AUSROC series of educational launch vehicle projects, and was instrumental in the establishment of the ASRI Small Sounding Rocket Program (SSRP) and other national educational space technology initiatives.

Brendan BURNS University of NSW “From early life on Earth to microgravity – astrobiology research at the ACA” Dr Brendan Burns completed his PhD in microbiology at The University of New South Wales in 1999. From here, he was awarded a highly prestigious Alexander von Humboldt Fellowship and conducted a post-doc in Germany from 2000-2001. He was then awarded an ARC Australian Post-doctoral Fellowship to return to UNSW in 2002. Since

then he has led research on the Shark Bay stromatolites, complex geomicrobial communities that are analogues of the very earliest evidence of life on Earth. The key to understanding the past is to study the present, and Dr Burns’ research team have used stromatolites as excellent model systems to address important evolutionary questions. Using these ancient life forms as blueprints, Brendan has also consulted with NASA to better focus efforts on the search for signals that may help in the detection of life on other planets. More recently, Brendan has led research examining the effects of microgravity on cellular function in human stem cell lines. This research is critical to both space science and cell biology due to its vast potential to decipher the effect of microgravity on humans at a cellular level as well as regeneration of tissues in the human body, and to use these alterations to solve ground based medical problems.

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Christine CHARLES Australian National University “Australian research on plasma thrusters for spacecraft propulsion” Dr Christine Charles is Associate Professor at the Australian National University (ANU) and Head of the Space Plasma, Power and Propulsion laboratory at ANU. Born in Brittany (France), she has a French Engineering degree in applied physics, a Ph D in plasma physics, a French Habilitation thesis in materials science and a Bachelor of Music degree in Jazz from the ANU (Jazz

drums and Jazz arrangement and composition). For the past twenty years, she has been working on experimental expanding plasmas (hot ionized gases) and their applications to electric propulsion, microelectronics and optoelectronics, astrophysical plasmas, and more recently to the development of fuel cells for the hydrogen economy. She is the inventor of the Helicon Double Layer Thruster, a new type of space engine, which applications include satellite station keeping or interplanetary space travel. In 2009 Christine received the Australian Institute of Physics Women in Physics Lecturer of the year award. She actively popularises her science on ABC Catalyst, Discovery Channel, radio and public lectures. She enjoys playing music, surfing, canoeing, cycling and bushwalking.

Alina DONEA Monash University “Australian Research on Solar Physics” Alina Donea is a senior lecturer in astrophysics at Monash University since 2008. Her research interests cover the research field of solar physics and the active galactic nuclei. In solar physics Alina is mainly interested in the physics of solar flares and solar quakes. The extragalactic interests span from the physics of accretion disks

surrounding supper-massive black holes to relativistic jets and their radiative signatures.

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Alina Donea had obtained a PhD (1999) on the symbiosis between accretion disks and relativistic jets, work done at Max Planck Institute for Radioastronomy in Bonn, Germany. She returned to Romania as a solar physicist working in particle acceleration in solar flares, followed by postdoctoral visits at the National Solar Observatory in Tucson, and Bordeaux Observatory. Solar quakes captivated her attention since 1998 when the first solar quake was discovered. Alina spent 3 years as an Australian Research Fellow at the University of Adelaide working on the high energy astrophysics of relativistic jets, followed by a postdoctoral and a lecturer position at Monash University working in helioseismology and solar flares. Alina Donea and her team have discovered all but one of the 20-odd known solar quakes, and have instituted a completely novel technique for doing so, the holographic imaging of the acoustic source. Satellite data from SOHO, SDO, RHESSI and also ground based data from various sources are widely used by the solar physics team at Monash to analyse the solar activity.

Trevor IRELAND Australian National University “HYABUSA Returns” Trevor Ireland is Professor at the Research School of Earth Sciences at the Australian National University. His research focuses on the broad area of cosmochemistry ranging from the preservation of interstellar stardust in meteorites, through to the earliest

development of Earth’s crust, hydrosphere, and atmosphere. His work on meteorites includes dating the oldest known materials in the solar system (at 4,560 million years) and measuring isotopic compositions of materials that can trace their parentage back to supernovae and red giant stars. His work also involves tracing the evolution of the earliest stages of the solar system when high temperature processing left refractory condensates and residues that we can now find in meteorites.

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Oscar MOZE Italian Embassy “Space Science in Italy: links between science and industry and the economic potential of the collaboration” Professor Oscar Moze was born in Melbourne, Australia and obtained his doctorate in Physics from Monash University (Melbourne). After a period of three years spent as a post-doctoral fellow in the United Kingdom he moved to Italy were he worked as a research fellow,

specializing in neutron scattering, with the National Research Council of Italy, firstly in Parma and then in Rome. In 1992 he became an Associate Professor in condensed matter physics, specializing in the study of the magnetic and superconducting properties of matter, in the Physics Department of the University of Parma. Prior to taking up his appointment as Science Attaché in the Embassy of Italy, Canberra, he was engaged in teaching and research at the University of Modena and Reggio Emilia. He is the author of over 150 research publications in internationally refereed scientific journals. He has been a consultant and referee for various national and international research centres. He is married with one child.

Robert PIDGEON Curtin University “Planetary Science in Australia” Robert T. Pidgeon completed an undergraduate degree in geology and physical chemistry with honours in geology at UWA in 1960. He spent nine months as an exploration geologist with Mangore Australia, exploring for vanadium deposits in Western Australia, before moving to

the Department of Geophysics at the ANU as a PhD student from 1961-1965. He was a Post-doctoral Fellow at the California Institute of Technology from 1996-1967 and a Research fellow at the Swiss Federal Institute of Technology (ETH) in Zurich from 1967-1968. From 1968-1976 he was Senior Lecturer and foundation leader of

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the Isotope Geology Unit of the Scottish Universities Research and Reactor Centre at East Kilbride. He returned to Australia as a Senior Research Fellow in the Research School of Earth Sciences ANU and from 1979-1982, was a Director of the Nuclear Codes Section in the Land Protection Branch of the of the Department of Science and the Environment of the Commonwealth Government. In 1982 he moved to Western Australia as Associate Professor in Geoscience at the Western Australian Institute of Technology (now Curtin University) and was appointed Professor of Geology in 1992. He retired in 2003 and has continued his involvement in research in geochronology at Curtin as an Adjunct Professor.

Anthony REA Bureau of Meteorology “Remote Sensing in the Bureau of Meteorology’s Composite Observing System” Anthony Rea is the manager of the Bureau of Meteorology’s Composite Operations Section, responsible for operational management of the Bureau’s observations network. The Section, located at the Bureau’s Head Office in Melbourne’s Docklands, employs around 30 staff and has responsibility for operation and

maintenance of the Bureau’s network of field stations, automatic weather stations, radars, marine observing platforms and satellite earth receiving stations across Australia and Antarctica. After graduating as a surveyor, Anthony worked in oil exploration, road construction and hydrography before joining the Bureau of Meteorology in 2000. In 2005 he obtained his PhD in the use of meteorological satellites for tracking cloud motion and in 2008 he completed an Executive Masters of Public Administration through the Australia and New Zealand School of Government (ANZSOG).

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Sam REISENFELD Macquarie University “Satellite Modems and Communications Technology” A/Prof Sam Reisenfeld is currently an Associate Professor in the Department of Electronic Engineering, Faculty of Science at Macquarie University. He received the B.S. Degree (Information Engineering) from the University of Illinois in 1969 and M.S. and Ph.D.

Degrees (Communication Systems Engineering) from the University of California at Los Angeles in 1971 and 1979, respectively. From 1969 until 1988, he was a Space Systems Engineer at the Hughes Aircraft Company in El Segundo, California. He was an Associate Professor at the University of Technology, Sydney from 1988 until 2009. During 1988 through 1992, he also held the position of satellite communication research engineer at OTC, Research and Development, in Sydney. While at UTS, from 1998 until 2005, he was the Program Director for Ka band Satellite Communications in the CRC for Satellite Systems. A/Prof Reisenfeld’s current research interests are advanced signal processing in satellite applications, cognitive radio oriented wireless networks, and software defined radio. He received the IEEE Millennium Medal in 2000 and is a member of ΦΚΦ. Mike Terkildsen IPS Radio Services “Australian Research on Space Weather” Dr Mike Terkildsen is a scientist with the Ionospheric Prediction Service (IPS), part of the Australian Bureau of Meteorology. IPS operates as the Australian Space Weather Agency, providing regional space weather services. His role within IPS includes both consultancy and research related to space weather impacts on trans-ionospheric services such as satellite communications and GPS navigation with a key focus on modelling ionospheric variability, and specifically its impacts in the Australian region on technological systems such as GNSS. This role has involved a range of consultancies, including the analysis of an ionospheric threat model

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for GPS augmentation, a study of ionospheric variability in the sub-equatorial region, and an analysis of regional ionospheric conditions for the CSIRO SKA bid. Current research and development projects include the development of a regional ionospheric model, the development of a trans-ionospheric observation network and web service, and the analysis of regional ionospheric gradients and ionospheric storm features in the context of GPS augmentation.

Paul TREGONING Australian National University “Science Results from Australian Geodesy” Dr Tregoning received his PhD in geodesy from The University of NSW in 1996. He was a postdoctoral research fellow at MIT and Scripps Institution for Oceanography in 1995 before taking up a position at the Research School of Earth Sciences where he currently heads the Geodynamics Group and is the

Director of the ANU Centre for Natural Hazards. His research utilises observations from space geodetic satellite missions to study geophysical processes on Earth, including plate tectonics, earthquake deformation, sea level studies and mass balance changes in polar regions, satellite orbit estimation, atmospheric water vapour, hydrological changed and related crustal deformation. He is the Australian delegate to the International Association for Geodesy, serves on the Steering Committee of AuScope Geospatial and has been a member of several national committees and working groups related to space geodesy in Australia.

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Robert VINCENT University of Adelaide “Australian Research in the Middle Atmosphere and Lower Ionosphere” Professor Bob Vincent’s research interests include the development and application of innovative radar and optical techniques for to studies of the atmosphere, with a particular interest in atmospheric dynamics. His group operates a unique network of wind-measuring radars that are located

from the equator to the Antarctic. The group participates in a large number of collaborations to study atmospheric processes from both the ground and space. He serves on a number of national and international bodies that promote research in the atmosphere and the solar-terrestrial environment. He is a Fellow of the Australian Academy of Science, a Fellow of the American Geophysical Union and is President of the Scientific Committee for Solar-Terrestrial Physics (SCOSTEP/ICSU).

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List of Presentations Abstracts are listed in alphabetical order of first author

Name of Presenter Names of all authors Title

Yuri Amelin Yuri Amelin Sequencing the early Solar System

Sudantha Balage

Sudantha Balage, Russell Boyce, Neil Mudford and Sean O’Byrne

Near-Body Asymptotic Similarity of Hypersonic Bluff Body Flows – Gas Dynamics of Planetary Entry Capsules

Rasit Baykara

Rasit Baykara, Alistair Moore, Alex Fairlie, James Nour, Jasim Ahmed, *Victor Djamovski, *Jaeyhung Choi, *Ishan Mor,*Goitseone Montiya, *Steven Talevski, *Yasas Thalagala

Innovative approach for NEA Exploration

Brett Biddington Dr Rosalind Dubs and Space Industry innovation Council

The Space Industry Innovation Council: Opportunity and Challenge

Brett Biddington

Carol Oliver, Matthew Connell, Salah Sukkarieh, Michael O’Brien, and Brett Biddington

Pathways to Space: Empowering the Internet Generation

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Mark Bishop Mark A. Bishop and David Tran

Linear Dune Spacing and the Influence of Topography, Simpson Desert: An Analogue for the Understanding of Dune Formation on Earth and Titan

Mark Blair Mark Blair ASRI Programs in Space Education

Russell Boyce

Russell Boyce, Sean O’Byrne, Con Doolan, David Buttsworth, Allan Paull, Philip Teakle, Jerome Vethecan, Don Fry, Klaus Hannemann, Tetsuji Sunami, Gennaro Russo, Graham Candler, University of Minnesota (UMN), Stuart Kearney

The ASRP-funded project “Scramjet-based Access-to-Space Systems”

Laurie Brown Laurie Brown Numerical Considerations for the Simulation of Supersonic Combustion Ramjet Intakes

Daniel Bunker D. Bunker and Dr. S. Sukkarieh An Electrodynamic Tether System for Picosatellites

David Buttsworth David Buttsworth and Michael Jokic

Beagle 2 Mars Lander Flight Dynamics Investigation via Experiment and Simulation

Manuel Cervera Manuel Cervera, Trevor Harris

Modelling of the effects of ionospheric disturbances using 3D magneto-ionic raytracing techniques

Christine Charles Christine Charles Australian research on plasma thrusters for spacecraft propulsion

Rattanasuda Cholathat Rattanasuda Cholathat, Linlin Ge, Xiaojing Li, Chris Rizos

Monitoring Geologic Sequestration with Radar Remote Sensing

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Aditya Chopra Aditya Chopra and Charles Lineweaver Stars to Planets to Life: An Elemental Scheme

Jen Jen Chung

Jen Jen Chung and Salah Sukkarieh

High Level Risk Analysis and Decision Making for an Autonomous Mars Glider

David Cooper David Cooper Spaceward Bound Australia – Pilbara 2011 – and it’s predecessors

Bernard Davison Richard Samuel and Bernard Davison

ASRI Small Sounding Rocket Program Activities and Developments

Alina Donea Alina Donea Australian Research on Solar Physics

Thomas Fahey Thomas Fahey Ausroc Nano Intertank Fairing Structural Analysis and Design

Thomas Ferguson Thomas Ferguson, Thomas Jazra, Michael Kevin Smart

Rocket Booster Design for Scramjet-Assisted Access-to-Space Vehicles

Yue Gao Yue Gao, Craig Smith, Ben Greene Laser Tracking of Space Debris

Jed Guinto Jed Guinto and Lachlan Thompson Artificial Muscles for EVA Space Glove Design

Li Guo Li Guo, Linlin Ge, and Xiaojing Li

Integration of remotely sensed indices for land cover changes caused by the 2009 Victorian bushfires using Landsat TM imagery

Trevor Harris Trevor Harris and Manuel Cervera

SpICE: A Program to Study Small-Scale Disturbances in the Ionosphere

Alan Harrland Alan Harrland Hypersonic Inlet for a Laser Powered Propulsion System and its Interaction with an Idealized Laser Induced Detonation Wave

Jason Held Dr. Jason Held, Mr. Nigel Hoschke, Dr. Don Price

Estimating Spacecraft Structural Health Impacts Using Hybrid State Space Models

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Jason Held Dr. Jason Held, Dr. Alex Green, Mr. Michael Lamont

The Operationally Responsive Space Project

Dillon Hunt D.C. Hunt, R.R. Boyce and A. Paull

Computational Investigation Of An Axisymmetric Scramjet Configuration

Trevor Ireland Trevor Ireland HAYABUSA Returns

Michael Jokic Michael Jokic, David Buttsworth, Albert Chong

Temperature Estimation of the Hayabusa Capsule during Re-entry via direct Near Infrared Imaging

Eriita Jones Eriita Jones, and Charles Lineweaver Planetary Phase Models - Searching For Life

Eriita Jones

Eriita Jones, Johnathan Clarke, Frank Mills, Bruce Doran, and Charles Lineweaver

Thermal Land Cover Map of Mars (a GIS-based Study)

Chontisa Kalyanamitra

Chanapat Bhadrakom, Chontisa Kalyanamitra, Pongpaiboon Akapaiboon, Siwat Koekiatpibul, Thanit Chanjarhatpong, Toppak Chiammunchit

An AUSROC NANO

Timothy Kaufmann Timothy Kaufmann The Mobile Space Academy (MSA) Concept: Practical Hands-on Science & Engineering Generates Enthusiasm for Space

Lucyna Kedziora-Chudczer Lucyna Kedziora-Chudczer VSTAR modelling of the Jupiter clouds

Razmi Khan Razmi Khan, Troy Eichmann, Ben Upcroft, David Buttsworth

Automated Visual Tracking and Spectral Analysis of the Hayabusa Re-entry

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Myrtille Laas-Bourez Myrtille Laas-Bourez, John A. Kennewell and David M. Coward

Tracking Australian Quasi-Geosynchronous Space Debris with the Zadko Telescope

Nicholas Lawrance Nicholas R.J. Lawrance, Salah Sukkarieh Autonomous soaring for atmospheric exploration

Andrew Layden Andrew Layden, Iver Cairns, Peter Robinson

Changes in mode properties versus mode conversion for waves in Earth's auroral ionosphere

Brett Layden Brett Layden, John Percival, Iver Cairns, Peter Robinson

Thermal Correction to the Rate of Second Harmonic Plasma Emission

Joseph Leach J. H. J. Leach and Q. J. K. Tan

A late flood event in the formation of the Warrego Valles system on Mars

Charles Lineweaver Charles Lineweaver, Aditya Chopra

The Earliest Divergences in the Tree of Life and Constraints on the Earliest Terrestrial Environments

Yonghua Liu Y. H. Liu, B. J. Fraser, F. W. Menk

Pc2 waves observed by Cluster and Antarctic ground stations in dayside outer magnetosphere

Austyn Luke Austyn Luke, Jackson Richards HIGHGlide Project - Rocket Deployment of UAVs

Kenneth Lynn Kenneth Lynn VLF Gravity Wave Observations

Franklin Mills F. P. Mills, B. J. Sandor, R. T. Clancy, Y. L. Yung, and M. Allen

Analytic modeling of SOx in Venus’ mesosphere

Chandrakant More Chandrakant More, Ashokkumar Sharma and Rajaram Bhonsle

Field strength measurement of VLF radio wave propagation at 19.8 KHz between Australia and India

Oscar Moze Oscar Moze Space Science in Italy: links between science and industry and the economic potential of the collaboration

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Dave Neudegg Dave Neudegg IPS Radio and Space Services - The Bureau of Meteorology space weather capability.

Sean O’Byrne Sean O'Byrne, Varun Prakash

Embedded Data Acquisition System for Hypersonic Heat Flux Measurements

Hideaki Ogawa Hideaki Ogawa and Russell Boyce

Physical Insight into Nozzle Flow Behaviour of Axisymmetric Scramjets for Access-to-Space via Design Optimisation

John Olsen Rhys Wolfendon, John Olsen, John Page

Simulations of the effect of electrode geometry on the performance of an electric ion rocket

Marco Ostini Macro Ostini Lunar Numbat - Open Source Space technologies

David Petty D. Petty, M. Smart, V. Wheatley and S. Razzaqi

Numerical Simulations of Hypervelocity Scramjet Combustion Flows

Robert Pidgeon Robert Pidgeon Planetary Science in Australia

Robert Pidgeon Robert.Pidgeon, Marion Grange and Alexander Nemchin

The Early Heavy Bombardment of the Moon at 4.34 Ga

Drew Ravalico Drew Ravalico The Challenges in the Design and Build of the University of Adelaide CubeSat

Sarah Razzaqi Sarah Razzaqi, Thomas Jazra, Michael Kevin Smart

Optimisation of Scramjet-Assisted Access-to-Space Vehicles Using Oxygen Enrichment

Anthony Rea Anthony Rea, Susan Barrell

Remote Sensing in the Bureau of Meteorology’s Composite Observing System

Obaid ur Rehman Obaid ur Rehman, Ian Petersen Nonlinear Robust Control design for Hypersonic Flight Vehicles

Sam Reisenfeld Sam Reisenfeld Satellite Modems and Communications Technology

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Chris Rizos Andrew Dempster, Chris Rizos SAR Formation Flying – a Second Round ASRP Project

Chris Rizos Chris Rizos Australia & Future Satellite Navigation Systems – the “Lucky Country”

Elyse Schinella Elyse Schinella and Craig O’Neill

Constraints on crustal rheology from the evolution of Venus' geological landforms

Leila Norouzi Sedeh Leila Norouzi Sedeh, Colin Waters Properties of ULF waves observed by TIGER SuperDARN radars

Cameron Sinclair

Cameron Sinclair, Kylie Bedwell, Daniel Bettcher, Laura Brooks, Matthew Tetlow

Sensitivity and Single Failure Mode Analyses of a Six Degree of Freedom Model for a Multi-Stage Launch Vehicle

Elizabeth Smith Elizabeth Smith, Richard Marshall, Colin Waters, Murray Sciffer

A Risk Assessment of Space Weather Effects on the Australian Power Network

Ted Steinberg

Ted Steinberg, Martin Castillo, Owen Plagens, David Lynn, Matthew Hales, Antoine Diana and Wayde Martens

Queensland University of Technology Reduced Gravity Drop Tower Facility and Research

Steven Talevski Steven Talevski and Lachlan Thompson Completion of the AUSROC Nano gimballing system

Ken Tan Q. J. K. Tan, J. H. J. Leach The Channels of Mars and the Basalt Plains of Victoria: An Investigation of Channel Formation Chronology

Mike Terkildsen Mike Terkildsen Australian Research on Space Weather

Sandy Tirtey Sandy Tirtey The SCRAMSPACE I Hypersonic Flight Experiment Feasibility Study

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Paul Tregoning Paul Tregoning Science Results from Australian Geodesy

Paul Tregoning

Paul Tregoning, Daniel Shaddock, Craig Smith, Bob Oreb, Bruce Warrington

The GRACE Follow On mission

Franziska Ullrich Franziska Ullrich and Salah Sukkarieh

Design Optimization of a Mars Rover Rocker-Bogie Mechanism using Genetic Algorithms

Robert Vincent Robert Vincent Australian Research in the Middle Atmosphere and Lower Ionosphere

Xin Wang

Xin Wang, Linlin Ge, Xiaojing Li and Michael Chang

Detection of Pastures in Southern Western Australia based on ENVISAT ASAR Dual Polarimetric Data

Xin Wang Hai Tung Chu, Linlin Ge and Xin Wang

Using dual polarized L band SAR and optical satellite imagery for land cover classification in Southern Vietnam: Comparison and Combination

Andrew Wheeler Andrew Wheeler, Mark A. Bishop

Quantifying Crescentic Dunefield Development Utilizing Spatial Statistics, North Polar Plains, Mars

Andrew Winstanley Andrew Winstanley Hybrid Rocket Autonomous Fly Home Recovery System

Stefan Würgler Stefan Würgler and Salah Sukkarieh Path Planning for a Planetary Rover

Hongang Yang Hongang Yang, Brian Fraser and Murray Sciffer Wave induced particle precipitation using test-particle simulations

Hannah Young Hannah H. Young From the backyard to beyond: investigating the cultural significance of amateur satellites

Kefei Zhang Kefei Zhang The Australian Space Research Program: Platform Technologies

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for Space, Atmosphere and Climate project

Yuanyuan Zhang Yuanyuan Zhang, Linlin Ge and Xiaojing Li

Comparison of HPF fusion and Wavelet fusion approaches on Image Fusion of Hyperspectral image and Multispectral image

Yingxin Zuo Yingxin Zuo and Linlin Ge Evaluation of ALOS PALSAR Applicability to Generate Bushfires Scars Map

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Posters Posters are listed in alphabetical order of first author

Name of Presenter Names of all authors Title

Zahra Bouya Zahra Bouya Mapping the Regional Australian ionospheric TEC using a Spherical Cap Harmonic model and ARGN products

Alan Brockman Alan H Brockman, Myrtille Laas-Bourez, and John A Kennewell

Monitoring Space Debris in Australia

Nerida Hector Mark A. Bishop, Nerida Hector, Andrew Wheeler

Comparative Pattern Evolution and Self-Organization for Dunefields of the Ar Rub’ al Khali Sand Sea, Earth, and the North Polar Plains, Mars

Dean Hillan Dean Hilllan, Iver Cairns, Peter Robinson

Type II Solar Radio Bursts : Extraction of shock parameters and detailed comparison of theory with observations

Timothy Kauffman Timothy Kauffman NASA ISS Microgravity Research Platform Open for Business

Bo Li Bo Li, Iver H Cairns, and Peter A Robinson

Probing Spatial Temperature Variations in Solar Corona via Type III Solar Radio Bursts

Joseph Leach

Joseph Leach, Richard Arndt, Botao Shen, Zhong Xiao Goh, Damian Yeung, Noriko Hirashima, and Zhixu Li

Site selection for long duration lunar bases

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Vasili Lobzin

Vasili Lobzin,Iver Cairns, Alexander Warmuth, Roman Gorgutsa, Peter Robinson, Gottfried Mann, Valery Fomichev

Evidence for Gently Sloping Plasma Density Profiles in the Deep Corona

Seann McKibbin Seann McKibbin Mn-Cr systematics in meteoritic olivine measured by SHRIMP (Sensitive High-mass Resolution Ion Micro-Probe)

Franklin Mills Manuraj Shunmuga Sundaram, Franklin Mills, Mark Allen, Yuk Yung

A modelling assessment of nitrogen oxide chemistry in the Venus mesosphere

Chandrakant More Chandrakant More and Ashokkumar Sharma

Studies On Effect Of Solar Activities On Transequatorial Vlf Radio Wave Propagation At 19.8 Khz

Fiona Schleyer Fiona Schleyer, Iver Cairns, Eun-Hwa Kim, Peter Robinson

Linear mode conversion of upper hybrid waves to radiation: Averaged energy conversion efficiencies, polarization, and applications to Earth's magnetosphere

Graham Steward Graham Steward, Vasili Lobzin, Phil Wilkinson, and Dave Neudegg

Automatic Recognition of Complex Magnetic Regions on the Sun using GONG Magnetogram Images and Their Usefulness in Predicting Flares

Dion Tiu Dion Tiu and Iver Cairns Evidence for Reformation of the Uranian Bow Shock

Xiaofeng Wu

Xiaofeng Wu and Xueliang Bai

A Virtual Satellite Design for the University Student Satellite Program

Hongang Yang Hongang Yang A. Bhattacharjee, Yi-Min Huang, Lei Ni, B. Rogers

Fast reconnection in high-Lundquist-number plasmas due to the shear flow and plasmoid Instability

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Abstracts

Sequencing the early Solar System

Yuri Amelin, Research School of Earth Sciences, the Australian National University

Recent discoveries in astronomy and planetary science have overturned the previously accepted paradigm of planetary system formation. It was thought, until recently, that accretion of the solar nebula progressed from mineral grains and their millimetre-size aggregates (chondrules - spherules of silicate minerals, and CAIs), to mountain-size bodies (planetesimals), and eventually to planetary embryos and planets, and that the onset of igneous activity on asteroids post-dated the CAI and chondrule formation by 5-10 Ma. Instead, these studies indicate that formation of chondrules and accretion of the parent asteroids of chondrites, occurred simultaneously with formation of the early differentiated asteroids. The protoplanetary disk was a dynamic system comprising domains with very diverse environments that coexisted in space and time for about 5 Ma, from formation of CAIs to formation and collisional re-processing of Moon-size planetary embryos. Understanding the interaction between these domains is impossible without accurate knowledge of the sequence and duration of the early processes occurring in the Solar System. The time markers for these processes are provided by abundances of short-lived (now extinct) isotopes such as 26Al, 53Mn and 182Hf, and by accumulation of radiogenic Pb isotopes from the decay of uranium and thorium. Modern advancement in the early Solar System chronology, based on analytical developments, finding more pristine meteorites originating from various parent asteroids, and integration of multiple isotopic chronometers and high-resolution geochemical and petrologic studies, will be reviewed in this presentation.

Near-Body Asymptotic Similarity of Hypersonic Bluff Body Flows – Gas Dynamics of Planetary Entry Capsules

Sudantha Balage, Russell Boyce, Neil Mudford and

Sean O’Byrne

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An investigation of fundamental flow physics of planetary entry configurations, funded by the Australian Research Council, was undertaken at the University of New South Wales at Australian Defence Force Academy (UNSW@ADFA). This paper discusses one of the theoretical findings of the above study. A hitherto-unexamined class of dynamically similar, hypersonic bluff-body flow fields named near-body asymptotic similarity (NBAS) flows is introduced. The CFD corroboration of NBAS results in an apparent violation of the Buckingham Pi theorem as significantly different freestream Pi groups result in ostensibly similar flow fields downstream of the bow shock, as shown in figure A. The asymptotic nature of bluff-body flow parameters at Mach numbers high enough to make the flow field insensitive to that parameter facilitates the above class of approximate similarity in the near-body flow. Two distinct approaches to NBAS are studied assuming cases of calorically perfect gas flow and thermally perfect gas flow. The concept of NBAS, by revealing the way flow similitude without demanding significant, if any, modifications to a test facility, contributes towards the present understanding of the scaling problem of the hypersonic to bluff-body flows from laboratory to flight. The similarity transformation group associated with NBAS can be used to discriminate empirical formulae describing hypersonic bluff-body flow parameters. NBAS-compliant empirical formulae of the near-body flow parameters are required to be invariant under the above similarity transformations while the non-compliant formulae would erroneously predict different solutions for dynamically similar flow fields. The concept of the effective Reynolds number generalizes the post-shock flow dynamics by linking the effects of freestream Mach number and specific-heat ratio to the Reynolds number of the near-body flow. Furthermore, the analysis reveals that the effective Reynolds number is inversely proportional to the Knudsen number. The existing definition of the Mach-independence limit is therefore qualified based on the Knudsen/effective Reynolds numbers, clarifying some implicit assumptions found in the literature.

Innovative approach for NEA Exploration Rasit Baykara, Alistair Moore, Alex Fairlie, James Nour, Jasim Ahmed,

Victor Djamovski, Jaeyhung Choi, Ishan Mor, Goitseone Montiya, Steven Talevski, Vasas Thalagala

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School of Aerospace, Mechanical and Manufacturing Engineering,

RMIT University The study of the composition of a Near Earth Asteroid (NEA) would significantly expand the scientific knowledge of the solar system. Many missions would involve the obvious plan of going to an asteroid to undertake the study. However the method involved with this project is to deflect the asteroid off its original orbital path and bring the asteroid closer to earth, to allow for more time to study the asteroid. Hence eliminating the limitations of time, technology and space environmental factors such as radiation, micro-gravity etc. The asteroid would be moved to a lagrangian point using robotic probes, which will initially be launched. There are five lagrangian points around earth and point 2 has been selected for this mission profile. Lagrangian point two (L2) has the advantages of, the protection from the sun’s radiation by the earth’s magnetic field and is also close enough to get to. Once the asteroid has been brought to L2 at the required speed, a crew will be sent to the NEA to undertake the study of the asteroid. The crew will have the long periods of time available to undertake the study. Once the study is complete the crew will return to earth, however the Transit vehicle will remain in GEO for future missions. This mission will enable study to be undertaken for long periods of time on the asteroid. The risk of human life and radiation exposure will also be reduced. A platform can be built for future deep space missions (eg. mars and beyond). And this concept will also reduce the overall cost of such a mission.

The Space Industry Innovation Council: Opportunity and Challenge

Dr Rosalind Dubs and Space Industry Innovation Council

The Space Industry Innovation Council (SIIC) was established in late 2009. The Council Chair is Dr Rosalind Dubs and comprises 17 members drawn from government, industry and the academic community. This talk will discuss the composition of the Council, its terms of reference and its work.

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Pathways to Space: A multi--million dollar initiative aimed a increasing space-related skills for an emerging Australian

space program Carol Oliver, Matthew Connell, Salah Sukkarieh, Michael O’Brien, and

Brett Biddington In February, 2010, Pathways to Space: Empowering the Internet Generation, became the first education project to be funded under the Australian Space Science Research Program, and only one of two funded education projects funded to date. ‘Pathways to Space’ is University of NSW-led (Australian Centre for Astrobiology) with three other consortium members – the Powerhouse Museum (where the project is being created), the University of Sydney (Australian Centre for Field Robotics) and Cisco Systems Australia. The project is funded to nearly $1m and is supported by nearly $1.5m in-kind by the four consortium members. The project has three inter--linked elements designed to (a) allow thousands of Year 10-12 students to work with real science and engineering in a museum environment; (b) provide a vehicle for up to four new space-related doctorates; and (c) provide the basis for a robust longitudinal study, the results of which may help to guide the delivery of science education in the future. In essence, the high school students will be exposed to the multidisciplinary nature of space science through the planning, analysing and testing the results of a simulated remote sensing mission to Mars. They will engage in the robotics research being carried out in the Powerhouse and will use Cisco's telepresence as a unique window onto the research environment, connecting them live with astrobiology research at UNSW and internationally. The objective is to systematically address how to encourage students to consider space-related courses that could potentially provide skills needed for an emerging Australian space program, and to track how many actually go onto taking those courses. At the heart of the program is a ‘living laboratory’ in the Powerhouse, staffed with university researchers, together with a Marscape covering around 300 square metres and open to the public from early next year.

Linear Dune Spacing and the Influence of Topography, Simpson Desert:

An Analogue for the Understanding of Dune Formation on Earth and Titan

Mark A. Bishopa,b, David Trana

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aBarbara Hardy Institute [Terrain Analogue Understanding (TAU) research]

School of Natural and Built Environments, University of South Australia, Adelaide, SA, 5000 Australia

bPlanetary Science Institute, Tucson, Arizona, 85719, USA

The identification of extensive linear dune fields on Titan has required that the models and uncertainties of dune formation, climate mechanisms, wind regimes, and dune field evolution on Earth, be revisited prior to reaching an understanding of the immense equatorial dune fields of organic ‘sand’ on Titan. For terrestrial deserts, spacing relationships are used extensively for the morphometric and evolutionary description of linear dunes, and as found for crescentic dune systems, may prove to be measures of dune field self-organisation and maturity. However, little is known about the inherent variability of linear dune spacing and the manner in which this may be influenced by topography. Thus to characterize the interaction of dune and topography, a Titan analogue site was chosen in an area of linear dunes bordering the Rodinga Ranges of the northern Simpson Desert. The interaction of linear dunes with the inselberg-like forms of the Ranges has shown that spacing relationships can be both unsystematic, and organized. For the latter, a statistically significant nonlinear, cubic relationship was found between dune spacing and distance from the topographic obstacle. Such a relationship is suggested to have arisen from local areas of dune field that may have been perturbed by catastrophic floods, and which has led to the subsequent reestablishment of dunes and their spacing under different environmental conditions. Overall, dune field spacing can be highly variable and demonstrate significant local and regional diversity. Thus the quantification of changes in dune field patterns may offer a baseline from which comparative metrics for other terrestrial ergs and those of Titan can be made to further the generally limited understanding of dune formation, pattern development and erg evolution in which linear dunes are the principal types.

ASRI Programs in Space Education

Mark Blair

CEO Australian Space Research Institute Ltd. The Australian Space Research Institute Ltd. (ASRI) is one of Australia’s premier institution for ‘hands-on’ education and

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development in the field of space science and technology. ASRI was formed through the consolidation of several space engineering research groups in 1992 in an effort to provide focused, nationally integrated programs for the advancement of space science and technology education within Australia. The objectives with which ASRI was founded are to:

• develop and advance space science and technology. • conduct, encourage and promote research in the field of space

science and technology. • educate and extend knowledge in the field of space science

and technology and to make available education opportunities in the field of space science and technology to supplement and further those opportunities made available by established educational institutions.

• conduct, co-ordinate and support projects for the advancement of the above objects.

ASRI is currently undertaking ‘hands-on’ research, development and educational programs in the launch vehicle and satellite technology fields in order to fill the education void in these disciplines within Australia. ASRI is coordinating numerous space engineering projects around the country that allow ASRI members, students and interested members of the general public to gain practical experience in these increasingly important disciplines. This presentation describes the structure, operation and educational activities of ASRI.

Monitoring Space Debris in Australia

Alan H Brockman1 , Myrtille Laas-Bourez2 and John A Kennewell3

1Learmonth Solar Observatory, IPS Radio and Space Services, Exmouth, Western Australia

2International Centre for Radio Astronomy Research, University of Western Australia, Crawley, Western Australia

3 Australian Space Academy, Meckering, Western Australia In the last twelve months two separate facilities have been established in Western Australia to monitor orbital space debris. The United States Air Force Research Laboratory (AFRL) has set up two fifty centimetre telescopes at Learmonth Solar Observatory in a test to expand the US Space Surveillance Network with globally spread

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small sensor systems. One of the telescopes will be used to perform high accuracy orbit determination of geosynchronous space objects (active satellites and debris), and the other will be used to survey and monitor the low Earth orbit. Just north of Perth, the University of Western Australia is automating their one metre Zadko telescope and integrating it into the TAROT network with other telescopes in France and Chile. This network will be used to detect and analyse astronomical transients and space debris in near real time. The paper will discuss details and operation of the two systems.

Mapping the Regional Australian ionospheric TEC using a Spherical Cap Harmonic model and ARGN products.

Zahra Bouya

IPS Radio and Space Services, Bureau of Meteorology, Sydney The Spherical Harmonic Analysis (SHA) is a well known technique for global modelling (Albertella et al., 1993, De Santis et al., 1999, Schaer, 1999). For regions with a fairly dense coverage of data at different latitudes, a regional model offers a better resolution of the regional field. By using basis functions satisfying the boundary conditions at the edge of a spherical cap, Haines(1985) developed a method to apply this technique to data from only a region of the earth called the Spherical Cap Harmonic Analysis (SCHA) an attractive regional modelling tool having close relationship with global SHA. This paper proposes an approach to the regional Total Electron Content (TEC) representation by the SCHA. The model was based on longitudinal expansion in Fourier series and fractional legendre colatitudinall functions over a spherical caplike region including the Australian continent. The SCHA has been applied to the values of the TEC ionospheric parameter as observed by the Australian Regional GPS Network (ARGN). Slant TEC values along the GPS signal path from the ARGN receivers are converted to vertical TEC. The SCHA coefficients are estimated from the vertical TEC at the Ionospheric Pierce Points (IPPs). Diurnal TEC variations with 15 minutes resolution and 2D TEC regional maps are constructed using the estimated spherical harmonic coefficients. It has been found that modelling the ARGN TEC by SCHA showed quite well satisfactory results for low spatial indices of the harmonics.

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It requires a suitable choice of the maximum degree by which the spherical harmonic expansion is truncated, according to a reasonable detailed spatial description of the ionospheric TEC. The SCHA estimated single receiver TEC variations follow expected diurnal variations with low night-time TEC values and midday peaks.

The ASRP-funded project “Scramjet-based Access-to-Space Systems”

Russell Boyce

University of Queensland (UQ)

Sean O’Byrne University of New South Wales

Australian Defence Force Academy (UNSW@ADFA)

Con Doolan University of Adelaide (UA)

David Buttsworth

University of Southern Queensland (USQ)

Allan Paull Defence Science and Technology Organisation (DSTO)

Philip Teakle

Teakle Composites

Jerome Vethecan BAe Systems

Don Fry AIMTEK

Klaus Hannemann

German Aerospace Center (DLR)

Tetsuji Sunami Japanese Aerospace Exploration Agency (JAXA)

Gennaro Russo

Italian Aerospace Research Center (CIRA)

Graham Candler

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University of Minnesota (UMN)

Stuart Kearney Australian Youth Aerospace Association (AYAA)

Access to space is necessary for the deployment of space-based systems and technologies for communications, remote sensing, space science, and so on. It is a major technological challenge of the 21st century for all nations due to the dependence of the global economy on assured and secure access to space-based services. The most promising way to meet this challenge is to extend aeronautical technology to hypersonic vehicles powered, at least partially, by supersonic combustion airbreathing engines (scramjets). Scramjets can be combined with rockets to produce a more fuel-efficient hybrid launch system. Australia's present focus is to achieve working concept technology demonstrators which can achieve scramjet-powered atmospheric flight, at Mach 8. The ultimate aim is to develop mature scramjets which can operate at much higher Mach numbers, to accelerate a vehicle to the speed required to leave the earth’s atmosphere. The first step in this process is being taken by the recently funded project “Scramjet-based Access-to-Space Systems”, or SCRAMSPACE. SCRAMSPACE is a $14M, 13-member international project led by UQ and including : UNSW@ADFA, UA, USQ, DSTO, BAe Systems, AIMTEK, Teakle Composites, AYAA, DLR, CIRA, JAXA, and UMN. The Australian Government has invested $5M in SCRAMSPACE through the Australian Space Research Program (ASRP). The objectives of SCRAMSPACE are both scientific and strategic. Firstly, we will use our hypersonic ground testing facilities, in particular the unique X3 expansion tunnel at UQ, to push the upper limits of scramjet operation for access-to-space purposes. This ground test research is innovative, will address key S&T questions for such scramjets, and will maintain Australia at the forefront of world scramjet research for access to space. Secondly, we will deliver an advanced free-flying scramjet flight experiment, SCRAMSPACE I, at the entry point to the Mach 8-14 access-to-space range for scramjets. The in-flight performance of an exciting, innovative and commercially-attractive scramjet concept being explored jointly by UQ and DSTO, as well as high temperature materials with embedded sensors, and novel laser-based flight instrumentation, will be demonstrated. In so doing, SCRAMSPACE will

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build an experienced and immediately-industry-ready team of flight scientists/ engineers that will contribute to the talent pool for a future Australian access-to-space capability. We will directly involve Australian space-related industry, at both small-to-medium-enterprise and large company level, so that the project benefits from industry capability and so that industry acquires enhanced skills, expertise and capacity. The full paper will outline the SCRAMSPACE project and report on progress to date.

Numerical Considerations for the Simulation of Supersonic Combustion Ramjet Intakes

Laurie Brown

Centre for Hypersonics, University of Queensland This paper addresses the difficulties found when attempting to numerically simulate an important aerothermodynamic phenomenon that is responsible for producing substantial localised heating - shock wave/boundary layer interactions (SWBLI). SWBLI are important physical phenomena that can occur in many critical locations over a hypersonic vehicle. A SWBLI forms whenever a shock wave encounters, or is generated by, an aerodynamic surface. They are especially important within supersonic combustion airbreathing engines (scramjet). When combined with rocket technology, scramjet engines offer significant efficiencies over conventional access-to-space launch vehicles. SWBLI have profound implications upon the performance and structural integrity of scramjets. SWBLI can cause substantial increases in drag, a reduction in mass capture into the combustion chamber or even extinguish combustion altogether through the process of ‘engine unstart’. Correctly predicting the intense localised heating produced by the SWBLI must be performed to ensure sufficient heat shielding is in place to prevent material failure. Scaled tests within ground-based experimental facilities cannot always replicate the full complement of flight conditions that a hypersonic vehicle experiences. Validating computational fluid dynamics (CFD) tools against experiment is therefore the ideal means with which to bridge this gap and provide the information necessary to mitigate the deleterious effects of SWBLI within access-to-space scramjet vehicles.

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This paper presents the results of a detailed study into the effect of numerical factors that affect the prediction of hypersonic SWBLI pressure and heat flux loads within 2nd order accurate total variation diminishing finite volume CFD schemes. Specific emphasis is placed on correct grid generation practices, application of artificial dissipation schemes and the calculation of thermal conductivity to provide ‘best practise’ guidelines for the numerical simulation of hypersonic SWBLI flows. Code-to-code comparisons are performed for a 15∞ compression corner case study, which demonstrates that these best-practise methodologies can eliminate the large discrepancies previously reported between CFD codes.

An Electrodynamic Tether System for Picosatellites

D. Bunker1, Dr. S. Sukkarieh2

1Saber Astronautics Australia Pty Ltd 2Australian Centre for Field Robotics, University of Sydney, Australia

With an escalating interest in electrodynamic tether systems and spacecraft subsystem testing on low-cost picosatellites, the mergence of the two is imminent. This paper presents the development of an electrodynamic tether system for both power generation and de-orbit applications aboard CubeSats. A systems engineering approach to tether design is used, with a rigorous mathematical analysis implemented that models the power generated in the tether using orbit motion limited theory. Our analysis showed that a conventional picosatellite in low earth orbit can produce approximately 330mW of additional power with a 200m Aracon tether. The resultant drag induced by the tether will lead to de-orbit in a number of weeks, leaving enough time to complete many mission objectives while surreptitiously rendering the spacecraft obsolete at end of life. Our final system was manufactured from aluminium 6061 and weighed approximately 95 grams, taking up less than 10% of the total internal volume of a CubeSat. We present this system for incorporation into future picosatellites to provide additional power for the onboard electronics, especially on the dark-side of the orbit where solar panels are unable to provide energy. Such a system will also allow for the removal of spent satellites at end of mission life, hence reducing the accumulation of space junk at low orbital altitudes. As such, it holds promise to provide added redundancy, additional power and lessen the environmental impact of small satellite missions.

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Beagle 2 Mars Lander Flight Dynamics Investigation via Experiment and Simulation

David Buttsworth and Michael Jokic University of Southern Queensland

In this paper we outline the experimental and simulated flight dynamics of a Beagle 2 Mars lander test model. Experimental observations were made at Mach 2 flow conditions in the USQ wind tunnel facility using a schlieren system with a video rate of 210 frames per second. By processing the video, we were able to extract the pitch angle of the model as a function of time. We are able to clearly show a growth in the pitch oscillations of the 20 mm diameter model prior to any break-down in the experimental flow. The observed behaviour of the Beagle 2 lander test vehicle has been simulated using a model developed in MATLAB/Simulink. We report on the design of the model and the agreement achieved with respect to the experimental observations. The simulation model has been developed to verify the observed dynamic behaviour and to facilitate the design of the next set of experiments in the USQ facility.

Modelling of the effects of ionospheric disturbances using 3D

magneto-ionic raytracing techniques

Manuel Cervera and Trevor Harris Defence Science and Technology Organisation

Ionospheric disturbances are manifest over a large range of spatial and temporal scales. Currently DSTO has a good understanding of these disturbances at the largest scales (> 1000 km and > 15 min) through its network of vertical incident sounders. However, we are interested in investigating these disturbances at much smaller scale sizes. To this end, DSTO has initiated an experimental programme, SpICE or Spatial Ionospheric Correlation Experiment. This programme seeks to understand these ionospheric disturbances at scales < 150 km and temporal resolutions under 1 minute. In this paper we use 3D magneto-ionic Hamiltonian raytracing techniques to model and understand the various ionospheric disturbances giving rise to the effects we observe in our data.

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Australian research on plasma thrusters for spacecraft propulsion

Christine Charles

Space Plasma, Power & Propulsion Group (SP3) Research School of Physics & Engineering

The Australian National University (ANU), Acton, ACT 0200, Australia The current state of Australian research and development on plasma thrusters for spacecraft propulsion is presented. Recent studies on three distinct electric thrusters demonstrate Australia’s key contribution to future electric propulsion missions: these are the Helicon Double Layer Thruster (HDLT) and the Dual Stage Four Grids (DS4G) thruster at the Australian National University (ANU), and the asymmetric hollow cathode thruster at the University of Sydney. The HDLT is a new low-divergence electrode-less magneto-plasma space thruster with extended lifetime with a first generation prototype fully designed and fabricated in Australia in 2004 and tested at the European Space Agency in 2005. Since late 2006, the SP3 group has been developing the HDLT in collaboration with EADS-ASTRIUM, the largest space company in the world. In March 2009, EADS-ASTRIUM decided to fund the University of Surrey, as a part of ASTRIUM’s continuous investment in innovative space technologies, to produce a second generation Helicon Double Layer Thruster (HDLT) prototype suitable for space use, with a launch in 2013. A 3 ways collaboration has been officially established between ASTRIUM, the Surrey Space Center (University of Surrey, UK) and the ANU. The first DS4G ion thruster prototype was designed and built by a small Australian team and successfully tested at the European Space Agency in late 2005 and mid 2006. This prototype is currently in Europe. In 2007, a new thruster concept was also developed at the University of Sydney: this electric thruster makes use of the properties of an asymmetric hollow cathode glow discharge that ejects a collimated plume of high velocity neutral atoms. Helicon thrusters and other types of thruster are being developed worldwide. Australia currently does not have a large thermal vacuum chamber with thrust measurement capabilities, a key factor for further development of all Australian thrusters. An adequate site at the Mount Stromlo observatory in Canberra has been proposed but to date, we have not been able to attract any funding.

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Monitoring Geologic Sequestration with Radar Remote Sensing

Rattanasuda Cholathat, Linlin Ge, Xiaojing Li and Chris Rizos, School of Surveying & Spatial Information Systems, UNSW

Carbon dioxide is the major greenhouse gases generated by human activities which cause extreme weather such as storms, bushfires, floods, droughts and heat wave will become more prevalent and more intense. In order to maintain the atmospheric concentration of CO2, Geologic Carbon Sequestration is an essential instrument which has been aimed for mitigation of global warming. However, more understanding of storage processes and confirm their effective, assess environmental, safety, and health impacts in the event of a leak to the atmosphere are certainly important. Therefore, monitoring is one of the answer enabling technologies for CO2 storage. It is expected to support multiple purposes from providing information about safety and environmental concerns such as used to optimize storage projects, deal with unintended leakage and address regulatory, legal and social issues. Particularly, satellite radar remote sensing will be a necessary tool to monitoring subsurface deformation after injected CO2 underground. DInSAR is the powerful tool which can contribute to measure ground deformation to assess the movement of CO2 in the ground-surface up to millimetre scale. An evaluation of the storage stability, uplift could be one of the indicators for a potential storage leak. The CO2CRC Otway storage Project is the first advanced geosequestration project in Australia and the world’s largest research and demonstration project. Therefore, it will be the most consider target in South Hemisphere to monitor CO storage by using the technologies which are capable of delivering deep, cost-effective, and sustained emissions reductions such as Differential Interferometrie for Synthetic Aperture Radar (DInSAR) technique.

Stars to Planets to Life: An Elemental Scheme

Aditya Chopra and Charles Lineweaver Planetary Science Institute, The Australian National University

The elemental composition of the planets, moons and asteroids in the solar system reflects to a large extent the composition of the Sun,

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except that relative to the Sun, all are depleted in the most volatile elements hydrogen, helium and the noble gases. When the Sun formed from the solar nebula, volatile elements were swept away by the solar wind from the region of the solar nebula where terrestrial planets formed. Rocky planets like the Earth, accreted from the fractionated nebular condensate whose composition in refractory elements closely resembles the solar composition. Subsequent fractionation of elements through geologic processing and input of water, carbon dioxide and ammonia in the form of chondritic and cometary material onto the Earth's crust led to environments for the origin and evolution of life. We attempt to quantify the biological significance of different elements to life. We present changes in the distribution of elements in environments such as the oceans and examine how changes in the bioavailability of elements such as iron and copper may have affected the evolution of life on Earth over the past ~4 billion years. The process of formation of a star like the Sun, out of a collapsing molecular cloud polluted by heavy elements from earlier generation of stars, is observed wherever there are molecular clouds. The associated process of terrestrial planet formation is probably common in the universe and it is likely that the elemental abundances of the surfaces of extrasolar habitable planets will also be similar to cosmic abundances as represented by the Sun. We present a scheme to infer the elemental composition and metabolic processes of the extraterrestrial life from the elemental composition of the host exoplanetary system and the observed elemental fractionation between the Sun, the bulk Earth, the Earth's crust, the biosphere and life.

VSTAR modelling of the Jupiter clouds.

Lucyna Kedziora-Chudczer School of Physics, University of New South Wales

We used the IRIS2 instrument on the Anglo Australian Telescope to acquire spectra of Jupiter's atmosphere in the near-infrared H and K-bands. The spectra of zones and belts visible in the narrowband CH$_{4}$ image were compared with the models obtained by use of

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VSTAR, the line-by-line radiative transfer package. VSTAR was developed to model atmospheres of the Solar and extra-solar planets. Here we demonstrate its functionality by a reliable retrieval of the vertical and longitudinal distribution of aerosols in Jupiter's atmosphere.

High Level Risk Analysis and Decision Making for an Autonomous Mars Glider

Jen Jen Chung and Salah Sukkarieh Australian Centre for Field Robotics University of Sydney, NSW Australia

The ARES (Aerial Regional-scale Environmental Survey of Mars) glider project is an ongoing NASA program that aims to design a fully autonomous glider system to survey the Martian landscape from a gliding altitude of one mile. To prolong the mission endurance, it is desirable for the glider to actively seek out and exploit available energy sources such as thermal columns in the atmosphere in parallel to performing its surveillance mission. To attain the desired level of autonomy in terms of managing the competing objectives of exploring and exploiting the environment, it is proposed that a Bayesian Forecast-Decision System (BFS) is an effective method for real-time risk assessment and decision formulation for an autonomous glider performing point-to-point travel in an unknown and changing environment. The BFS predicts thermal motion according to a forecast model, and applies the Bayesian Processor of Forecast (BPF) to detect and manage the contribution of model and input uncertainties associated with glider sensor data and forecast data to produce a posterior distribution over future thermal positions. The role of the decision model of the BFS is to select the next waypoint by assessing the risk associated with traversing available paths through the environment, where risk is computed according to goal point reachability and the map uncertainty as quantified by the BPF. The results of this paper show that the forecast decision system requires very little a priori information to effectively gauge the system uncertainties and manage platform energy to navigate efficiently to the allocated goal point. Furthermore, it is shown that the system can run in real-time on an autonomous sensing and reacting system operating in a dynamic environment.

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Spaceward Bound Australia – Pilbara 2011 – and it’s

predecessors

David Cooper Mars Society Australia, Association of Mars Explorers

Spaceward bound is an educational program developed at NASA Ames Research Center. The mission of Spaceward Bound is to train the next generation of space explorers by having students and teachers participate in the exploration of scientifically interesting but remote and extreme environments on Earth as analogs for human exploration of the Moon and Mars. Spaceward Bound supports the second major NASA education goal to attract and retain students in STEM (Pre-Service Teacher - Science, Technology, Engineering and Mathematics) disciplines through a progression of educational opportunities for undergraduate and graduate students in STEM and Education, pre-service and in-service STEM K-12 teachers as well as STEM education faculty. After signing a Memorandum of Understanding with NASA Ames in 2007, we have undertaken two expeditions to the Flinders Ranges in South Australia in 2008 and 2009 involving scientists and secondary science teachers form both Australia and the USA. In 2011, we will be carrying out the first SBA expedition to the Pilbara. International expeditions with Spaceward Bound Australia’s involvement have taken Australian Educators to the Mojave Desert, USA and the deserts of Namibia. I will explain the benefits for Australians in the establishment of Spaceward Bound Australia, an initiative of the Mars Society Australia, Inc., a not-for-profit research and education organisation.

Australian Research on Solar Physics

Alina Donea Centre for Stellar and Planetary Astrophysics,

Monash University

The Sun has entered the solar cycle 24 very quietly, following an unexpected long and silent period of time. As the Sun awakens, we

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expect to collect a wealth of data about our star and its activity mainly from recently launched satellites. Solar flares, solar quakes, solar tsunamis and other magnetic and acoustic waves on the solar surface are only a few of the interesting aspects of the solar physics in Australia which I will present in my talk.

Ausroc Nano Intertank Fairing Structural Analysis and Design

Thomas Fahey RMIT University

The Australian Space Research Institute (ASRI) has identified the need to develop an Australian satellite launch vehicle and to develop the associated skills in this field. Since the creation of the Ausroc program, ASRI has worked in close collaboration with universities, especially RMIT to develop a series of rockets that are designed to be incremental steps in the development of a full-scale satellite launch vehicle with mature hardware. It is hoped that the Ausroc program will establish a low cost competitive rocket to meet the needs of the current market.

The Ausroc Nano vehicle aims to deliver a 10kg payload into a minimum polar low earth orbit (LEO) of 250km. The rocket has just completed the initial preliminary design stage, with this project a continuation of previous years research in developing a feasible, low cost, optimized design for manufacture. In particular this project is focused on the inter-tank fairings to develop a model for production and testing.

Completing this required a detailed stress analysis where the

loading conditions were examined to identify the critical deign loads, occurring at the maximum dynamic pressure. Once the design limit loads were known a theoretical analysis could be completed for different materials based on buckling equations. After the results were determined to be within the acceptable margin of safety, a CAD model of inter-tank fairing was developed and with the loading conditions an analysis was performed. With the correlation of results within an acceptable margin, this design was used as the basis of manufacturing the critical inter-tank fairing. This component was then further tested to verify the results and show that the manufacturing process was feasible and low cost. This design will be then integrated as a part of the Ausroc Nano overall design.

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Rocket Booster Design for Scramjet-Assisted Access-to-Space Vehicles

Thomas Ferguson, Thomas Jazra and Michael Kevin Smart

Centre for Hypersonics, The University of Queensland The option of scramjet-assisted access to space is a key focus at The University of Queensland's Centre for Hypersonics. A three-stage, rocket-scramjet-rocket configuration is envisaged for fulfilment of this task. The present paper introduces an engineering approach to the design of the liquid-hydrogen-fuelled first and third stages of such a launch vehicle, a fixed-design scramjet-powered second stage provided. The design process involves minimising the fuel mass required by stages I and III, respectively, while catering for the predetermined flight envelope of the airbreathing second stage. The specifications of the engine types installed and the structural mass of the two boosters are inferred from the data of existing rocket stages. With the design of all three stages completed, the payload mass fraction of the launch vehicle is computed for payload delivery to a low Earth orbit (200 km). Three airbreathers, different in size and shape, were used in this work to assemble and evaluate three rocket-scramjet-rocket configurations. The payload mass fractions determined (0.68%, 0.73% and 0.77%) compare satisfactorily to those of established rocket-powered launch vehicles of similar gross mass (0.4-0.7%). The results further quantify the often-cited potential of scramjets for access to space, despite the current low level of maturity of the (so far computer-modelled) scramjet technology. It is shown that the configuration with the smallest airbreather achieves the best overall performance which may be a trend worth exploring in more depth.

Laser Tracking of Space Debris

Yue Gao, Craig Smith, Ben Greene EOS Space Systems Pty Ltd

A quick overview about EOS, especially about EOS space technologies, research and development will be given first. Then the advantages of tracking space debris using laser in comparison with conventional radar technologies, and some preliminary results and milestones EOS has achieved with tracking space debris using laser in the last several years will be described. Finally some activities

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proposed for the ASRP Round-2 program - Automated Laser Tracking of Space Debris will be presented. Integration of remotely sensed indices for land cover changes

caused by the 2009 Victorian bushfires using Landsat TM imagery

Li Guo, Linlin Ge, and Xiaojing Li

School of Surveying and Spatial Information Systems, University of New South Wales, Australia

The 2009 Victorian bushfires, also called the Black Saturday bushfires, ignited across the Australian state of Victoria on Saturday 7th February 2009, resulting in Australia’s highest ever loss of life from a bushfire. According to the Victorian Police, the bushfires caused at least 173 known deaths of people and 414 people injured. The use of multispectral Landsat Thematic Mapper (TM) data was able to detect and analyse the land cover changes caused by the bushfires in a rapid and cost-effective way. Although the existence of vegetation is usually the primarily indicator to identify the location of bushfires, the evaluation of greenness information such as Normalised Difference Vegetation Index (NDVI) cannot fully exclude the surface change information caused by other factors. In addition, NDVI is inaccurate where fires occur after vegetation has died as well as areas that had already regrown. Thus, this research work contributes to exploit all surface change information using different indices derived from multispectral Landsat TM data related to bushfire detection, such as NDVI, Normalised Difference Water Index (NDWI), Normalised Burn Ratio (NBR) and Tasseled Cap (TC) transformation, and a new bushfire detection procedure is implemented in order to provide an efficient way to locate the bushfires.

SpICE: A Program to Study Small-Scale Disturbances in the Ionosphere

T. J. Harris and M. A. Cervera

Intelligence, Surveillance and Reconnaisance Division Defence Science and Technology Organisation PO Box 1500, Edinburgh SA 5111,

Australia. Ionospheric disturbances observed by bottom-side soundings appear

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at many temporal and spatial scales. Australia has many simultaneous observations from vertically orientated sounders with spatial separations on the scale of 1000km. However, with this spatial sampling only large scale ionospheric disturbances can be mapped and subsequently modelled. DSTO has an experiment based program in progress to investigate the smaller spatial scale disturbances. These are often seen on vertical incidence soundings and are uncorrelated with soundings from greater than 500km away. They can also be uncorrelated with soundings from the same site only 15 minutes later. The DSTO program to investigate these ionospheric disturbances is called SpICE, for Spatial Ionospheric Correlation Experiment. SpICE uses a small set of transmitters and receivers with varying separations to achieve a geographically spread set of near- vertical incidence ionospheric reflection points separated by 50-150km. Using the latest digital receiver technology we can collect continuous wave transmissions from a nearby transmitter that is rapidly sweeping through the HF band and process the signal at a very high resolution to achieve good signal-to-noise ionograms at better than one-minute time updates. To date there have been three SpICE campaigns. The first campaign was a mid- latitude experiment conducted in the countryside east of Adelaide, Australia (~35°S, magnetic inclination ~67° upwards and declination ~8°E). HF transmitters and receivers were deployed to form an approximate equilateral triangle of oblique and near-vertical ionospheric soundings with ~300km baselines. Ionograms were collected every 60 seconds on the 4 paths formed. This revealed many strange and exciting disturbance features. The second campaign was conducted in the Australian low latitudes (~18°S, magnetic inclination ~47° upward and declination ~7°E) and explored closer geometries and faster ionogram update rates. The third campaign was conducted in Puerto Rico in the northern hemisphere at magnetic dip and geometries equivalent to the second campaign (~18°N, magnetic inclination ~44° downward and declination ~12°W). This paper will discuss the SpICE program goals and highlight some of the unusual features observed so far. The temporal behaviour of medium and small scale disturbances will also be explored.

Hypersonic Inlet for a Laser Powered Propulsion System and its Interaction with an Idealized Laser Induced Detonation

Wave

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Alan Harrland School of Mechanical Engineering, University of Adelaide

The idea of laser powered lightcraft was first conceptualised in the early 1970's as a means of launching small scale satellite payloads into orbit with a much lower cost in comparison to conventional techniques. Interest has recently been renewed in laser powered lightcraft vehicles by the United States Air Force. Propulsion is produced via laser induced detonation of an incoming hypersonic air stream. This highly sensitive process requires suitable engine configurations that offer good performance over all flight speeds and angles of attack to ensure the required thrust is maintained. The method of stream traced hypersonic inlets has demonstrated the required performance in conventional hydrocarbon fuelled scramjet engines, and this process has been applied to the laser powered lightcraft vehicle. This paper will outline the current research into the stream traced inlet design methodology being developed, with a particular focus on the interaction between the laser induced detonation wave and the resulting inlet. An ideal computational fluid dynamics model has been produced to approximate the thrust produced by the detonation and it's interaction with the vehicle. The performance of the lightcraft inlet has been evaluated.

Comparative Pattern Evolution and Self-Organization for Dunefields of the Ar Rub’ al Khali Sand Sea, Earth, and the

North Polar Plains, Mars

Mark A. Bishopa,b, Nerida Hectora , Andrew Wheeler a

aBarbara Hardy Institute [Terrain Analogue Understanding (TAU) research]

School of Natural and Built Environments, University of South Australia, Adelaide, SA, 5000 Australia

bPlanetary Science Institute, Tucson, Arizona, 85719, USA

The geographic signature of dune distribution and self-organization, as measured by the R-statistic, offers a viewpoint on the geography of crescentic aeolian systems and proposes an index from which to determine the degree of self-organization across a variety of spatial scales. Using a suite of orbital image data, mega-barchanoids of the

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Ar Rub’ al Khali sand sea (Empty Quarter) and crescentic forms for the north polar plains of Mars were examined by nearest neighbour analysis to discern their geography and processes of spatial development. In both planetary contexts pattern regularity (dispersion) is pervasive however, pattern homogeneity at the global scale contrasts with local scale heterogeneities. Where domes, barchans, barchan-seif and short barchanoid ‘chains’ occur, the degree of self-organization is less than for those regions comprising compound forms. The evolution of crescentic dunes into compound fields identifies with the process of long term self-organization (and maturity) of the aeolian system. Consequently, the degree of self-organization is for the most part regarded to be an association between morphological diversity and dimensional variability. Such associations also have significant bearing on a field’s response to sediment supply, transport capacity and sediment availability. These results infer that aeolian systems reflect, within different spatial regions of the field, the sum of changes that result in the spatially variable states of dune field organization, regardless of planetary context.

Estimating Spacecraft Structural Health Impacts Using Hybrid State Space Models

Dr. Jason Held1, Mr. Nigel Hoschke2, Dr. Don Price2

Saber Astronautics Australia, Pty Ltd1

8/5 Osborne Road, Manly NSW CSIRO Materials Science and Engineering2

P.O.Box 218, Lindfield, NSW

Research into structural health management has resulted in increased ability to sense debris impacts using a network of passive sensors along a structure. A key area open for research is ways to understand the nature of the impact and estimate its strength given certain sensor conditions. This is especially important for spacecraft because of the challenges in recording sensor impact data in a radiated environment which can cause false or missing sensor readings with onboard data logging. This paper presents a non-linear state-space model which can estimate the state of an impact sensor. The model uses a Dynamic Bayesian Network (DBN) to handle time series data and a Gaussian Mixture Model (GMM) to handle switching states. DBNs are successful in determining highly complex, nonlinear interactions with emergent

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properties and missing data. It has shown to produce equivalent solutions to Hidden Markov Models and Kalmann Filters but does not require process noise. This makes them suitable to learning complex models but only if sensor vibration interactions remain in the same state. Switching states in a DBN would require a separate model or “hidden nodes”, which are computationally expensive and require domain knowledge. Gaussian Mixture Models (GMMs) are widely used in the computer vision recognition to discretely identify objects in an image. GMMs are used to identify statistical data mixtures, allowing the system to switch to the most accurate DBN model needed at that time. The combination also has the potential to statistically identify failure modes and anomalies, which may also occur during a space weather event. Hard and soft structural impacts were collected using CSIRO’s Self-organised Sentient Structures (SOSS) project demonstrator. Results demonstrated a high degree of accuracy using the DBN/GMM model and evidence suggests that this approach can result in a general modeling solution independent of the strength of the impact.

The Operationally Responsive Space Project

Dr. Jason Held, Dr. Alex Green, Mr. Michael Lamont

Saber Astronautics Australia Pty Ltd The Operationally Responsive Space (ORS) project addresses spacecraft mission maintenance, where mission is defined as operating the spacecraft to best accomplish tasks useful to downstream customers. The customer can be a firefighter operations center needing timely satellite imagery, a military command center, or environmental research operation. Mission responsiveness maintains the health of the spacecraft with awareness of dynamic space environments and customer needs. Previous approaches to ORS have trouble because of the difficulty in tracking spacecraft performance. The spacecraft operates in a dynamic environment. Attempts to model spacecraft at the ground station are limited due to a lack of joint representations. Downstream customers, the reason why expensive spacecraft exist in the first place, also have no connectivity with any existing performance models. We have formed an international coalition to develop the tactics, techniques, and procedures for ORS to make Australia a key global

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player in space operations. This involves technology development in space systems, collaboration with the international space operations community, as well enabling fundamental university research. The first step in solving the ORS problem is a common framework allowing the dynamic interconnection between environment, spacecraft, ground station, and mission health to be analyzed as a “Systems of Systems”. Using a single framework allows learning information about their interactions and interconnections. This knowledge tells us how a space environment condition (such as weather event) impacts the spacecraft, its individual subsystems, and the downstream mission. With knowledge, responsive control required for ORS becomes possible. Solving this problem represents a significant advance in spacecraft operations because it brings spacecraft health into context with the space environment as well as mission metrics, all within the same analytical model. This research will provide perception on the total space mission operation, which is the primary prerequisite to making spacecraft responsive to downstream user needs.

Type II Solar Radio Bursts : Extraction of shock parameters and detailed comparison of theory with observations

Dean Hillan, Iver Cairns and Peter Robinson,

School of Physics, University of Sydney We use the current type II theory and a data-driven solar wind model to simulate dynamic spectra of type II bursts. We start by developing techniques and performance metrics for extraction of model shock parameters. An iterative downhill simplex method is used, which compares two dynamic spectra and quantitatively assesses and then improves the agreement using two performance metrics; the first is based on the correlation function and the second is based on a normalized difference. By maximizing the agreement we are able to extract the input model shock parameters to within 30% or better when using model solar winds of increasing complexity. When using a realistic solar wind model, the parameters are recovered very accurately, generally to within a few percent of the correct solution. We then quantitatively compare the theory with observations and extract the parameters of the shocks for three well observed type II events. We first obtain good qualitative and semi-quantitative agreement (40-50% correlations) between the predicted and observed dynamic spectra using estimates of shock parameters from

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LASCO/SOHO coronal mass ejections (CME) observations. The iterative downhill simplex method with the two assessment parameters then extracts model shock parameters that increase the agreement between theory and observation in terms of relative flux levels, spectral intensifications and drift rates. The assessment parameters agree qualitatively and semi-quantitatively with the parameters estimated from CME observations (speed, size and expansion index) for two events. Quantitatively, the simulated radio emission is typically overpredicted for each event by around 5 dB. Parameter extraction for the third event leads to improved agreement for only a range of times and frequencies in the dynamic spectra, and leads to an implausible shock size. The theory and methods show great potential in space weather prediction and remote inference of CME-driven shock parameters.

Artificial Muscles for EVA Space Glove Design

Jed Guinto and Associate Professor Lachlan Thompson RMIT University, Melbourne, Australia

With NASA setting goals for returning to the moon by 2018 and reaching Mars by 2030 the current space glove requires drastic improvements. The current spacesuit has one major contradiction which is the source of continued discussion amongst researchers. How do you provide adequate breathing pressure, whilst not causing the suit to balloon into a rigid shell which renders the user almost immobilized? Simple tasks such as squeezing have become tests of human strength and endurance due to this pressurization. One astronaut claiming the squeeze action is like squeezing a tennis ball. Severe blistering and bleeding are just some of the symptoms which occur due to the scraping of the skin against the suit. Finger nails have been known to rip off and knuckles have been left with a fiery red rawness. Feeling in the hand slowly diminishes until eventually the fingers feel almost broken. At this point heavy fatigue would set in and EVA would usually come to a halt. By increasing the strength output of the user through the use of polymers strips onto individual fingers, the energy expenditure of the astronaut and the force he/she applies to the inner layers of the suit will be reduced, thus eliminating the afore mentioned issues and dramatically increasing efficiency and space walk time. Polymers can bend, shrink, expand, solidify or elongate when activated by an electrical, optical, chemical, magnetic or thermal signal. Tests have shown that one particular polymer known as PAN fibre, can exhibit more than 150 grams of deformation force in less than 100 milliseconds. Amazingly, this test was carried

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out with a PAN fibre strip weighing only 0.2 grams. Polymers such as this will become the artificial muscles of the hand to increase strength, reliability, comfort, control and dexterity of the hand during EVA.

Computational Investigation Of An Axisymmetric Scramjet Configuration

D.C. Hunt*, R.R. Boyce**, A. Paull ***

* Applied Hypersonics, Defence Science and Technology Organisation, Brisbane, Australia; Centre for Hypersonics, The University of

Queensland, Brisbane Australia ** Centre for Hypersonics, The University of Queensland, Brisbane

Australia *** Applied Hypersonics, Defence Science and Technology

Organisation, Brisbane, Australia This paper reports on the CFD results of an inward turning axisymmetric scramjet in comparison to the experimental data reported on in [1]. These experiments investigated an axisymmetric scramjet configuration based on the concept of radical farming. Through surface pressure measurements the experiments demonstrated significant heat release where mean combustor conditions were too low for hydrogen combustion supporting the theory of radical farming. Initial CFD with fuel-off and pre-mixed fuel-on reported in [1] show discrepancies between the CFD and the experimental data. In the fuel-off case the discrepancy in surface pressures with CFD increased with distance along the scramjet. In the premixed fuel-on cases the combustion model appeared to over predict ignition and reaction times. Recent work by Schloegel & Boyce [2] and Boyce [3] have demonstrated the sensitivity of computational analysis to this class of scramjet to nozzle flow non-uniformity, and turbulence and combustion models. A CFD study has been conducted accounting for nozzle non-uniformity based on the experimental pitot survey, correction of the leading edge from as-designed to as-measured, and using the shear stress transport (SST) turbulence model. In addition, while the experimental results were nominally at zero degrees angle of attack, 3D CFD analysis indicates a possible slight misalignment of the tunnel nozzle and scramjet axes of approximately 0.5 degrees (Figure 1). A comparison of the Evans & Schexnayder combustion model used in [2] with the Jackimowsky model used in [1] will also be conducted

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with pre-mixed calculations at equivalence ratios ranging from 0.2 to 0.7. References [1] Hunt D.C., Paull A., Boyce R.R., Hagenmaier M.,

Investigation of an Axisymmetric Scramjet configuration Utilising Inlet Injection and Radical Farming, International Symposium on Air Breathing Engines, 2009

[2] Schloegel F., Boyce R.R., CFD Analysis of Radical Farming Concept Scramjet Engine, 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, AIAA2009-7416, 2009

[3] Boyce R.R., Private Communication , 2010

HAYABUSA RETURNS

Trevor Ireland Research School of Earth Sciences and Planetary Science Institute

The Australian National University Canberra ACT 0200

The purpose of the Hayabusa Mission of the Japanese Aerospace Exploration Agency (JAXA) was to demonstrate the technologies necessary to complete a sample return mission to a near Earth

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asteroid. The three major technologies developed for this mission were autonomous guidance, ion-engine propulsion, and sampling. The mission launched in 2003 and successfully arrived at the asteroid in November 2005. Upon arrival, asteroid Itokawa was thoroughly imaged and characterized for many physical characteristics. The main space craft touched down twice to obtain samples. The mechanism for sampling involved a sampling horn that deflects on touchdown, triggering the firing of a projectile into the surface. Ablated material travels up the tube to the sample container in the sample return capsule. On the first touch down attempt, a safety interlock stopped the firing of the gun and so only accidental capture of material is expected. On the second touchdown, a computer malfunction immediately after touchdown prevented transfer of data back to Earth and was quickly followed by a malfunction in the chemical thrusters. The thrusters fired all of the propellant sending the sapcecraft into a chaotic spin. Without control of the spacecraft, the Earth-return leg to return in 2007 could not be achieved. Recontrol of the spacecraft was achieved in 2006 and an Earth-return rescheduled for 2010. The return to Earth was largely uneventful. The loss of one of the neutralizers on one engine was overcome by using the neutrlizer from one of the other engines. On return to Earth, the control manoeuvres worked flawlessly and the SRC landed in Woomera on June 13, 2010. The SRC has now been opened and the contents of the containers are now being examined. An update on progress in terms of the sample characterization will be presented.

Planetary Phase Models - Searching For Life

Eriita Jones and Charles Lineweaver Planetary Science Institute, Research School of Astronomy and

Astrophysics, Research School of Earth Sciences, Australian National University

Terrestrial life is known to require liquid water, however studies into the extreme habitats of microbial life have revealed apparent temperature and potential salinity limits on the environments which support life. These limits fall within the stability regime of liquid water, indicating that there may exist liquid water on Earth without life. Such a conclusion would necessarily force us to re-define our strategies in searching for extant life. In this paper we present out published pressure-temperature model of the Earth which we used to investigate the primary requirements of life and quantify the limits on

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the habitability of liquid water. We find that ~88% of the volume of the Earth where liquid water exists is not known to host active life, and we identify the regions of potentially uninhabited terrestrial water. We will also present our current work on a pressure-temperature model for present day Mars, and apply the limits of terrestrial life to this model to investigate the depths on Mars at which terrestrial-like life could potentially survive. We will also discuss the likelihood of liquid water and its activity in these subsurface Martian environments.

Temperature Estimation of the Hayabusa Capsule during Re-entry via direct Near Infrared Imaging

Michael Jokic, David Buttsworth and Albert Chong

University of Southern Queensland

This paper presents our analysis of near infrared imaging of the Hayabusa capsule during re-entry. Observations were made during the Hayabusa re-entry during the evening of the 13th of June 2010 at 30∫ 43.092' South and 134∫ 29.414' East. Two commercially available high-definition cameras were used to observe the re-entry. The Canon Legria HFS11 and the Sony HDR-HC3E both have night mode capabilities that offer enhanced object detection. We have calibrated the Sony camera while in night-shot mode to determine its spectral response and pixel intensity as a function of temperature. The Sony was used to manually track the re-entry from first detection near Beta-Leonis until the capsule was lost. We report the black-body temperature profile of the capsule from bus break-up including peak heating. We also present the process and results of our calibration, and report on the observation field trip.

Thermal Land Cover Map of Mars (a GIS-based Study)

Eriita Jones, Planetary Science Institute, Research School of Astronomy an Astrophysics, Research School of Earth Sciences,

Australian National University Jonathan Clarke, Mars Society Australia

Frank Mills, Research School of Physics & Engineering and The Fenner School of Environment & Society, Australian National University

Bruce Doran, The Fenner School of Environment & Society, Australian National University

Charles Lineweaver, Planetary Science Institute, Research School of

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Astronomy and Astrophysics, Research School of Earth Sciences, Australian National University

Maps of thermal inertia-albedo units and thermal inertia-elevation units on the Martian surface were published in 2005 by Putzig & Mellon (Icarus 173, pp325-341; later updated in Putzig: PhD Dissertation, 2006, Thermal inertia and surface heterogeneity on Mars). The units were interpreted as distinct mixtures of materials on the surface (eg. fines, rock + bedrock, ice). We are conducting sophisticated unsupervised classifications of TES thermal inertia, TES albedo, MOLA elevation, THEMIS infra-red emission and modelled surface temperatures, using neural networks and hard and soft classifiers. The methods used here differ from those Putzig and Mellon used as they are largely unsupervised and we are including relevant thermal data on surface infra-red emission (from THEMIS) and surface temperature variations from the MAIC-2 climate model (Greve et al., 2010, Planet. & Space Sci. 58, 931-940). The purpose of this study is to provide a more rigorous classification of the Martian surface into land cover units which have distinct thermal behaviours. The properties of these units (their thermal inertia, albedo, and mean and range of surface temperatures within a Martian year) can then be used to model subsurface temperatures and investigate the subsurface stability of water ice. In this talk we will discuss our method and justification and present some preliminary results.

An AUSROC NANO

Chanapat Bhadrakom, Chontisa Kalyanamitra, Pongpaiboon Akapaiboon, Siwat Koekiatpibul, Thanit Chanjarhatpong, Toppak

Chiammunchit

School of Aerospace, Mechanical and Manufacturing Engineering, RMIT University

ASRI (Australian Space Research Institution) is the non-profit organization devoted to space technology is Australia. Its main projects include the development of Launch Vehicle. One of the well known development program at the moment is the AUSROC launch vehicle. The ultimate goal is to develop a microsatellite launch vehicle utilizing technology that can be scaled up for use in heavier launch vehicles.

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The AUSROC Launch Vehicle Program has been underway since 1988. Ausroc family includes AUSROC 1, AUSCROC 2, AUSCROC 2.5, AUSCROC 3, AUSCROC 4. AUSROC NANO is the launch vehicle designed to carry up to 10 kg payload deliver into low earth orbit. The goal of this project is to take part in designing, analyzing, optimizing, manufacturing, and launching the vehicle. AUSROC program cooperate with many top universities and organizations such as University of Queensland, and RMIT University. Up until 2009, AUSROC NANO had been designed to the preliminary stage with some optimization made. AUSROC NANO is a three stages rocket, the first and second stages are liquid engines while the third stage is a solid engine. This year project will carry the work into more detailed design. The focus of development on the first stage is the engine system. One of the goals is to optimize and manufacture the tube used to carry the fuel into the injector, serving as the engine cooling system as well. The tubes will be attached around the combustion chamber. The task includes the method to expand one end of the tube to fit around the combustion chamber (by pressing the tube is not sufficient to give the dimension required) and also to braze them together. Another consideration is the design of upper and lower manifolds, this manifold serve to supply the fuel from propellant tank to injector. There are 2 types of manifolds in first stage that have to be analyzed which are upper and lower manifolds. The second stage also determines and optimizes the engine. Calculating the angle of engine is significant task as well as the method of cooling the engine. In addition, the manifolds are essential part for designing, analyzing and optimizing. Nevertheless, the manifolds of second stage is not similar to first stage due to there is only lower manifolds which is less complicate. The third stage rocket engine of AUSROC Nano project is a solid rocket engine launch vehicle. The primary objective of the third stage design is analysis and optimization of baseline configuration of the third stage rocket, which focuses on separation system, spin mechanism and overall third stage sizing to achieve the ultimate goal of best cost-effective, low-risk, and finalize the launch vehicle design. Moreover, designing and calculating the value of the configuration and its various performance parameters during the optimization process are considered in this project.

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The Mobile Space Academy (MSA) Concept: Practical Hands-on

Science & Engineering Generates Enthusiasm for Space

Timothy Kauffman

TriVector International, Pte Ltd (a private Singapore company) is owned and operated by former NASA engineers with 60 years of NASA space program experience. The Mobile Space Academy (MSA) provides a 5-day space science curriculum to 13- to 19-year old students. The MSA curriculum is delivered by actual NASA rocket scientists, each with 20 years of space flight experience. These rocket scientists have worked on NASA space programs from concept to launch & activation, including hands-on experience with currently orbiting space hardware: the X-37B, Hubble Space Telescope, the International Space Station (ISS) Node 2 “Harmony” and ISS Node 3 “Tranquility.” The curriculum exposes qualified students to the history and basics of space science while they are still choosing an academic career. It is an immersive and highly interactive survey of space science, engineering, including: Astronautics, Life Sciences, Long term effects of micro- and low gravity environments, and in-situ resource utilization (includes student re-enactment of challenging international space contract negotiations). • Satellite communications, navigation and challenges (includes

student re-enactment of a challenging outer space legal conflict, and a live satellite telemetry downlink)

• Astrodynamics & planetary exploration (includes history of astrodynamics and actual remote robotic rover operation)

• Fundamentals of rocketry (includes history of rocketry, and design and launch of a water rocket system).

• Fundamentals of Unmanned Aerial Planetary Exploration (includes program planning, management, & execution of a planetary exploration exercise using an actual unmanned aerial system).

The MSA concept has proven effective in the US and Singapore and promotes an interest in science and engineering with the students, and expands public awareness of the space industry. The authors offer this paper to foster international cooperation in space education, and to elicit ideas for similar education in Australia and other emerging Asia-Pacific space industries.

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NASA ISS Microgravity Research Platform Open for Business

Timothy Kauffman TriVector International, Pte Ltd (a private Singapore company) is owned and operated by former NASA engineers with 60 years of NASA space program experience, including more than 10 years on the International Space Station Program (ISS) Node “Harmony,” the avionics hub of the ISS, and Node 3 “Tranquility,” the US Habitation functionality of the ISS. With the launch of Node 3 "Tranquility" in February 2010, the ISS assembly is complete, and is now accessible as an international microgravity research platform. The purpose of the presentation is to provide information on access to this unique science laboratory in low earth orbit, including: • an overview of the ISS research capabilities and unique

advantages for research; • research opportunities and application processes; • access to services for hardware, software and experiment

integration into the ISS platform; • familiarize interested parties with NASA Payload Planning,

Integration & Operations Process. The International Community built the platform. Now is the time to use it.

Automated Visual Tracking and Spectral Analysis of the Hayabusa Re-entry

Razmi Khan, Troy Eichmann, Ben Upcroft

University of Queensland, Brisbane 4067, QLD, AUSTRALIA David Buttsworth

University of Southern Queensland, Brisbane 4350, QLD, AUSTRALIA This paper presents an automated visual tracking system for the recording of emission spectra during Hayabusa’s atmospheric re-entry. The super-orbital velocities provided a rare opportunity to experimentally measure radiation emitted from the shock-compressed air in front of the capsule at true flight conditions. An automated visual servoing control scheme enabled accurate tracking of the capsule compared to human operation where it is often difficult to keep a target in the field of view.

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The system was composed of two end-effector mounted cameras, a narrow field of view camera combined with a visible-NIR transmission grating to form a spectrograph, and a co-aligned wide field of view tracking camera. Automated tracking was accomplished using optical flow, a computer vision algorithm, which computed the difference between the centre of the camera frame and the visual target. This track error was used to control a pan-tilt servo unit on which the cameras were mounted. An overview of the tracking performance during re-entry, equipment setup, and calibration will be discussed. Each frame recorded by the narrow field camera contains an array of spectra from fragments of the disintegrating main spacecraft body as well as from the intact sample return capsule. Each of these spectra show features of a black body continuum as well as atmospheric absorption and emission lines from superheated materials in the shock layers surrounding each of the falling bodies. A preliminary analysis of the emission spectra will be presented with the objective of furthering our current understanding of the physical processes involved, allowing future theoretical observations to be verified, and demonstrating the effectiveness of our approach. Tracking Australian Quasi-Geosynchronous Space Debris with

the Zadko Telescope

Myrtille Laas-Bourez1, John A. Kennewell2 and David M. Coward3

1,3 International Centre for Radio Astronomy Research

University of Western Australia, Crawley, Western Australia

2 Australian Space Academy, Meckering, Western Australia

3School of Physics, University of Western Australia Crawley WA Australia

A total of 14 Australian satellites have been launched into orbit over a 43 year period. Ten of them were geosynchronous communication satellites. One of the ten failed to deploy from its upper stage and thus never made it to geosynchronous orbit – it decayed into the Earth’s atmosphere together with its booster rocket after 2.5 years. Of the remaining nine, four have reached the end of their usable life and were boosted into supersynchronous orbit. To remain clear of active GEO satellites, these graveyard orbits need to be at least 250 km and preferably over 300 km above true geostationary orbit. This allows manoeuvring space for active satellites and orbit perturbations

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for defunct satellites. The first two defunct Australian GEO satellites do not satisfy this criterion. It is thus essential that they are monitored for potential conjunctions with other geospace objects. We outline a new geosynchronous space debris tracking pilot program using the Western Australian 1-m Zadko Telescope. This fully robotic optical facility is the Australian node of a global robotic telescope network employed to track geosynchronous satellites. We present preliminary orbital data using optical observations of geosynchronous satellites and outline the strategy for obtaining very precise positional data of geosynchronous objects.

Autonomous soaring for atmospheric exploration

Nicholas R.J. Lawrance, Salah Sukkarieh The Australian Centre for Field Robotics, the University of Sydney,

NSW, Australia

Unmanned Aerial Vehicles (UAVs) provide a number of advantages for exploration of bodies in the solar system with atmospheres dense enough to sustain aerodynamic flight. The speed, manoeuvrability and range of aerial vehicles offer significant advantages over ground or space based exploration. However, flight usually requires significant energy input to provide propulsion; requiring additional mass and limiting useful mission duration. The current work aims to reduce this energy requirement through autonomous soaring; the process of capturing energy from the atmosphere during flight. An algorithm is presented which allows simultaneous exploration and exploitation of an atmosphere. An internal wind map is generated using Gaussian process regression on point observations made during flight. The resulting map is used to plan paths which maximise information about the field and collect energy. The method is tested in simulation for environments modelled on the atmospheric properties of Venus and Saturn’s moon Titan. Results demonstrate the ability of the planner to generate paths in energy gain regions such as rising air whilst minimising estimated uncertainty of the atmospheric map. Changes in mode properties versus mode conversion for waves

in Earth's auroral ionosphere

Andrew Layden, Iver Cairns and Peter Robinson School of Physics, University of Sydney

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Plasmas support numerous types of high-frequency waves, including Langmuir waves in the case of an unmagnetized thermal plasma, and whistler and Z-mode waves in a cold magnetized plasma. These are commonly observed by satellites in Earth's ionosphere and magnetosphere. Theories for these waves often invoke generation in one mode and then a mode-conversion process into a distinct mode. A specific example is of observations of Z-mode (whistler-mode) emissions in the weakly (strongly) magnetized regions of the auroral ionosphere, which have been previously interpreted as mode-converted Langmuir waves; this conversion is said to occur because the Z-mode (whistler-mode) dispersion branch is connected to the Langmuir-mode dispersion branch for weakly (strongly) magnetized plasmas. We investigate this hypothesis through dispersion calculations of wave modes in a thermal magnetized plasma. We find that when thermal effects are included, the plasma no longer supports distinct Langmuir, whistler, and Z modes; instead, in the weakly (strongly) magnetized regime there exists a generalized Langmuir-Z (Langmuir-whistler) mode, which has Z-mode (whistler-mode) properties for large wavelengths and Langmuir properties for small wavelengths. Thus, our interpretation of these emissions is that there is no mode-conversion process; rather, these waves propagate in a single mode whose characteristics change as the wave propagates. We also investigate the notion in the literature that these Z-mode waves are electromagnetic by ray-tracing and dispersion calculations, and find that such waves in fact remain predominantly electrostatic as they propagate.

Thermal Correction to the Rate of Second Harmonic Plasma Emission

Brett Layden, School of Physics, University of Sydney

*John Percival, Defence Science and Technology Organisation *Iver Cairns, School of Physics, University of Sydney

*Peter Robinson, School of Physics, University of Sydney Radio emissions at multiples of the local plasma frequency (fp), often termed ìplasma emissionsî, are generated in various regions of our solar system including the solar corona, the interplanetary medium, Earth's foreshock, and the outer heliosphere. The prevailing theory of plasma emission involves nonlinear interactions between three plasma wave modes: ion sound waves, free-space transverse waves, and Langmuir waves (which have frequency close to fp). In this theory, second harmonic (2fp) emission is generated by the coalescence of two Langmuir waves to give a free-space electromagnetic transverse

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wave. Three-wave interactions such as this are described by the quadratic response tensor, which can be used to calculate the interaction rate. Until now, the Langmuir-wave coalescence process has been treated using the cold-plasma quadratic response tensor, in which thermal effects are neglected in the wave coupling. For the first time, we derive a thermal correction to the cold-plasma quadratic response tensor. The expression for the thermal correction is valid for any particle velocity distribution. Applying the thermal correction to the Langmuir-wave coalescence process leads to a substantially enhanced interaction rate when the speed of the electron beam driving the Langmuir waves is a few times the electron thermal speed.

A late flood event in the formation of the Warrego Valles system on Mars.

J. H. J. Leach and Q. J. K. Tan

University of Melbourne, Parkville, Vic, Australia The Warrego Valles drainage system, to the south east of the Tharsis bulge, has long been recognised as one of the best examples of developed dendritic drainage on Mars. The channel formation clearly indicates that most of the system was formed by early pluvial processes. However, the system is located in a region that has a history of tectonic activity and has a complex development. This paper described the results of stream order and stream profile analysis for a distinct stream segment to the east of the main Warrego Valles system. This analysis indicates that this portion of the system was formed by the rapid drainage of a large amount of water, either from a lake or from beneath a snow pack. This flood resulted when the water breached the containing wall of a degraded crater and flowed through the previously eroded valley system. This resulted in sub-parallel drainage on the floor of the old crater, a deeply eroded cascade where the crater wall was breached, and is possibly responsible for the erosion of the deep canyon in the southern part of the main Warrego channel. That this happened well after the main Warrego system was formed illustrates the complexity, the diversity and the prolonged duration of Martian fluvial activity.

Site selection for long duration lunar bases

Joseph Leach, *Richard Arndt, *Botao Shen, *Zhong Xiao Goh, *Damian Yeung, *Noriko Hirashima, and *Zhixu Li

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Department of Geomatics, University of Melbourne Vic, Australia

There has been much renewed interest in the establishment of long-term or permanent lunar bases on the Moon. This is especially so after the recent discovery of larger than expected amounts of water on the Moon. Lunar radiation poses a huge barrier to such a project as it is the single largest health threat due to its high amount of radiation. The longer an area is in shadow, the lower its radiation environment. Given the nature of solar and cosmic radiation, a lunar exploration base should ideally be situated in shadow and adjacent to a crater wall with a thickness of at least two metres. It is known that these conditions are met near the poles but exploration also needs to occur at low lunar latitudes. Therefore this research seeks to determine those areas near the equatorial region of the Moon which are the most shadowed. These may then form suitable proposed locations of a long-term lunar base. The project used a comparison of multi-temporal telescopic imagery to select the most suitable target areas. These areas were then analysed using the topographic data returned from the lunar orbiters Clementine and SELENE, both of which had laser altimeters onboard. These data allowed detailed site modelling.

Probing Spatial Temperature Variations in Solar Corona via Type III Solar Radio Bursts

Bo Li, Iver H Cairns, and Peter A Robinson School of Physics, University of Sydney, NSW, Australia

The electron temperature Te and ion temperature Ti in the solar corona vary with time and location, due to both transient and persistent activity on the Sun. Type III solar radio bursts are produced when energetic electrons accelerated in solar flares propagate as beams along open magnetic field lines into the interplanetary medium. The effects on type III solar radio bursts of both monotonic variations and spatially localized disturbances in Te and Ti in the corona are simulated. Spatially localized disturbances are found to have stronger effects than monotonic variations. Notably, distinct signatures of Te and Ti disturbances exist in the dependence on frequency of the spectral characteristics (e.g., the maximum flux) of type III radiation observed remotely. In the presence of monotonically varying Te the frequency drift rate of type III bursts agrees quantitatively with the standard prediction, which relates the drift rate with plasma density profile and a characteristic beam speed vb. In addition, vb was found to vary with position and to scale with Te

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via vb = A Te1/2 (where A is a constant). The results indicate that

nonthermal type III bursts offer a new tool to diagnose and distinguish between spatially localized structures in Te and Ti, and to probe monotonically varying Te profiles in the corona along the paths of type III beams. Furthermore, localized temperature disturbances may be responsible for some fine structures in type III bursts, e.g., flux modulations with band or/gap structures, as in type IIIb and stria bursts. The Earliest Divergences in the Tree of Life and Constraints on

the Earliest Terrestrial Environments

Charles Lineweaver and Aditya Chopra Planetary Science Institute, Australian National University

Increasingly accurate phylogenetic trees of all terrestrial life allow us to identify the earliest divergences in the tree. These divergences are associated with the changes in the earliest terrestrial environments between ~3 and ~4 billion years ago. We will describe the most fundamental differences between the earliest diverging taxa and try to relate these differences to environmental factors. Pc2 waves observed by Cluster and Antarctic ground stations

in dayside outer magnetosphere

Y. H. Liu, B. J. Fraser, F. W. Menk Center for Space Physics, University of Newcastle, Newcastle,

Australia Plasma waves in the Pc2 (0.1-0.2 Hz) frequency band, existing between the more studied neighbouring Pc1 (0.2-5 Hz) and Pc3 (10-100 mHz) waves, have received little attention in the past. Are they similar to Pc1 electromagnetic ion cyclotron (EMIC) waves or to Pc3 field line resonances? Two Pc2 wave events were observed by the four Cluster satellites as they traversed sunward over a range from L~9 out to the magnetopause located at L~15, in the high latitude cusp region near local magnetic noon. During the events, the magnetosphere was generally magnetically quiet with no magnetic storm or compressions. The Pc2 waves were mainly left-hand polarized and their frequencies decreased with increasing radial distance towards the magnetopause. Wave energy was dominantly transported along the field line direction indicating a travelling EMIC wave rather than a resonance. Energy packets propagate in

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alternative directions, back and forth supporting the well-known bouncing wave packet model originally proposed to explain the “pearl” Pc1 waves near the plasmapause. It also indicates the waves were propagating on closed outer magnetospheric field lines. The Pc2 wave vectors show generally large wave normal angles with an outward component, again suggesting the waves have their sources within the magnetosphere. Ground observations show that the Pc2 waves were mainly located in late morning and early afternoon, conjugated well between Cluster and its geomagnetic footprints. Away from the footprints, the wave frequency band and burst pattern were significantly different again suggesting that the waves are also transmitted horizontally by the ionospheric waveguide from the footprints to other more distant sites. The results will be summarised in terms of generation by the proton cyclotron instability in the equatorial region of the outer magnetosphere leading to propagation by bouncing wave packets along closed field lines between hemispheres and subsequent propagation in the ionospheric waveguide. The energy source is considered to be plasma sheet keV protons convected from the magnetotail to the dayside outer magnetosphere.

Evidence for Gently Sloping Plasma Density Profiles in the Deep Corona

Vasili Lobzin, The University of Sydney, Australia Iver Cairns, The University of Sydney, Australia

Alexander Warmuth, Astrophysikalisches Institut Potsdam, Germany Roman Gorgutsa, Pushkov Institute of Terrestrial Magnetism,

Ionosphere and Radiowave Propagation, Russia Peter Robinson, The University of Sydney

Gottfried Mann, Astrophysikalisches Institut Potsdam, Germany Valery Fomichev, Pushkov Institute of Terrestrial Magnetism,

Ionosphere and Radiowave Propagation, Russia

Type III radio bursts are produced near the local electron plasma frequency fp and near its harmonic 2fp by fast electrons ejected from the solar active regions and moving through the corona and solar wind. These bursts have dynamic spectra with frequency rapidly falling with time, the typical duration of the coronal burst being about 1–3 seconds. We have analysed 37 well-defined coronal type III radio bursts (25–450 MHz). It is found that the temporal dependence of the central frequency of the emission can be fitted to a power-law model, f(t) ~ (t – t0)–α. The index α varies in the range 0.2 to ∞, with mean and median values of 1.2 and 0.5, respectively. A surprisingly large

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fraction of events, 84%, has α ≤ 1.2. Assuming a constant speed of the electron beam, these results provide strong evidence that in the type III source regions within about 1 solar radius above the photosphere the electron number density scales as n(r) ~ (r – r0)–β, with minimum, mean, and median β of 0.4, 2.4, and 1.0, respectively. Hence, the typical density profiles are more gently sloping than could be expected from the existing empirical coronal models. In the case of negligible plasma acceleration and conical flow, from conservation of the number of electrons it follows that the electron number density will decrease as r–2 with α = 1, like in the solar wind. Several events are found with such a wind-like dependence of burst frequency on time. Smaller power-law indices could result from the effects of non-conical geometry of the plasma flow tubes, deceleration of coronal plasma, and/or the curvature of the magnetic field lines. The effects of curvature of the magnetic field lines are shown to be too weak to explain such low power-law indices.

HiGlide Project - Rocket Deployment of UAVs

Austyn Luke, Jackson Richards Australian Youth Aerospace Forum

The Australian Youth Aerospace Association set up their Zuni Rocket Program at the end of 2009. The program aims to provide third year engineering students with financial and technical support to successfully launch a Payload. The Payloads are carried by Zuni Rockets made available through ASRI’s Small Sounding Rocket Program. The HiGlide project is the first in the program with launch planned for early October this year. The project involves the design and manufacture of a glider to be housed within the payload tube and a payload tube ejection system. Design work began in November 2009 and sponsorship was obtained from Australian Aerospace in May 2010. The operation of the capability can be sectioned into three phases; pre-launch, rocket flight and free flight. During pre-launch the glider’s wings are folded in half along the chord length and swung back along the fuselage to fit within the payload tube and maximise wing area. The horizontal stabilizers also swing forwards along the fuselage to provide sufficient flight stability. The glider is then slid backwards into the payload tube along two rails. This depresses the ejection system which is spring loaded. The Zuni Rocket’s nosecone is placed over the

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glider and attached to the Payload. The payload tube is then mounted to the Zuni motor. The ejection system consists of a remotely activated timing circuit and 2 explosive cable cutters. Shortly before Zuni launch the ejection system is armed. During rocket flight the glider remains within the payload tube until after the main parachute is deployed and the ejection system cuts the wires holding the nosecone. The glider through natural stability assumes a spiral descent and records and transmits GPS data to a handheld recover system. Using the GPS coordinates the glider is recovered.

VLF Gravity Wave Observations

Kenneth Lynn

Observations were made at night of a gravity wave train over a VLF path from Omega Australia to Adelaide on 7 September 1982. The reflection height was around 90km. Only one other observation of such a wave train was observed on this path in 1982. More recently, a similar wave train was reported over a VLF path from Hawaii to Alaska on 11 February 2000 by Bell in a report now available on the internet. Such wave trains were apparently a more common occurrence for VLF paths near the auroral electrojet in Alaska. Both observations show the clearest wave trains ever identified by radio wave reflection from the ionosphere. The Australian wave train increased in period from 3 to 14 minutes along with an associated increase in oscillation amplitude in both signal strength and phase. The Alaskan wave train showed the same characteristics with a period increasing from 5 to 17 minutes. Mn-Cr systematics in meteoritic olivine measured by SHRIMP

(Sensitive High-mass Resolution Ion Micro-Probe)

Seann McKibbin, Research School of Earth Sciences, Australian National University

The early Solar Nebula and its precursor molecular cloud once hosted radioactive isotopes with half-lives in the range 0.1-100 million years (Ma). Though these isotopes are now completely extinct, their initial abundances in meteorites can constrain the timing of formation of asteroids and planets. The extinct nuclide 53Mn (half-life of 3.7 Ma, decaying to 53Cr) is particularly useful for dating planetary rocks containing the mineral olivine which incorporates Mn but excludes Cr during crystallisation. Simultaneous measurement of Cr-isotope

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anomalies and Mn/Cr ratio in coexisting grains or grain parts allows regression of an ‘isochron’; in conjunction with a suitable meteorite anchor (dated precisely with Mn-Cr and an extant nuclide system) this can be used to calculate model ages for rocks which are unsuitable for dating with other methods. Sensitive High-mass Resolution Ion Micro-Probe (SHRIMP) is an in-situ, nearly non-destructive analytical technique for measurement of isotopic composition, and is a powerful tool for dating samples which are small or rare and hence not always amenable to more destructive methods of analysis. However, mineral standardisation is required to enable compositions to be extracted from unreduced data and avoid bias. To understand matrix effects fully, we have prepared synthetic olivine samples with compositions over the range of Mg-Fe-Ca solid-solution applicable to many natural rocks. The Mn/Cr of these samples was analysed by SHRIMP-II, SHRIMP-RG, and Laser-Ablation Inductively-Coupled-Plasma Mass-Spectrometry to allow corrections to be made to SHRIMP analyses.

Analytic modeling of SOx in Venus’ mesosphere

F. P. Mills1,2, B. J. Sandor3, R. T. Clancy3, Y. L. Yung4, and M. Allen4,5

1Research School of Physics and Engineering,Australian National

University, Canberra, ACT, Australia 2Fenner School of Environment and Society, Australian National

University, Canberra, ACT, Australia 3Space Science Institute, Boulder, CO, USA

4Geological and Planetary Sciences, California Institute of Technology, Pasadena, CA, USA

5Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA, USA

Observations of SO and SO2 in Venus’ mesosphere have found substantial abundances of SO and SO2 above 85 km altitude (Bertaux et al, 2008; Sandor et al, 2010). Submillimeter observations have also identified substantial temporal variations in mesospheric SO and SO2, significant differences for SO and SO2 in the day-and night-side mesospheres, and larger SO and SO2 mixing ratios at 85–100 km than at 70–85 km (Sandor et al, 2010). An initial attempt to model the submillimeter observations has been made by extracting approximate analytic expressions for the day-and night-side equilibrium SOx (= SO + SO2) chemistry from a global-average

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photochemical model (Mills and Allen, 2007). Given the substantial abundances of sulfuric acid aerosol detected in Venus’ mesosphere (Wilquet et al, 2009) and the substantial variability observed for mesospheric temperatures (Bertaux et al, 2007) and water vapor abundances (Gurwell et al, 2008), initial modeling has focused on the [SO2]/[SO] ratio. Good agreement is found between the calculated and observed day-side [SO2]/[SO] ratios using the concentrations of O, ClO, and OH from global-average calculations (Mills and Allen, 2007). The calculated night-side ratio, however, is two orders of magnitude larger than is observed, making the same assumptions for the concentrations of O, ClO, and OH. This suggests either the night-side chemistry is not a equilibrium or the assumed concentrations of O, ClO, and/or OH in the night-side model are not correct. The approximate analytic day-and night-side SOx models and comparisons with observations will be presented. References Bertaux et al (2007), Nature 450, 646–649. Bertaux et al (2008), AGU Fall Meeting, Abstract P22A-05. Gurwell et al (2007), Icarus 188, 288–304. Mills and Allen (2007), Planetary and Space Science 55, 1729–1740. Sandor et al (2010), Icarus, accepted. Wilquet et al (2009), Journal of Geophysical Research 114, E00B42.

A modelling assessment of nitrogen oxide chemistry in the Venus mesosphere

Manuraj Shunmuga Sundaram, RSPSE, Australian National University

Franklin Mills, RSPE and FSES, Australian National University Mark Allen, JPL, California Institute of Technology Yuk Yung, GPS, California Institute of Technology

One of the most puzzling unresolved questions for planetary atmospheres is understanding what process(es) is (are) responsible for the chemical stability of CO2 on Venus. CO2, the primary atmospheric constituent (96%), photodissociates to form CO and O at wavelengths < 200 nm. Modelling suggests that an initially pure CO2 atmosphere would evolve rapidly to include approximately 7% CO and 3.5% O2 (Nair et al, Icarus, 1994). For Venusí actual conditions, modelling suggests a majority of the atomic oxygen produced from photodissociation of CO2 combines to form O2 (Yung and DeMore, Icarus, 1982), and observations of intense nightside airglow emission (eg., Bailey et al, Icarus, 2008), require a net yield of O2 which is at least 50% (Gerard et al, GRL, 2008). However, the observed volume mixing ratio of CO is ~ 1e-5 (Connes et al, Ap J, 1968) and no

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observation has been able to determine an abundance for O2 (Trauger and Lunine, Icarus, 1983). The smallest observational upper limit on O2 is a volume mixing ratio of < 1.5e-7 (Krasnopolsky, Planetary and Space Science, 2006). Several catalytic chemistry schemes have been proposed (cf, Mills et al, AGU, 2007) to reduce modelled CO and O2 abundances but no model has achieved satisfactory agreement with the observational constraints on both CO and O2 (Mills and Allen, Planetary and Space Sciences, 2007). The recent detection of NO in the clouds (Krasnopolsky, Icarus, 2006) has revived interest in nitrogen oxide chemistry and a preliminary modelling assessment has been made (Sundaram, MPhil Thesis, 2008). The observed amount of NO produced little change in the modelled oxygen chemistry, but increasing the NO by a factor of three to five above that observed did introduce significant changes in the modelled oxygen chemistry. These initial modelling results and their potential implications will be presented.

Studies On Effect Of Solar Activities On Transequatorial Vlf Radio Wave Propagation At 19.8 Khz

Chandrakant More and Ashokkumar Sharma Physics ,Shivaji University,Kolhapur,INDIA

The Sun is an important star and it affects the earth in a number of ways. The solar activity like x-ray flares affect the D-layer of the ionosphere and hence VLF radio wave propagation. We have installed the Sudden Ionospheric Disturbance Monitoring Station with the help from Stanford Solar Center USA; have measured the VLF wave field strength for one year from 1st July 2009 to 30th June 2010. We have detected many solar x-ray flares. We have observed diurnal and seasonal variation of VLF wave field strength Detail analysis of the data has been discussed. Field strength measurement of VLF radio wave propagation at

19.8 KHz between Australia and India

Chandrakant More, Ashokkumar Sharma and Rajaram Bhonsle Physics, Shivaji University, Kolhapur,M.S. INDIA

The purpose of this experiment was to study the effects of solar activities on field strength of VLF radio waves reflected from D-region

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of Ionosphere. For this we built a square loop antenna of 1.5-meter diameter and connected it to the VLF receiver The VLF field strength monitoring system is installed at Khatav,India(15o 44′ N, 75o54′ E). The receiver was tuned for 19.8 kHz. to receive the radio waves transmitted by VLF radio station NWC Cape North Australia(21o46S,114o44′ E). The field strength of the radio wave was continuously monitored for more than one year at 5 seconds interval. The data was automatically recorded in a computer. We observed the diurnal and seasonal variation in the vlf field strength. We also observed the effects of solar flares and annular solar eclipse of January 15, 2010. We present here analysis and interpretation of the data received. Key words: vlf radio propagation, diurnal and seasonal variation, solar x-ray flares annular solar eclipse. Space Science in Italy: links between science and industry and

the economic potential of the collaboration

Oscar Moze Scientific Attaché

Embassy of Italy, Canberra Italy has a long and proud tradition in space science. Modern Italian space science was founded after the Second World War, principally by the eminent physicist Eduardo Amaldi, a co-founder of the European Space Research Organization and the aeronautical engineer Luigi Broglio, considered as the father of Italian astronautics. Italy is now a key global player in space science via the Italian Space Agency which co-ordinates all activities and investments in this sector. This talk will start with a brief history of Italian space science but the main focus will be to outline the present status of Italy’s space program, its participation in the European Space Agency and the strong links which are present between industrial entities such as the aerospace conglomerate Finmeccanica and academic institutions. As a final point some mention will be made of the important economic return which results from a substantial public and private investment in space science and research.

IPS Radio and Space Services - The Bureau of Meteorology space weather capability

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Dave Neudegg

IPS Radio and Space Services The Ionospheric Prediction Service (IPS) has existed since 1947 and been a branch of the Bureau of Meteorology since 2007. IPS is the national space weather organisation and delivers services to a range of customers whose technology is affected by variability in the solar-terrestrial physics (STP) environment, such as; HF radio communications and surveillance, satellite navigation and communication, geomagnetic surveys, pipelines and power grids. Services are delivered via real-time internet maps, email alerts and warnings, software products and consultancies on communication or navigation system design. IPS also delivers the internationally approved Regional Warning Centre (RWC) for space weather, the Australian Space Forecast Centre (ASFC). These services require advanced solar-terrestrial and space science and an understanding of the technologies affected by it. They are also underpinned by real-time and long-term space physics data, most of which for the Australasian region is collected by a ground-based sensor network IPSNET of ionospheric, geomagnetic and solar instruments, whilst foreign spacecraft supply the global picture. IPSNET forms a core component of the proposed Spaceship Australis project in the Decadal Space Science Plan and the STP research in the plan will enhance the modelling and prediction of space weather effects.

Embedded Data Acquisition System for Hypersonic Heat Flux Measurements

Sean O'Byrne and Varun Prakash

School of Engineering and IT, University of New South Wales, Australian Defence Force Academy

The paper presents the development of an embedded data acquisition system that can be used for making surface heat flux measurements during the simulation of a hypersonic flow in a short-duration impulse facility. Traditionally, models are held stationary using a sting or wire suspension method, with the electrical signals from sensor measurements passing through the wire or sting to a data acquisition system located outside the flow facility. While this technique works well for forebody heat flux measurements, measurements in some portions of the flow field, such as the wake, are disturbed by the

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presence of these suspension mechanisms. Wires will form small, high-temperature stagnation regions, while even a small rear sting mount will completely alter the velocity distribution in the wake, by imposing a zero-velocity boundary condition at the surface of the sting. At UNSW@ADFA, we have developed a free-flight deployment system that drops the model into the center of the facility’s nozzle during the 1 millisecond of the facility’s steady flow time. Because the model is no longer suspended or held in place, the signal can no longer be carried with wires. In this presentation we discuss the development of a data acquisition system, based upon the ADuC7020 microcontroller, that is embedded within a sphere-cylinder aerodynamic model. The model has an outer diameter of 40 mm and a cylindrical length of 80 mm. The data acquisition system is triggered by an accelerometer and takes 8 ms worth of data from a single platinum thin-film gauge, with a sampling rate in excess of 100 000 samples per second. The presentation will discuss the design of the system, and will compare preliminary heat flux measurements to computations. We will also present high-speed visualisations of the flow around the model during the flow using resonantly enhanced shearing interferometry.

Physical Insight into Nozzle Flow Behaviour of Axisymmetric Scramjets for Access-to-Space via Design Optimisation

Hideaki Ogawa and Russell Boyce

Centre for Hypersonics, The University of Queensland Hypersonic air-breathing propulsion offers great potential for reliable, reusable and economical access-to-space. Scramjet (supersonic combustion ramjet) propulsion, in particular, is a promising technology that can enable efficient and flexible transport systems. The SCRAMSPACE program is now underway as an international collaboration led by The University of Queensland, where innovative internal-compression axisymmetric scramjets with inlet fuel injection and radical-farming shock-induced combustion are being investigated in both ground and flight tests. A scramjet engine typically consists of an inlet, combustor and nozzle, where flow compression, combustion and expansion occur in a sequential manner. Scramjet operation inherently represents substantially complex flowfields which involve various aerodynamic

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and aerothermal phenomena including shock wave / boundary layer interaction, boundary layer separation, and chemical reactions. A high degree of flow coupling consequently necessitates particular care in scramjet design, where every component plays a crucial role in determining the overall engine performance in conjunction with the other portions. The aerodynamic design of the expansion nozzle, in particular, is of major importance for the design of high-performance scramjets, exerting a direct impact on the engine efficiency. The detailed flow physics in the axisymmetric scramjet nozzle, however, is yet to be understood, particularly in the presence of non-uniform inflow, a characteristic of scramjets operating on radical-farming shock-induced combustion. This paper presents the physical insight into the scramjet nozzle flowfields which has been gained as a result of design optimisation by means of a state-of-the-art design methodology coupling a high-fidelity CFD solver and an advanced optimisation capability using surrogate-assisted evolutionary algorithms. The rear section of the axisymmetric scramjet comprising the inner nozzle and external contour is to be optimised, in order to take into account the interactive effects of the inner and outer flows, represented by 10 design parameters as the decision variables for a single objective, i.e. the thrust force acting on the surface. Considered here are flow conditions in a Mach 8 flight at an altitude of 30km in the presence / absence of fuel (H2) supply, which is achieved by imposing inflow profiles at the nozzle entrance obtained from separate CFD computations with / without inlet fuel injection (finite-rate chemical reactions / thermochemical equilibrium state are assumed in the respective case). The influence of non-uniformity of the combustor exit flow on the nozzle flowfield is investigated by comparison with the stream-thrust-average uniform inflow cases. The robustness of the design is assessed by cross-referencing the optimised geometries under off-design conditions and examining their performance in freestream at different altitudes on a constant dynamic pressure trajectory for access-to-space.

Simulations of the effect of electrode geometry on the performance of an electric ion rocket

Rhys Wolfendon, John Olsen and John Page

School of Mechanical and Manufacturing Engineering, The University of New South Wales

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As mankind continues its advance into outer space, the search is on for cheaper and more efficient ways to conduct interplanetary flight. Spacecraft propulsion has been identified as a critical area of technology for these missions, as the vast majority of the weight of a spacecraft powered by chemical rockets is its fuel. While chemical rockets have served faithfully for the last 70 years, and will continue to serve as launch vehicle engines into the foreseeable future, they are a poor solution for interplanetary flight as their low efficiency (specific impulse) requires them to carry large amounts of fuel. This necessitates the development of a new form of propulsion, one that is not dependent on chemical interactions, and thus will be able to operate at a much higher specific impulse. The search for a practical solution led to the study of electric rocket propulsion, and ion propulsion in particular. Ion propulsion has a high specific impulse and low propellant consumption, making it a strong candidate for interplanetary travel and has been an area of active research since the 1960s. Ion propulsion has already been proven to have real potential as a reliable long term efficient propulsion system for these applications. However, it must be said that there are trade-offs as ion propulsion involves a higher level of complexity and requires an external power source. Ion propulsion is still a maturing technology, with problems such as accelerator grid wear posing a serious problem for efficient long term operation. One solution to this is to remove the grid and use the electrode geometry to both accelerate and control the flow of the ions. This was the basis of some recent experimentation done at the University of Sydney, and at least in the laboratory, this method has proved successful. The Sydney model was a technology demonstrator, only exploring one geometry. Using computer simulation, the experiment can be recreated in a virtual environment using the modelling program COMSOL multiphysics, where further investigations can be carried out on multiple geometry types. This simulation will allow us to evolve the electrode geometry of the demonstrator to improve its efficiency. It will extend our understanding of the technology involved and form the basis of a new generation of more reliable and highly efficient ion engines.

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Lunar Numbat - Open Source Space technologies

Marco Ostini, Lunar Numbat Lunar Numbat is an open-source space technology collaboration which was formed by a group of people from across Australia and New Zealand in 2009, with the intention of developing innovative, low-cost, open-source hardware and software solutions for space technology. Lunar Numbat hopes to encourage Australian and international innovation in space science and increase accessibility for space development. Key areas of our research and development at present are focused on three main areas: rocket engine throttle control avionics, radar altimeters, and compression techniques for the transmission of high-definition video and still images from spacecraft. Lunar Numbat is collaborating with the Australian Space Research Institute (ASRI), and with White Label Space, a team competing for the Google Lunar X-Prize. ASRI are receiving from us innovative, low-cost open source solutions to meet the needs of AUSROC 2.5. In the process, we’re making a positive contribution back to Australian space research. We’re now completing the development and testing of the CAN-interfaced propellant valve throttle controllers developed for AUSROC 2.5, a powerful liquid-fuelled sounding rocket developed as part of ASRI’s AUSROC program. These throttle controllers embody a combination of open electronic hardware, open-source embedded software, and some open mechanical design. This presentation would touch on each of Lunar Numbat's focused development areas, but more closely describe our work on the throttle control avionics for AUSROC 2.5. Numerical Simulations of Hypervelocity Scramjet Combustion

Flows

David Petty, Michael Smart, Vince Wheatley, Sarah Razzaqi, Centre for Hypersonics, The University of Queensland

A numerical investigation of the internal flowfield within a hypervelocity scramjet combustion experiment (Razzaqi 2009) was performed using steady two-dimensional Reynolds-averaged Navier-

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Stokes simulations. The experiment was performed at Mach 12 equivalent flight conditions, within the access-to-space regime. Oxygen enriched scramjet combustion was tested as a method to enhance combustion and thrust at high altitudes. The aim of these simulations was to develop a more detailed understanding of the compressible turbulent mixing and combustion characteristics through the flowfield of the experiment. Simulations of the experiment were completed for three cases: fuel-off, mixing only and finite rate chemistry. The fuel-off case provided insight into the compressible and viscous effects occurring along the duct. Boundary-layer growth along the duct was found to be significant, altering wave locations, despite the high Reynolds number of the flow. The thickness of this boundary-layer was validated by high density grid simulations without an applied wall model. The mixing only case injected hydrogen into a core flow of nitrogen. This case provided an overview of the compressible turbulent mixing within the flowpath. The recirculation regions that form behind the injection strut were shown to delay the formation of a high velocity ratio mixing layer. Finite rate chemistry was applied to the final simulation of hydrogen injected into a core flow of air to model hypervelocity combustion within the experiment. Comparison between numerical and experimental results is made for all cases and the accuracy of modelling assumptions is discussed. BIBLIOGRAPHY Razzaqi, S. A. & Smart, M. K. 2009, ‘Shock Tunnel Experiments on Oxygen Enrichment in a Hydrogen Fuelled Scramjet’, 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, Bremen, Germany, Oct. 19-22, 2009, American Institute of Aeronautics and Astronautics

Planetary Science in Australia.

Robert Pidgeon Department of Applied Geology, Curtin University of Technology,

Perth, Western Australia, 6102.

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Defining planetary science is not straightforward. Planets and other bodies of the solar system are clearly within the realm of planetary science whereas the universe is the territory of astronomy. But what about planets around other stars? The formation and early evolution of the earth is a subject shared between geology and planetary science but later earth processes such as plate tectonics are firmly claimed by geology. The history of mega impacts from asteroids and comets are planetary events but have had profound effects on the geology and evolution of life on Earth. Within this complexity a small band of Australian scientists battle on, in isolation and with minimal funding, to make a significant, internationally recognized contribution to research in planetary science. In this lecture we will look at the scale of planetary science research in Australia and discuss some of the problems and advantages in undertaking research in planetary science in this country.

The Early Heavy Bombardment of the Moon at 4.34 Ga

Robert.Pidgeon, Marion Grange and Alexander Nemchin Department of Applied Geology, Curtin University of Technology,

Perth, Western Australia, 6102 The consistency of total rock U-Pb K-Ar and Rb-Sr isochron ages of sample of highland breccias at 3.8-3.9 Ga led to the proposal that the Moon experienced a series of major impacts at this time, referred to as the late heavy bombardment. However, this event is not recorded by the U-Pb systems of lunar zircons which have U-Pb ages older than 3.9Ga. On the contrary published SIMS zircon U-Pb geochronological results indicate a massive impact or impacts on the Moon at ~4.34 Ga. The strongest age peaks in zircon populations from breccia samples from Apollo 14 and 17 are at ~4338Ma for Apollo 14 and ~4341Ma for Apollo 17. The dominance of the age peak at ~ 4.34 Ga in Apollo 14 and 17 zircon populations, suggests that the impact at this time was possibly the largest event in lunar history since the crystallization of the magma ocean. SIMS U-Pb studies of complex zircon grains and zircon crystallised in impact melt provide evidence that the major 4.34 Ga lunar event involved one or more mega-impacts. We refer to this as the early heavy bombardment. The ~4.34 Ga zircon peak represents the first major generation of zircon-bearing rocks on the Moon. A major age peak at this age is not present in the >3.9Ga zircon populations from quartz rich metasediments from Western Australia.

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The Challenges in the Design and Build of the University of Adelaide CubeSat

Drew Ravalico

School of Mechanical Engineering, University of Adelaide Project AUSAT 2010 is a final year undergraduate project carried out by five students in the School of Mechanical Engineering at the University of Adelaide. The project aims to design, build, integrate and test subsystems of a small satellite based on CubeSat standards. Throughout the design and testing phases of the project several key challenges were identified. These challenges include developing a virtual satellite package, integrating solar cells and designing and testing magnetorquers. Several models were necessary to estimate the position, power generation, thermal loading and attitude control. Difficulties in constructing the models included time restrictions, unknown orbital parameters, integration of various models and lack of experience. Assumptions were initially made to simplify the orbital position model. The assumptions include using a simplified Earth model, negligible aerodynamic drag and constant radius orbit. As prior experience of orbital mechanics was limited, further development and research will allow for a higher fidelity model to be created. Following the completion of individual models a generic virtual satellite package will be constructed that incorporates the position, temperature distribution and power generation, use and availability of a satellite. GaAs solar cells were used as the means of power generation for the satellite. Budget constraints required the panels be manufactured within the university. Initial attempts in soldering GaAs cells by means of standard soldering techniques resulted in two cells being damaged beyond repair. A hot air soldering technique was then adapted to successfully solder a third test cell. Magnetorquers were identified as an appropriate method of actively controlling the attitude of the satellite. The design of the magnetorquers was challenging due to power, size and space limitations. Furthermore, testing of the magnetorquers proved quite challenging. Despite the numerous challenges present throughout the project the students are confident of a successful outcome by following appropriate design procedures.

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Optimisation of Scramjet-Assisted Access-to-Space Vehicles

Using Oxygen Enrichment

Sarah Razzaqi, Thomas Jazra and Michael Kevin Smart Centre for Hypersonics, The University of Queensland

The option of scramjet-assisted access to space is a key focus at The University of Queensland's Centre for Hypersonics. A three-stage, rocket-scramjet-rocket configuration is envisaged for fulfilment of this task, in which the flight envelope of the airbreathing second stage dictates the performance requirements of the complementary rocket stages. The payload mass fraction of the launch vehicle is strongly coupled with the performance of the airbreather. The present paper investigates oxygen enrichment as an option to extend the flight envelope of the second stage and thus increase the efficiency of the launch vehicle. Three Mach 12 REST scramjets are integrated with the airframe of a NASA winged-cone vehicle to assemble the second vehicle stage. Using multidisciplinary optimisation of this airbreather, the effect on the design and performance from supplementing the freestream oxygen flow by 10% and 20%, through the premixing of oxygen with fuel, is analysed. As suggested by a related study, the freestream dynamic pressure is held constant at q=100kPa during the ascent of the airbreather. It is shown that oxygen enrichment allows a reduction of the gross mass of the launch vehicle and provides for a higher flight altitude and velocity for deployment of the third vehicle stage. This ultimately reflects in the payload mass fraction that is increased relative to the non-enriched case, despite the additional mass of the on-board oxygen. The results emphasise the potential of oxygen enrichment to bridge the gap between current non-enriched scramjet technology and the performance requirements of scramjet engines for airbreather-assisted access to space. The full paper will quantify the gains obtained using enrichment by a comparison of the optimised launch vehicle with a non-enriched, airbreather-assisted configuration as well as existing rocket-powered launch technology.

Remote Sensing in the Bureau of Meteorology’s Composite Observing System

Anthony Rea and Susan Barrell

Observations and Engineering Branch, Bureau of Meteorology

The Bureau of Meteorology (Bureau) has responsibility for providing Australians with weather forecasts and warnings, climate and water

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information, and space weather forecasts and warnings. To carry out this function, the Bureau requires timely and robust observations of physical parameters both within Australia and globally, from the Earth’s surface to the ionosphere, over oceans and land, and in all conditions. The Bureau meets this need through operating a Composite Observing System; composite in the sense that observations are drawn from a variety of sources including manual measurements, automatic weather stations and, importantly, meteorological and Earth observation satellites. To a great extent, the Bureau’s forecasting and warning functions are underpinned by numerical weather prediction systems which run over global, regional and mesoscale domains. These systems are highly data intensive and, as the accuracy of any model is somewhat dependent on the initial state, improvements in forecast skill can often be attributed to the addition of new or more accurate data streams. In the Australian context, given the large uninhabited regions of the continent and the surrounding oceans, satellites often provide the only feasible means of obtaining the necessary data to initialise the model. The dynamic nature of weather events, such as severe convective storms or the passage of fronts, requires real-time monitoring of developments between regular 6-hourly numerical predictions. This activity, often termed ‘nowcasting’, draws in data from many sources including surface-based, radar and satellites. For nowcasting, the high temporal resolution afforded by geostationary satellites is of the greatest benefit. Nonlinear Robust Control design for Hypersonic Flight Vehicles

Obaid ur Rehman and Ian Petersen

UNSW at ADFA The nonlinear longitudinal equations of motion for AHFV's are characterized by a coupling due to the control surfaces as well as a significant coupling between engine and flight dynamics. In addition to these couplings the non-standard dynamic characteristics of AHFV's and uncertainties in the parameter values make the flight control design of these vehicles highly complex. In the presence of input coupling terms and uncertainties nonlinear control design using feedback linearization may not be possible. The reason is that the low order derivatives of the regulated outputs of the AHFV model contains an expression depending on the input and consequently this makes

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feedback linearization a highly challenging task. In this paper, we apply a methodology of using a feedback linearization base uncertainty modelling approach in order to design a nonlinear robust controller for an AHFV. In this paper we consider a more recent curve fitted model (CFM) model of an AHFV recently reported in the literature. This model contains an extra input in the form of a canard, input couplings and flexible effects. The main objectives achieved in this paper are the derivation of a control-oriented linearized uncertainty model (CLUM) based on the CFM and the design of a nonlinear robust tracking controller to track velocity and altitude step reference commands. The CLUM is developed by considering uncertain aerodynamic and inertial parameters. We assume that the uncertainties arising due to the couplings and parameters satisfy an integral quadratic constraint condition. This approach of modeling allow us to obtain a full vector relative degree system with respect to the regulated outputs of velocity and altitude, which is one of the conditions needed to be satisfied for feedback linearization. Based on the CLUM for the AHFV, a robust nonlinear tracking controller is constructed by using a minimax LQR approach. Simulation results using a curve fitted model (CFM) and varying uncertain parameters are presented to demonstrate the effectiveness of the CLUM and minimax control design method. Furthermore, a Monte-Carlo type simulation has been performed to verify the stability and performance of the proposed controller for the greater ranges of uncertainties.

Satellite Modems and Communications Technology

A/Prof Sam Reisenfeld Department of Electronic Engineering, Faculty of Science

Macquarie University With increasing interest in the utilisation of Ka band satellite communications for commercial and defence applications, techniques were developed to mitigate the effects of rain attenuation of signals on the channel. The DVB-S2 Standard incorporated adaptive coding and modulation to provide the basis for a new generation of satellite communication systems. The adaptive approaches automatically adjust the transmitted data rate to the maximum supported by the link conditions. The graceful degradation of the quality of service with diminishing link quality is a far better option than the total loss of the communication link. In the case of video streaming over the satellite link, the compression ratio may be adjusted to be compatible with the available channel data rate. The presentation includes a discussion on

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the current trends in adaptive coding and modulation for high link availabilities in Ka band satellite communication system designs.

SAR Formation Flying – a Second Round ASRP Project

Andrew Dempster and Chris Rizos School of Surveying & SIS, University of New South Wales

The successful projects in the second round of the Australian Space Research Program (ASRP) were announced in July 2010. This paper outlines the work to be done in one of those projects, “SAR Formation Flying”. The overarching aim of the project is to investigate the feasibility of flying in formation satellites that carry synthetic aperture radar (SAR) payloads, to deliver environmental monitoring and disaster response outcomes. The project is broken into eleven work packages, each led by an investigator from one of the consortium partners. The partners (and their named investigators) are UNSW (Dempster, Rizos, Linlin Ge); Curtin University of Technology (Peter Teunissen); Delft University of Technology (Sandra Verhagen); Astrium, UK (David Hall, Martin Cohen); BAE Systems, Adelaide (Ian Tuohy); and General Dynamics, NZ (Kevin Parkinson). The work packages are specifically related to the operation of SAR satellites. Two examine different formation configurations: side-by-side and vertical. One work package will develop orbit (and relative orbit) models. Two further work packages examine the system requirements of such formations if carrying SAR payloads, with extra emphasis on the attitude and orbit control (AOCS) subsystem. Another group of work packages are assigned to the satellite’s onboard satellite navigation systems: one looks at the algorithms that enable the accurate relative positioning required for formation flying, one aims to develop a satellite-based receiver, and one looks at the signal processing required to enable GPS/GNSS bistatic radar. The ground segment and Australian industry also have dedicated work packages. This project will not be formally launched until early 2011, hence this paper will just describe the plans and structure of the project.

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Australia & Future Satellite Navigation Systems – the “Lucky Country”

Chris Rizos

School of Surveying & SIS, University of New South Wales Global Navigation Satellite Systems (GNSSs) involve satellites, ground reference and control stations, and user equipment, and support many activities within modern societies that require reliable positioning, navigation and timing (PNT). The U.S. Global Positioning System (GPS) is the best known, and only currently fully operational GNSS. The present GPS positioning performance spans the range from centimetre to millimetre accuracy for professional and scientific applications, to consumer vehicle and personal navigation at the dekametre-level accuracy, though there are a variety of operational constraints to these different levels of performance. Russia also operates its own (to be fully deployed in 2010-2011) GNSS called GLONASS. Fuelling growth in applications during the next decade will be ‘next generation’ GNSSs that are currently being developed and deployed. Next generation GNSSs include the U.S.’s modernized GPS and planned GPS-III constellations, Russia’s revitalised GLONASS, Europe’s GALILEO system (to be deployed 2013-2018), and China’s planned COMPASS system (to be deployed 2015-2020 – some satellites have already been launched). Furthermore, a number of Space Based Augmentation Systems (SBASs) such as Japan’s QZSS (first satellite launch in 2010) and MSAS, India’s GAGAN, Russia’s SDCM, and a possible Australian SBAS. These SBASs, as well as Regional Navigation Satellite Systems (RNSSs) such as India’s IRNSS and China’s CAPS, will add extra satellites and signals to the multi-constellation ‘mix’. These extra satellites and signals will likely drive a new wave of innovation in user devices, value-added navigation services and new applications. The Asia-Oceania region will be able to ‘see’ more navigation signals than any other region in the world. This will give the region the opportunity for early experimentation with multi-constellation technology (user equipment as well as ground reference stations) and applications. This paper explores some of the issues of multi-constellation GNSS/SBAS/RNSS from the perspective of different user groups in Australia.

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ASRI Small Sounding Rocket Program Activities and Developments

Richard Samuel and Bernard Davison, ASRI

Recent activities and developments in ASRI’s Small Sounding Rocket Program will be presented. The presentation will offer an overview highlighting program benefits such as research and experimentation opportunities, as a medium for practical undergraduate aerospace engineering education and, as a framework for public outreach. The presentation will use as examples of these benefits, the experimental payloads launched by SSRP over the past twelve months for several Australian universities that offer aerospace engineering programs. The presentation will conclude by asking the audience to consider how SSRP’s internationally unparallel accessibility and low cost can satisfy their business requirements.

Constraints on crustal rheology from the evolution of Venus'

geological landforms

Elyse Schinella and Craig O'Neill GEMOC, ARC Key National Centre, Department of Earth and Planetary

Sciences, Macquarie University, Sydney 2109 Tectonic and volcanic terrain produced during various stages of Venus’ geological history can be observed within the highlands and low-lying plains regions. The oldest terrain unit, occurring within the highland regions is tesserae, which consists of multiple cross-cutting ridges and troughs, whilst the younger, volcano-tectonic lowland plains range from being highly fractured to smooth. Deformational mechanisms that produced these terrains are poorly constrained and a suitable rheological profile is required to understand the processes that contributed to surface deformation. Rheological profiles of Venus’ crust and lithosphere, however, are also poorly constrained. Surface temperatures of ~730K, pressures of 90 bars and an absence of water make Venus' rheology unique. This study simulates Venusian conditions to determine plausible rheological profiles of Venus’ geological landforms. Observations of the style and spacing of faults from Magellan radar maps, act as indirect analogues to the underlying crustal and lithospheric rheology, whilst observations from Magellan topography and gravity are used to infer a plausible crustal structure. These observations, compared with numerical simulations of tectonic forcing, result in plausible rheological profiles of Venus’ geological landforms. Fault style and spacing, as well as the crustal structure

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below certain geological landforms, are consistent with a cooling, thickening and strengthening of Venus’ crust and lithosphere over time. Venus’ rheological profile and landforms are also compared to the Earth’s providing constraints on the deformational mechanisms that operated on Venus.

Linear mode conversion of upper hybrid waves to radiation: Averaged energy conversion efficiencies, polarization, and

applications to Earth's magnetosphere.

Fiona Schleyer, School of Physics, University of Sydney Iver Cairns, School of Physics, University of Sydney

Eun-Hwa Kim, Princeton Plasma Physics Laboratory, Princeton University

Peter Robinson, School of Physics, University of Sydney Mode conversion is a process in which energy is transferred from one wave mode to another, this can either be through a linear process known as Linear Mode Conversion (LMC) or a nonlinear process, such as wave-wave interactions. This work presents new LMC calculations of electrostatic upper hybrid (z-mode) waves to electromagnetic ‘free space’ ordinary (o-mode) and extraordinary (x-mode) waves in density gradients, focusing on the unaveraged and averaged energy conversion efficiencies. As an application, the possibility of LMC explaining the generation of terrestrial continuum radiation is then explored. Unaveraged theoretical energy efficiencies are found to be of the order of 10^-4 to 10^-3 for the Earth's plasmapause and magnetopause. Energy efficiencies, averaged over the upper hybrid wave vectors and the orientations of the density irregularities, are found to be of the order 10^-9 to 10^-5. These values are compared to other observed and predicted efficiencies and the relevance of LMC to continuum radiation is discussed. It is also found that upper hybrid waves can convert into both the o- and x-mode at the magnetopause and possibly at the plasmapause thereby producing radiation polarized in both senses, contrary to the accepted model of linear mode conversion.

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Properties of ULF waves observed by TIGER SuperDARN radars

Leila Norouzi Sedeh, Colin Waters School of Mathematical and Physical Sciences, University of Newcastle

The detection of ULF waves at ionospheric heights reveal some features of the solar-terrestrial connection. The ionospheric perturbations are detected using the Doppler shift obtained from HF radars as a variation in the Doppler velocity. We have analysed Bruny Island SuperDARN radar data and ground magnetometer data from Macquarie Island over 2006-2009 year period. The temporal, spatial and spectral variation of ULF wave occurrence and properties have been investigated using a 3-year statistical data analysis. We find a consistent, low frequency band with frequency around 2 mHz and independent of latitude. A second population exists around 8 mHz. These resulst will be discussed in terms of present understanding of ULF generation and propagation models.

Sensitivity and Single Failure Mode Analyses of a Six Degree of Freedom Model for a Multi-Stage Launch Vehicle

Authors: Cameron Sinclair, Kylie Bedwell, Daniel Bettcher

Co-authors: Laura Brooks, Matthew Tetlow School of Mechanical Engineering, University of Adelaide

Sensitivity and failure mode analyses of a six degree of freedom trajectory model are necessary components of a Range Safety Template. In order for ASRI to be approved multi-stage sounding rocket launches at the Woomera Test Facility, a Range Safety Template is required. This paper discusses the sensitivity and failure mode analyses of a six-degree of freedom trajectory model of a two-stage launch vehicle. The sensitivity analysis varies individual parameters within design limits to determine the reaction of the system to measurement errors. The effect of single failure mode scenarios on the simulated trajectory is then considered. A Monte Carlo analysis is then used to create a plot of ground impact locations, taking both parameter sensitivities and failure scenarios into account.

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A Risk Assessment of Space Weather Effects on the Australian Power Network

Elizabeth Smith, IPS Radio and Space Services, Bureau of

Meteorology Richard Marshall, IPS Radio and Space Services, Bureau of

Meteorology Colin Waters, University of Newcastle

Murray Sciffer, University of Newcastle

It is well documented that power networks at high latitudes are vulnerable to the effects of space weather. In recent years the Australian region state power networks have been physically connected which is likely to increase their susceptibility to space weather. Currents can be generated in power lines by electric fields produced from rapid geomagnetic variations according to Faraday’s Law. These currents are known as Geomagnetically Induced Currents (GIC’s). Previously documented occurrences of increased GIC activity are investigated and categorised by the effects of GIC activity on the relevant power network. Geomagnetic field data recorded nearby to the observed increased GIC activity was analysed in terms of a GIC index to determine a threshold value, above which power networks are considered to be at a greater risk of GIC related incidents. The geomagnetic field variations in the Australian region were analysed in terms of this GIC index threshold to determine the risk of the Australian region power network to increased GIC activity. In this paper it is shown that 46 occurrences of GIC indices above the determined threshold are found in the southern states of Australia over the previous two solar cycles. This suggests that the southern regions of Australia are at risk of levels of GIC activity comparable to levels that caused line trips in previously documented cases. A connection between the solar wind and GIC indices is also presented which may lead to predictions of increased GIC activity and potentially a warning system for the power networks of Australia.

Queensland University of Technology Reduced Gravity Drop Tower Facility and Research

Ted Steinberg1, Martin Castillo2, Owen Plagens3, David Lynn3,

Matthew Hales3, Antoine Diana3 and Wayde Martens4 1Professor, Queensland University of Technology,

2 George St, Brisbane 4001, QLD Australia 2Lecturer, Queensland University of Technology

3PhD Student, Queensland University of Technology

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4Post-doctoral Research Fellow, Queensland University of Technology The Queensland University of Technology (QUT) Drop Tower provides access to a high-quality reduced gravity test environment. Drop towers allow researchers to conduct numerous and repeated short duration experiments in reduced gravity while requiring only limited preparation (as compared to other methods of accessing reduced gravity). Access to many drop tower facilities is also much less competitive and less expensive than other forms of reduced gravity facility, such as parabolic flight, sounding rockets, sub-orbital flights or the international space station. The QUT Drop Tower has been in operation for approximately two years, during which time a number of projects (by researchers and students from QUT, as well as a number of external institutions and companies) have been undertaken. The drop tower itself has also undergone an optimisation program to maximise a) the reduced gravity time available and b) quality of reduced gravity produced. Presented here are details on the drop tower facility and its operation over the past two years. Several of the projects undertaken and the subsequent results produced will be discussed. A brief summary of current and future projects is also provided.

Automatic Recognition of Complex Magnetic Regions on the Sun using GONG Magnetogram Images and Their Usefulness in

Predicting Flares

Graham Steward, IPS Radio and Space Services Vasili Lobzin, The University of Sydney

Phil Wilkinson, IPS Radio and Space Services Dave Neudegg, IPS Radio and Space Services

Global Oscillation Network Group (GONG) magnetograms can be used to automatically identify active regions associated with sunspots and flares by thresholding of line-of-sight component of the solar magnetic field. Once these regions are identified, they can be useful in predicting flare potential by locating strong-gradient polarity inversion lines (SPILs). To a trained eye, the inversion line analysis of an active region can be drawn on to estimate the flare probability. With this aim in mind, a well-known pixel shifting technique is used to automatically find the SPILs. Then a measure of curvature along the SPIL is calculated. By this means, a steepness of the gradient value is obtained and used as a proxy for the expected strength of the flare,

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while the curvature measured along the SPILs is related to the flare potential. The GONG magnetograms are produced 24 hours a day seven days a week providing an opportunity for near real-time flare warning capability. The techniques used to locate active regions are uncomplicated to implement and can also be used to identify regions of interest for an automatic analysis of H-alpha images.

Completion of the AUSROC Nano gimballing system

Steven Talevski and Lachlan Thompson School of Aerospace, Manufacturing and Mechanical Engineering,

RMIT University Technological advancements have led to the invention of rockets and missiles. In society today rockets are used to launch vehicle such as that of the space shuttle and satellites. As technology advances, electronics become smaller and compact. The Royal Melbourne Institute of Technology (RMIT) in conjunction with the Australian Space Research Institute (ASRI) is developing a launch vehicle for a nano satellite. The rocket will carry a 10 Kg nano satellite travelling along a predetermined trajectory. For that reason a system needs to be put in place to ensure pitch and yaw control of the rocket. The need for control comes in the form of a gimbal system, allowing gimballing of the engine in the required direction. The gimbal ring used has been designed and made, however the associated components and support systems are yet to be modelled and or selected, actuators, servos, the structure connecting the gimbal and actuators and the tubing between kerosene tank to the servo and servo to the actuators. Furthermore the framework that will run the servo will need to be developed, this will be completed using Simulink to develop a control loop. The end result will see a working gimballing system with the ability to gimbal the engine up to ten degrees in two degrees of freedom. Once the system is completed it will be tested using a mock up test rig, whereby a model will be used to simulate the engines mass and moment of inertia and an LVTD to measure the displacement of the piston hence the gimballing angle. Also the LVDT will be used to determine whether cross coupling is an issue and if any refinements are required.

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The Channels of Mars and the Basalt Plains of Victoria: An Investigation of Channel Formation Chronology.

Q. J. K. Tan, J. H. J. Leach.

University of Melbourne, Parkville, Vic 3010, Australia.

This paper compares stream maturity between an ancient valley network on Mars, the Warrego Valles, and streams within the western volcanic plains of Victoria using digital terrain model (DTM) data derived from stereo images taken by the High Resolution Stereo Camera (HRSC) on board the ESA Mars Express orbiter and digital elevation data from the Victorian Government respectively. Warrego Valles is chosen for this study due to its extensive dendritic valley networks and lies on the southern edge of the Tharsis bulge, where very active volcanism was present during the late Noachian to the early Hesperian period of Mars. The elevation data from Mars and Victoria are directly comparable with both datasets accurate up to 10m post processed. With the Victorian data, observation on the maturity of the stream systems was undertaken and the respective sites geologically dated using radiometric dating of the underlying basaltic plains provided by the Department of Primary Industries, Victoria. The quaternary Victorian stream systems are immature by normal terrestrial standards having been formed after flood basalts covered the prior drainage systems. The same stream analysis was then applied to the Warrego Valles, where there is limited dating control, to better understand the chronology of their formation. Current models of Martian channel formation postulate a sudden change in the environment during the Hesperian period. Preliminary results reveal streams with similar profiles are dated to 2.0 million years ago, narrowing down the time when channel formation ceased to approximately the same amount of time (2Ma) after the volcanic plains were formed south of the Tharsis bulge.

Australian Research on Space Weather

Dr Mike Terkildsen IPS Radio and Space Services

Bureau of Meteorology Through a complex chain of processes, changes in the near earth environment precipitated by solar disturbances can impact upon many of the technologies we have come to rely on. Termed Space Weather, these effects are not limited to those produced by ‘catastrophic’

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disturbances of the sun-Earth system; day to day variability of the system can also impact terrestrial and space-based technologies. As we head toward a more active phase of the solar cycle the impacts of space weather will certainly increase. However, the recent extended solar minimum was far from dormant in terms of space weather, providing a unique opportunity to study the effects of variability in the solar terrestrial system commonly masked by more active solar conditions. The aims of space weather research are to firstly improve understanding of those key elements of the solar-terrestrial system that can impact technological systems and human health; and secondly, to monitor and predict the systems-level impacts of such disturbances on technology. Significant research is being done in Australia in both of these key areas with Australian scientists contributing to research into space weather, both in a regional context and globally, through international collaborations. This paper provides a brief introduction to space weather and reviews some of the current space weather research activities being undertaken in Australia, with an emphasis on the development of space weather applications.

The SCRAMSPACE I Hypersonic Flight Experiment Feasibility Study

Sandy Tirtey, Group for Hypersonics, Mechanical and Mining

Engineering Department, University of Queensland

With the work performed by the Australian hypersonic community, including universities, industry and the Defence Science & Technology Organisation, Australia is internationally recognised as a world leader in this field of research and development. Current ground-based and flight programs conducted in Australia (for example, HyShot and HIFiRE) are addressing low to midrange technology readiness levels for scramjet-powered atmospheric flight, at Mach 8. The ultimate aim however is to reach high technology readiness levels for access to space, and this requires scramjet vehicles that can operate at much higher Mach numbers, to accelerate a vehicle to the speed required to leave the earth’s atmosphere. No scramjet designs have been flight tested at these extreme speeds before now. The gap cannot be easily closed in one leap, and a stepping-stone approach is required. The SCRAMSPACE I flight experiment aims to deliver and study an advanced free-flying scramjet flight experiment at the entry point to the Mach 8-14 access-to-space range for scramjets. An innovative

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and commercially-attractive axisymmetric scramjet concept, explored jointly by UQ and DSTO, has been selected for this mission. Furthermore, the SCRAMSPACE program is setup to enhance the aerothermodynamic tools for design and validate from flight results the validity of our ground facility and computational simulations based extrapolation-to-flight methodology. These capabilities are critical to the process of extending our scramjet technology to higher speed, and ultimately to the realisation of hybrid access-to-space launch systems. Finally, the SCRAMSPACE program also provides a technical framework, including high temperature materials with embedded sensors and novel laser-based passenger experimental payloads to the hypersonic flight test. The SCRAMSPACE I feasibility study is presented, highlighting the followed methodology, the different phases of the flight, the payload configuration including passenger experiments, the aerothermodynamic and stability aspects of the flight and finally, the preliminary trajectory and thermo-structural simulations performed in this phase A study.

Evidence for Reformation of the Uranian Bow Shock

Dion Tiu and Iver Cairns Complex Systems, University of Sydney

The cyclic reformation of shock structures is still a major unresolved issue for collisionless shock physics. We investigate the Voyager 2 spacecraft's encounter with the Uranian bow shock and present the first detailed quantitative evidence that the bow shock was reforming. This evidence is based on finding excellent agreement between comparisons of Voyager observations of the Uranian bow shock with results from a standard 1-D hybrid simulation code run with similar plasma parameters. Specifically, the large downstream magnetic compression B/B_0 ~ 16 observed, where B_0 = 0.19 nT is the upstream magnetic field, are elegantly explained by reformation. The observed values of B, the number density, velocity components, and ion and electron temperatures over an almost 2-hour period including and after the shock crossing are consistent with Voyager being very close to the reforming bow shock and with the Uranian bow shock receding planetwards with the spacecraft.

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Science Results from Australian Geodesy

Paul Tregoning

Research School of Earth Sciences, The Australian National University,

Canberra, ACT 0200

Broadly speaking, geodesy is the science of the measurement of the Earth. This encompasses the size, shape and rotation of the Earth but also its gravity field. With the advent of space geodetic missions over the past few decades and considerable improvements in accuracy, changes in these phenomena can now be detected and provide new insights into geological-, oceanic- and climate-related processes. Space geodetic techniques are essential for monitoring sea level rise, melting of polar regions, earthquake deformation patterns, detecting “silent” earthquakes, identifying regions undergoing pre-earthquake strain buildup and so on. In this presentation I will provide a brief overview of a few of the Earth-observing satellite missions that are used to detect these geophysical processes, including satellite altimetry, Global Positioning System, InSAR and the GRACE space gravity mission. I will then describe some of the scientific studies that have been undertaken by Australian researchers using these techniques for Australian-based and global studies. This includes advances in analysis procedures that have led to vastly improved accuracy of estimates, thereby allowing even smaller changes in the Earth to be detected. The results that have been derived include quantification of variations in hydrology across the Australian continent, identification of earthquake deformation in Western Australia, crustal deformation of the Australian continent, sea level rise, estimates of hydrologic deformation and glacial isostatic adjustment.

The GRACE Follow On mission

Paul Tregoning, Daniel Shaddock The Australian National University,

Canberra, ACT

Craig Smith EOS Space Systems

Canberra, ACT

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Bob Oreb CSIRO Australian Centre for Precision Optics

West Lindfield, NSW

Bruce Warrington National Measurement Institute

West Lindfield, NSW

The NASA GRACE Follow On mission is scheduled for launch in 2016. Through our Australian Space Research Program consortium of Australian and international institutions, we will produce prototype hardware for the laser ranging system to be flown on this space gravity mission, as well as analysis capability for Australia to measure polar melting rates and to monitor its continental water resources, providing insight into the impacts of climate change in our region. The main objectives of the project are to develop laser technology components to complete the spacecraft-to-spacecraft laser ranging system for the GRACE Follow-on mission, build Australia’s capacity to exploit space gravity observations in areas of national research priorities and improve international collaboration and knowledge transfer between Australia, the USA, and Germany in space-related activities. The project will provide the missing components of the laser ranging system for GRACE Follow On, providing the technical maturity needed for the laser instrument to be included in the GRACE Follow On mission. This system will improve the sensitivity by a factor of 25 over the original GRACE mission. More accurate inter-spacecraft range measurements, enabled by this new laser technology, will deliver improved spatial resolution of the resulting geophysical analysis of the gravity observations, thus permitting water fluxes to be derived on smaller scales. This will greatly enhance the ability to study hydrology in Australia's drainage basins and to estimate melting rates of polar regions, which will ultimately yield more accurate predictions of contributions to sea level rise. This presentation will discuss briefly the proposed hardware developments as well as describe some of the analysis techniques and anticipated scientific exploitation of the data from the GRACE Follow On mission. Detection of Pastures in Southern Western Australia based

on ENVISAT ASAR Dual Polarimetric Data

Xin Wang¹, Linlin Ge¹, Xiaojing Li¹, ², Michael Chang1

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1. School of Surveying and Spatial Information Systems, the University of New South, Sydney, NSW, Australia;

2. School of Civil and Environmental Engineering, the University of New South Wales, Sydney, NSW, Australia

Efficient use of feed resources in the livestock industries of Australia is a major factor determining farm profitability. Both wet and dry grass is useful for feeding livestock. Optical remote sensing imagery has been applied to estimate the biomass of pastures. However, optical satellite data cannot get detailed information of grass outside the growing season due to senesced and dry pastures. Given the unique penetration ability and physical scattering characteristics, radar remote sensing can be used to complement to the optical data. The objective of this study is to evaluate dual polarimetric ENVISAT ASAR data (C-band) in terms of their capability to detect pastures in South-western Australia. Filtering is an important step of radar image processing. The performance of various radar speckles filters for separating and describing pasture grass, especially dry grass, are examined. Supervised and unsupervised classification with different filters (Box, Gaussian and Lee filter) were performed and compared. Five results are obtained. Firstly, ENVISAT ASAR image can be used for detection of grass, and wet and dry grass presents similar intensity of radar signal. Secondly, for supervised classification, Box filter gives the highest confusion matrix accuracy, and Gaussian and Lee filter provides more detail, with Lee acting as a good descriptor of shape. Thirdly, compared with supervised classification, unsupervised classification presents more detail concerning grass; Fourthly, transmitting and receiving both horizontal polarization radar signals (HH) or transmitting horizontal and receiving vertical polarizations (HV) presents more detail about grass than VH&VV. Fifthly, when the ground has more water content (after rain), ENVISAT ASAR presents stronger response from dry grass. In conclusion, the investigation confirmed the potential of dual polarimetric ENVISAT ASAR data to detect grass in the temperate South-western Australia, and provided a solid foundation for further research concerning retrieval of biophysical parameters of grass. Using dual polarized L band SAR and optical satellite imagery for land cover classification in Southern Vietnam: Comparison

and Combination

Hai Tung Chu, Linlin Ge and Xin Wang School of Surveying and Spatial Information Systems

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The University of New South Wales Sydney NSW 2052, AUSTRALIA

Synthetic Aperture Radar (SAR) and optical images are obtained in separated regions of the magnetic spectrum. Consequently, they carry different types of information of land covers. Moreover, whereas like polarization (HH or VV) SAR images are predominated by surface backscattering properties the volume backscattering characteristics of surfaces are well represented by SAR cross polarization (HV or VH) data. Hence, joint use of like and cross polarization data could enhance performance of land cover mapping process. This paper investigates potentials of multi-temporal dual-polarized L - band ALOS /PALSAR in combination with SPOT satellite images for land cover classification in Southern Vietnam. At the first stage, the classifications are applied for each single typed datasets, the classification accuracies are then compared to assess their capabilities in mapping land cover features. At the later stage, different combined datasets such as like + cross polarized SAR data, or dual-polarized SAR + optical data are generated and used for classifications. Incorporation of textural information is also taken into consideration. The classification processes are implemented using Artificial Neural Network (ANN) and Support Vector Machine (SVM) classifiers based on their strength in handling of multisource remote sensing data. This study shows advantages of using multi-temporal dual polarized SAR data and the significant improvement of classification accuracy using combination of multi-temporal dual-polarized ALOS/PALSAR and SPOT data for land cover classification. Design Optimization of a Mars Rover Rocker-Bogie Mechanism

using Genetic Algorithms

Franziska Ullrich and Salah Sukkarieh Australian Centre for Field Robotics (ACFR) J04,

The University of Sydney, Sydney NSW 2006, Australia.

The design of a Mars Rover suspension mechanism is a complex problem. The aim is to design a system which will allow the rover to traverse over obstacles and rough terrain whilst considering many important parameters including lateral and longitudinal stability, geometric trafficability, power consumption, traction/slip control, load equalization, wheel sinkage, and the rover’s variation in pitch. Many

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locomotion systems for planetary rovers have been studied in recent years, but unfortunately in most cases have not been evaluated or optimized thoroughly. In this work we present our findings in the optimization of a particular suspension system known as the “rocker-bogie mechanism” for our Mars rover. This type of mechanism has been used on most of the rovers on Mars and has proved to be a very simple and elegant design. The paper will define the most important performance metrics for a planetary rover presented above. A Genetic Algorithm is implemented and used to optimize the geometry and kinematics of the rover’s wheel suspension system subject to the defined performance metrics. A Genetic Algorithm is chosen for optimization due to its simplicity of implementation and its fast convergence to an optimal solution within a complex and unknown search space. This work reveals significant improvement of all individual performance metrics and the overall suspension system after their optimization. It is shown that the overall fitness of the rover suspension system can be increased by an average of 28.21% after 100 iterations. All performance metrics defined are improved significantly throughout the optimization. The method can be applied to different types of rovers in order to optimize the wheel suspension mechanism’s geometry.

Australian Research in the Middle Atmosphere and Lower Ionosphere

Robert Vincent

Physics, University of Adelaide The middle atmosphere is that part of the atmosphere that extends from about 10 to 100 km, i.e. the edge of space. In terms of the neutral atmosphere it encompasses the stratosphere, mesosphere and lower thermosphere. The basic thermal structure and the formation of the lower ionosphere are controlled by absorption of EUV and UV solar radiation. However, atmospheric gravity (buoyancy), tides and planetary waves profoundly affect the basic state by redistributing energy and momentum within the region. This part of the atmosphere is difficult to probe directly, so information is obtained by remote sensing from either the ground or space. Here we briefly

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review the solar and dynamical processes that control the region, including the impact of rising greenhouse gas concentrations, and then discuss recent research in the context of both national and international programs Quantifying Crescentic Dunefield Development Utilizing Spatial

Statistics, North Polar Plains, Mars

Andrew Wheelera, Mark A. Bishopa,b

aBarbara Hardy Institute [Terrain Analogue Understanding (TAU) research]

School of Natural and Built Environments, University of South Australia, Adelaide, SA, 5000 Australia

bPlanetary Science Institute, Tucson, Arizona, 85719, USA

Recent statistical investigations of the spatial relationships between aeolian dunes within crescentic dunefields, have demonstrated insight into quantifying and understanding pattern development of these landforms in terrestrial and extraterrestrial settings. Utilizing a preliminary version of the North Polar portion of the USGS Mars Global Digital Dune Database (NP-MGD3), dunefields consisting of dunes with crescentic morphology and located marginal to the erg Olympia Undae were selected for point pattern analysis. Nearest neighbour analysis of some 45,000 dunes across 18 regions of interest (ROI) determined that the dunefields were organized into moderately dispersed patterns with the value of the nearest neighbour or R-statistic ranging between 1.22 and 1.46. It has long been established that sand availability, sand supply and wind regime are determining factors for crescentic dune formation. While variation in dune morphology and distribution of voids within the ROI’s mainly explains the range in the R-statistics, it is argued that local topography of the essentially flat lying North Polar plains is also having a subtle influence on pattern self-organization. Hence, pattern heterogeneity exists at the local scale although homogeneity predominates at the global spatial scale. Terrestrial analogue research demonstrates that similar R-statistics correlate with mature crescentic dunefields formed throughout the Quaternary cycles of global glacial and interglacial climate events. The observed patterns of the Martian North Polar plains are also argued to be signatures of mature crescentic dunefields that are related to global climate change.

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Hybrid Rocket Autonomous Fly Home Recovery System

Anderw Winstanley

SAMME, RMIT University, Victoria This thesis was part of a wider Hybrid Rocket project being undertaken by RMIT University. The hybrid rocket is a replacement for current Zuni Sounding Rockets that are launched in the Woomera desert, which spans 4000km from east to west and has a width of 200km. Typically, Sounding rockets can be retrieved by a number of methods, including GPS tracking, visually, and by mathematical predictions. However as these Sounding rockets become more advanced and fly faster, higher and further, it becomes much harder to locate and recover the rocket after its landing. Therefore the aim of this Thesis project was to design an autonomous fly home recovery system, for quick and efficient retrieval of the RMIT hybrid rocket. This recovery system was designed to autonomously fly home the rocket payload after data collection, and to ensure not only the return of the payload, but a safe and gentle landing. The resulting design chosen was a Parafoil with a reefed and un-reefed stage to resist the high opening shock. The Parafoil was chosen for its gliding properties, and was automated with a programmed UAV V2 development board, and an R-DAS telemetry system. Testing and a Launch was conducted and the results evaluated.

A Virtual Satellite Design for the University Student Satellite

Program

Xiaofeng Wu and Xueliang Bai School of Aerospace, Mechanical and Mechatronic Engineering

University of Sydney In the last 10 years, commercial-off-the-shelf (COTS) components have been widely used in satellites, which provide a low-cost solution for university satellite programs. For example, a number of student-built satellites are based on the CubeSat platform. However, at the same time such small satellites have limited capabilities to carry out practical space missions. Hence until now most missions have been focused on education or technology demonstration purposes. For complex missions alternative structures have to be considered. One approach is ‘formation-flying’, which requires expensive on-board propulsion subsystem.

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In this work, we propose a virtual structure to replace traditional ‘monolithic’ spacecraft with heterogeneous spacecraft modules. Each module would support different capabilities of the satellite subsystems including bus and payload. In a virtual satellite each subsystem could be a physically-independent module. And eventually these modules will emulate a complete larger spacecraft. There are several advantages to this approach: Firstly, it reduces the launch cost by using small spacecraft modules. Secondly, it enhances the survivability from various space environment effects like radiation. Thirdly, it provides "plug-n-play" capability. Hence, the virtual satellite can be repaired and upgraded by sending new modules to the network. At the first stage, a simple virtual satellite is proposed by separating the payload subsystem from the satellite bus, resulting two individual spacecraft modules. In this paper we will discuss issues like inter-satellite link, data communication, and wireless control that are essential for the proposed virtual satellite. We will present a novel control technology that will be efficient for the virtual structure. At the same time we will present our picosatellites design which has been scheduled to be launched to demonstrate the virtual satellite in 2011.

Path Planning for a Planetary Rover

Stefan Würgler and Salah Sukkarieh Australian Centre for Field Robotics, University of Sydney

Path planning for planetary rovers are usually performed on grid maps to reduce the computational complexity of the problem. Standard search algorithms on grid maps result in suboptimal paths and are limited to a few headings, so that the resulting paths include unnecessary sharp turns. To overcome this problem, more advanced techniques such as Field D* were proposed, which can generate paths with arbitrary headings using interpolation between neighboring cells. Field D* is currently used on NASA’s Mars Exploration Rovers (MERs). As the rover’s differential constraints are not taken into account on the global level, non-feasible paths are only omitted by a local path planner later in the process. A more recent approach using “state lattices” generates paths using a set of path segments which satisfy the vehicle’s differential constraints in the first place. However, the MERs and also current research rovers, such as Rocky 8, are capable of turning on point, for which reason the differential constraints used in the state lattice approach do not apply.

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This work explores if it is beneficial to sacrifice the rover’s omni-directional capability during path planning in order to reduce the computational complexity and achieve smoother paths. For this purpose a Field D* and a state lattice path planner are implemented for an all-wheel steering rover designed for a Martian type landscape. The resulting paths were compared regarding computational time, feasibility, smoothness, and energy consumption. The paper will then present a new approach, which applies some of the benefits of state lattice to a general D* path planner without restricting the possible motions to a defined set of path segments. The amount of connecting cells is increased, sharp turns in the path are penalized, and the given start heading and the desired goal heading of the path are also incorporated.

Wave induced particle precipitation using test-particle simulations

Hongang Yang, Brian Fraser and Murray Sciffer

Centre for Space Physics, School of Mathematical and Physical Sciences , University of Newcastle, Callaghan NSW 2308, Australia

A test-particle code has been developed to study magnetospheric particle precipitation at the ionosphere and the evolution of particle pitch angle and distribution in the Earth’s dipole magnetic field. In particular, the influence of Electromagnetic Ion Cyclotron (EMIC) waves on the particle precipitation is studied. To generate the EMIC waves, we have used two methods. One is to solve the ideal MHD equations, and the other is to trace the waves using the WHAMP multi-ion plasma dispersion code in the dipole field. We will also compare simulations with observation results.

Fast reconnection in high-Lundquist-number plasmas due to

the shear flow and plasmoid Instability

Hongang Yang1 A. Bhattacharjee2, Yi-Min Huang2, Lei Ni2,and B. Rogers3

1. Centre for Space Physics, Department of Physics, University of Newcastle, Callaghan NSW 2308, Australia 2. Department of physics, University of New Hampshire, Durham, New Hampshire 03824, USA

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3.Department of physics and astronomy, Dartmouth College, Hanover, New Hampshire 03825, USA

Thin current sheets in systems of large size that exceed a critical value of the Lundquist number are unstable to a super-Alfvénic tearing instability, also called the plasmoid instability. The scaling of the growth rate of the most rapidly growing plasmoid instability with respect to the Lundquist number is shown to follow from the classical dispersion relation for tearing modes. As a result of this instability, the system realizes a nonlinear reconnection rate that appears to be weakly dependent on the Lundquist number, and larger than the Sweet–Parker rate by nearly an order of magnitude (for the range of Lundquist numbers considered here). This regime of fast reconnection is realizable in a dynamic and highly unstable thin current sheet, without requiring the current sheet to be turbulent. Linear analytical and numerical studies of the plasmoid instabilities in the presence of shear flow in high-Lundquist-number plasmas are also presented.

From the backyard to beyond: investigating the cultural significance of amateur satellites

Hannah H. Young

Flinders University, Adelaide Space has long captured the imagination of humanity every culture, throughout space and time, has ascribed significance to the sky and its celestial bodies, proving that our fascination with the ‘beyond’ is deeply rooted within the human experience. However, despite this, and more than fifty years since the first human-made instruments entered orbit, we have been exceptionally slow to explore the connections that tie social life on Earth to the celestial realm (MacDonald, 2007:592). In the animated children’s film, “Wall-E”, a spaceship leaving Earth crashes through a field of junk orbiting the planet (Pixar Animation Studios, 2008). Although obviously a fictional scenario, it may actually be closer to the truth than we anticipate (Evershed, 2009:20). In 2008, just 6% of a catalogue of some 13 000 objects in orbit were functional space craft, the remaining 94% was debris from explosions, collisions or breakups, including satellites (Evershed, 2009:20; Gorman, 2009:356). This project seeks to investigate the cultural significance of amateur satellites and the reasons why archaeologists and cultural heritage

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managers are now interested in them as part of the archaeological record. In doing so, it is based upon the Australian amateur satellite Australis Oscar V, created by University of Melbourne students in the 1960’s and compared with the RMIT University project TOAST SAT from earlier this decade. Orbital space archaeology is an emerging field, and this project has expanded upon the identification of the human material culture associated with space exploration.

The Australian Space Research Program: Platform Technologies for Space, Atmosphere and Climate project

Kefei Zhang

The Centre for Satellite Positioning and Navigation, School of Mathematical and Geospatial Sciences,

RMIT University of Melbourne, GPO Box 2476V, Melbourne Australia

Recently, the Australian Government established the Australian Space Research Program (ASRP) Scheme and supported the “Platform Technologies for Space, Atmosphere and Climate” project. The research consortium of the project consists of RMIT University (leading), the Bureau of Meteorology, Curtin University of Technology, the University of NSW, Electro Optic Systems Space System, GPSat Systems Australia Pty Ltd and National Central University of Taiwan in conjunction with National Space Organisation Taiwan and NOAA’s World Data Centre for Meteorology. The aims of this research are to investigate advanced platform technologies for space-related research, including in-space tracking and navigation, precise satellite positioning, space weather, atmospheric modelling and climate monitoring. New algorithms and enhanced atmospheric models will be developed in the context of new generation navigation and geo-environmental satellite programs to enhance Australia’s capability in space research and meteorological applications. It is anticipated that this will lead to a significant global competitive advantage for Australian companies involved in the use of advanced space technologies for positioning, tracking and environmental monitoring. The multiple million dollars space research ASRP project in the areas of in-space tracking and navigation, precise satellite positioning, space weather, atmospheric modelling and climate monitoring will be first introduced. This includes the aims and objectives, primary research tasks and work packages of the project and anticipated

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outcomes. Key issues related to the research work and challenges confronting Australian space research and space industry will be discussed and some preliminary outcomes will be shown. Finally, our view on future possible space research related to GNSS which is a key component of the ever-expanding future earth observation systems will be given.

Comparison of HPF fusion and Wavelet fusion approaches on Image Fusion of Hyperspectral image and Multispectral image

Yuanyuan Zhang, Linlin Ge, Xiaojing Li

Geodesy and Earth Observation System, School of Surveying and Spatial Information systems, The University of New South Wales

Image fusion is desired when both high spectral and spatial resolution are required. This article focuses on the image fusion of hyperspectal data and high spatial resolution multispectral data in order to enhance the spatial resolution of hyperspectral image while maintain it spectral resolution. Two fusion approaches namely, high pass filter (HPF) fusion and wavelet fusion, are applied. CHRIS/Proba and Landsat 7 image are used in this paper since they are able to be downloaded for no charge. The method is different from other image sharpening method since same wavelength bands of two data sets together for testing the methods instead of fusing with panchromatic band. The spectral quality of fused data was assessed by comparing the basic statistics, correlation coefficient and 2D scatter plots of raw data and fused data. Mean gradient of fused image and comparison of correlation coefficient of fused image and multispectral via high pass filter are used to assess the spatial quality of the fused image. The result showed that HPF fusion approach performs better than wavelet fusion approach. Evaluation of ALOS PALSAR Applicability to Generate Bushfires

Scars Map

Yingxin Zuo, Linlin Ge Geodesy and Earth Observation System, School of Surveying and Spatial Information systems, The University of New South Wales

One of the most important disasters in Australia is bushfire that occurs frequently. Hence, continuous monitoring of bushfires that is difficult, especially in mountainous areas is a demanding task. Radar remote sensing studies demonstrated the efficiency of this remotely

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sensed data for forest inventory purposes such as bushfire mapping. This imaging system can acquire plausible information over forest areas due to penetration into vegetative areas and response to the tree water content that is influenced during bushfire event. In this study, we investigated the feasibility of different ALOS PALSAR products including coherence image, textural attributes and backscatter data which were produced using three multi-temporal HH-polarized images. Two different classification methods comprising maximum likelihood classification (MLC) and support vector machine (SVM) were used to detect the fire affected areas. The classification method performances were compared to a map generated by aerial images. The results show that SVM can produce more accurate data in compare to MLC. Also the type of SAR product that is utilised for the classification significantly affects the results of classification, especially in mountainous areas.