esa mars robotic exploration preparation programme...

P. Falkner, SRE-FP, ASTRA 2013

P. Falkner Solar System and Robotic Exploration Mission Section

Future Mission Preparation Office, SRE, European Space Agency

ASTRA 2013 Workshop, ESTEC, 15. May 2013

ASTRA 2013 WS

ESA Mars Robotic Exploration Preparation

Programme MREP-2

ESA UNCLASSIFIED – For Official Use P. Falkner, SRE-FP, ASTRA 2013

MREP-2

• MREP-2 is an optional programme following MREP-1. Mars Robotic Exploration Programme Slice 2:

• Prepare post-ExoMars missions and enable decisions at next C-Min (2015) • Mars Sample Return mission is again confirmed as long term objective

Post ExoMars MREP activities are focused on two categories:

1. Technology Development

• Mission preparation: Inspire, Phootprint and TBD ? • Long term: strategic and enabling technologies for European Robotic Exploration

2. Mission Studies


MREP-2 status

MREP-1 • 5 mission studies done – presented at ASTRA 2011

2 candidate missions proposed at MC-12

• Phootprint & Inspire (received positive feedback from SSEWG

and HESAC advisory groups)

Mars Sample Return confirmed as long term objective

Many Technology Activities initiated

MREP-2 • Jan-Jun 2012: Preparation of programme proposal MREP-2

• Nov 2012: MREP-2 subscribed at C-Min 2012

• Mar 2013: First MREP-2 work plan approved – now under

implementation

• Apr 2012: Initiation of PB-HME working group on future robotic

exploration missions

MREP-2 candidate missions are currently under discussion


MREP general approach

1. MSR represents a significant international investment (5+ B€ class mission) that may not be initiated before early 2020s

a. International collaboration is mandatory. Preliminary work has been achieved over 2009-2011 in the context of ESA/NASA collaboration.

2. Intermediate missions following ExoMars are being considered for leading to MSR in a stepped approach

3. ESA-led mission is contemplated for 2024 launch opportunity, with implementation decision by C/MIN 2015

4. Mars-2024 mission is open to international partnership


Phootprint: Sample Return from Phobos


Phootprint: Mission Profile

• Ariane 5 launch from Kourou

• 3-stage spacecraft

• Mass: 3900 kg

• over 200 days Phobos characterisation

• < 1 day surface operations

• Mission lifetime < 3 years


Phootprint: Science Model Payload

The Science Model Payload (~25kg) is optimized to characterise Phobos and the sampling site:

1. Wide Angle Camera (WAC) 2. Narrow Angle Camera (NAC) 3. Sampling area Context Imager (SaCI) 4. Sampling point Close-UP Imager (CLUPI) 5. Visible/Near Infrared Spectrometer (VisNIR) 6. Mid Infrared Spectrometer (mid-IR)

Payload maturity benefits from Rosetta, Beagle 2 and Venus Express and current instrument developments for Bepi-Colombo and MarcoPolo-R

Beagle 2 microscope Camera

Rosetta Lander Imaging System (ROLIS)


INSPIRE: Science objectives

Combined investigations provides unique insight in: a. Planetary formation and Interior

b. Atmospheric and climate

c. Geological Features and Evolution

d. Habitability


GTO escape Hyperbolic release of 3 landers

Direct to Earth Comms

Carrier with 3 landers

1. Soyuz Fregat launch from Kourou into GTO.

2. Carrier supports landers during transfer to Mars and releases in sequence 3 network landers before Mars arrival.

3. Carrier break up and burn up in the Martian atmosphere. 4. Each lander performs ballistic entry, descent and airbag landing.

5. Surface platform deployed on the Martian surface with Direct-to-Earth communication 6. Deployment of instrumentation, some using a robotic arm.

7. Long duration surface operations (goal >1 full Martian year).

INSPIRE: Mission Profile


INSPIRE: Science model payload

1. Matured model payload of 15 kg per lander (double of previously assumed mass)

a. Seismometer

b. Mole with Heat Flow & Physical Properties Probe

c. Meteorological Boom d. Radio-Science Package

e. Camera

2. Robotic arm is added for instrument deployment

a. Significant development heritage for instruments from NetLander, Beagle-2, ExoMars Humboldt and InSight reduces development risk

SEIS sphere and levelling mechanism

HP3 support system and MOLE


Mars Precision Lander: Mission Architecture


MPL Entry, Descent and Landing (2/2)

Dropship final descent and landing (Astrium) • Hazard avoidance based on camera system • Rover lowered , landed on its locomotion system

EXM EDM-derived option (Thales Alenia) • Landing on crushable structure • Petals enclosing rover for plume protection

act as egress ramps • Hazard avoidance based on lidar system


Sample Fetching Rover

Key drivers: • Requires small rover < 100 kg

• High performance mobility needed to reach cache and return in time for MAV launch

Mobility Performance

• 177 m/sol capability, 15 km range in < 180 Sols

• GNC : high speed rover navigation capabilities (cf. SPARTAN activity) .

Two studies (Astrium-UK and TAS-I) with similar results and no major show stoppers

TAS-I concept

Astrium-UK concept

Presentation at ASTRA 2013


MSR reference architecture

1. The Caching Rover mission (MSR-C) selects and puts the samples in a Cache waiting for retrieval

2. The Sample Retrieval and Launch mission (MSR-R) retrieves the samples and launches them into Mars orbit

3. The MSR Orbiter mission (MSR-O) rendezvouses and captures the Orbiting Sample (OS) then returns it to the Earth 4. The Returned Sample Handling element (MSR-H) performs all the ground-based operations up to samples delivery to

laboratories


MSR-O: Planetary Protection Backward Contamination

Main requirement:

The probability that a single unsterilized particle of diameter > 10 nm (200 nm)

is released into the terrestrial biosphere shall be < 10-6

Main impacts of PP on MSR-O mission design: 1. Very high reliability of safety critical functions required

2. Biocontainer with unprecedented performance of the seal 3. Specific equipment for reliable & autonomous Earth avoidance manoeuver

in case of spacecraft failure leading to a risk of collision with the Earth

4. Enhanced protection from micrometeoroid impacts

Specific unit for ultra-reliable Earth avoidance manoeuvre

Biocontainer design


MREP Automation& Robotics Technologies

MREP plan on the web: http://iue.esa.int/science-e/www/object/index.cfm?fobjectid=50041

Many A&R technology activities, like:

• Rover (GNC, power, wheel/soil interaction, innovative operations…)

• Sampling tools

• Sample canister capture and Bio-Sealing

• Autonomy

• Robotic Arm

• Mechanism at low temperature • …

http://iue.esa.int/science-e/www/object/index.cfm?fobjectid=50041




Cosmic Vision Future Missions


Cosmic Vision L1 Mission: Juice

L1: Juice Jupiter Icy Moons Explorer


Cosmic Vision M3 candidates

LOFT X-ray observatory Equatorial orbit 550 km Energy range: 2-30 keV Resolution: 200 eV Time resolution: 10 µs

EChO Characterisation

of Exoplanets

STE-QUEST Measurement of Gravitational redshift and Gen. Relativity test.

PLATO Next Generation Planet Finder

MarcoPolo-R Sample return from asteroid 2008 EV5


Questions ?

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