technology risk dsm analysis for indian space exploration missions - aiaa space 2013 vps
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Technology Risk DSM Analysis for Indian Space Exploration Missions - AIAA SPACE 2013 VPSTRANSCRIPT
AIAA SPACE 2013 ConferenceBy
Prasad Sundararajan
Complex Project Interface and Technology Risk Assessment utilizing DSM Methods for Indian Space Exploration Missions
Indian Space Program Earth Observation (IRS, INSAT, IRNSS) Space Science & Planetary Exploration
Design/Dependency Structure Matrix [DSM]
Chandrayaan-I Mission India’s first deep space mission Discoveries of the mission Interface DSM and Technology Risk DSM
Indian Mars Orbiter (“Mangalyaan”) Mission India’s first interplanetary mission to the Red Planet Technology Risk DSM
Astrosat-1 Mission Multi-wavelength Astronomy Satellite Technology Risk DSM
Indian Space Exploration Missions Technology Risk Assessment
A PSLV launch by ISRO
Indian Space Exploration Missions Technology Risk Assessment
Indian Space Exploration Missions Technology Risk Assessment
DSM is an N x N matrix network modeling tool
Represent the elements/ components in a complex engineering system and their interactions/ interfaces in a graphical matrix format.
Highlight the product system’s architecture, the principal design and project implementation behavior in the development of the complex product.
Design/ Dependency Structure Matrix (DSM) – A Systems Engineering Management Tool for gaining insights on architectural and Integration benefits in complex engineering product/ process.
Indian Space Exploration Missions Technology Risk Assessment
A B C D E F G H
A X
B
C X X
D X X
E X
F X X
G X X
H X X
Task A depends on information from Task E
Task C and D must be done concurrently
The Design/ Dependency Structure Matrix (DSM)
Indian Space Exploration Missions Technology Risk Assessment
Interface DSM Consists of a component interface dependency
section and a section identifying the dependencies of components on the operational phases.
The interface dependency value assigned to the DSM cell is obtained by summing values representing the physical, energy and information interactions that exist between a pair of elements.
The purpose of the rating is to identify the spacecraft component interfaces with high interdependence and to identify critical components for the operational phases.
Indian Space Exploration Missions Technology Risk Assessment
Type of Element Interaction Points
Physical Interface - a direct physical interface exists in the
defined system architecture 2
Energy Interface - a direct energy transfer exists between
components such as power, propulsion, or thermal loads 2Information interface -
a) direct transfer of information between the components
b) indirect information exchanged between the
components
2
1
Matrix Values for Strength of Component Interface Dependencies
Type of component interaction during
critical operations phase Points
Essential component - a single point or major component
failure can cause failure in the specific operational phase 4
Critical component - a single point or major component
failure can cause degraded operations during the specific
operational phase 2
Matrix Values for Strength of Operation's dependence on a Component
Indian Space Exploration Missions Technology Risk Assessment
TRF NASA Technology Readiness Level (TRL) Definition TRL1 Actual system 'flight proven' through successful mission operations 9
2 Actual system completed and "flight qualified" through test and demonstration 8
2 System prototype in a space environment 7
3 System/ subsystem model or prototype demonstrated in a relevant environment 6
4 Component validation in relevant environment 5
4 Component validation in laboratory environment 4
5 Analytical and experimental critical function and/ or characteristic proof-of-concept 3
5 Technology concept and/or application formulated 2
5 Basic principles observed and reported 1
TRF of
Component
A
XTRF of
Component
B
X
Interface
dependence
value between
A and B
=TR-DSM matrix
value for A-B
interface
Indian Space Exploration Missions Technology Risk Assessment
Technology Risk DSM The technology risk DSM is intended to provide
an overall view of the project’s technological and operational risk areas
TR-DSM can be utilized as an analytical tool throughout a project’s development life cycle for identifying and communicating high-risk areas in a single system view.
The high TRF values identify the components/ subsystems that require a thorough mitigation strategy during development.
Chandrayaan-1 MissionObjectives:
Place an unmanned spacecraft in polar
orbit around the moon
Conduct mineralogical and chemical
mapping of the entire lunar surface (95%)
Upgrade technological base for future
planetary missions
Orbit: Lunar Polar Orbit at 100 KM Circular
Launched by Indian PSLV XL.
Timeline: Oct 22, 2008 - Aug 29, 2009
Spacecraft:
Basic architecture derived from the IRS
satellite bus, Spacecraft mass 1380 kg.
Single solar panel generated 700 W power.
Onboard liquid engine with 440 N
performed orbit raising maneuvers.
Eleven Science Instruments
(ISRO - 5, NASA - 2, ESA - 3, Bulgaria - 1)Credit: NASA/ ISRO
Credit: ISRO
Credit: NASA/APL/ USGS
Magmatic Water detected
on Moon’s Surface at
Bullialdus impact crater
by M3 Instrument carried
aboard Chandrayaan-1
- NASA, August 27, 2013
Indian Space Exploration Missions Technology Risk Assessment
Indian Space Exploration Missions Technology Risk Assessment
Credit: ISRO Annual Report 2012-13
India’s First Interplanetary Mission to the Red Planet
Indian Space Exploration Missions Technology Risk Assessment
Credit: ISRO
Indian Space Exploration Missions Technology Risk Assessment
Science Objectives of
Indian Mars Orbiter Mission:Exploration of Martian Surface Features
Morphology Topography Mineralogy
Study of Martian Upper Atmosphere Detect and measure Methane with an accuracy of ppb Explore the Martian Exosphere (>= 400 km above the surface of Mars) neutral density and composition
Optical Imaging Mars Phobos and Deimos Context for Science Payloads
Indian Space Exploration Missions Technology Risk Assessment
Payload Mass
(kg)
Primary Scientific Objective
Lyman Alpha Photometer (LAP) 1.5 Escape processes of Mars upper atmosphere through
Deuterium/Hydrogen
Methane Sensor for MARS (MSM) 3.6 Detect presence of Methane
Martian Exospheric Composition
Explorer (MENCA)
4.3 Study the neutral composition of the Martian upper atmosphere
MARS Color Camera (MCC) 1.4 Optical imaging
TIR imaging spectrometer (TIS) 4.0 Map surface composition and mineralogy
Indian Mars Orbiter
Science Payloads
Indian Space Exploration Missions Technology Risk Assessment
Indian Space Exploration Missions Technology Risk Assessment
Astrosat-1 MissionObjectives:
To carry out simultaneous observations
of cosmic sources for high resolution
timing, spectral and imaging studies.
High-resolution UV imaging for
morphological studies of galactic and
extragalactic objects
Orbit: Circular near equatorial orbit of
about 650 km altitude with orbital inclination
of 8 degrees
Timeline: 2014 - 2018
Spacecraft:
Basic architecture derived from Cartosat
satellite bus, Spacecraft mass 1600 kg.
Two solar panels generating 1,250 Watts.
Pointing accuracy is < 0.05º and 0.2
arcsec/s drift.
Five Science Instruments (mass: 868 kg)
Single Solid State Recorder: 120 Gb
Credit: ISRO
Indian Space Exploration Missions Technology Risk Assessment