1 science and robotic exploration (sre) small body sample return mission candidates at esa david...

1 Science and Robotic Exploration (SRE)

Small body sample

return mission

candidates at ESA

David Agnolon, Denis Rébuffat, Jens Romstedt

10th International Planetary Probe Workshop

19th June 2013


Why?

Returning a sample is of high priority in Europe

Outstanding science case for a primitive asteroid and Phobos

MarcoPolo-R follows more than 6 years of study and technology development

Europe wants to prepare itself for MSR

Timely given the international context


Why?

Some things just can’t be done in-situ


Why?

Phobos-Grunt mission Credit: Roscosmos

Philae/Rosetta landerHayabusa 2, Credit: JAXA

Stardust, Credit: NASA

OSIRIS-REX, Credit: NASA

Hayabusa, Credit: JAXA


Why again?

Charles Bolden: “…to help lead the first human mission to an asteroid and then on to Mars.” – June 17th 2013

JJ Dordain: “..help a European astronaut secure a spot on Orion crews bound for deep space, the moon, or asteroids” – Nov. 2012

(about ESA’s Orion service module)


Background

Cosmic-Vision: MarcoPolo-R is a mission candidate for the

2022-2024 slot

~ 500 M€ cost cap

Science-driven programme

Mars robotic exploration programme: Phootprint is a mission candidate for a 2024-

2026 slot

~ 700 M€ cost cap, under discussion

Robotic exploration focus


The “must” requirements

“The sampling device shall have the capability to acquire a minimum mass of the order of a hundred grams and shall return them to Earth”

“… and a selection of cm-sized fragments, plus a large number (…) of small particles (…)”

“Sample contamination shall be as low as possible”

“It shall be possible to perform multiple sampling attempts (up to 3)”

“… Verify that a sample was collected”

“It shall be possible to characterize the

entire body at e.g. dm-scale …”

“… and up to 5 potential sampling sites

candidates at e.g. mm-scale before the

actual sampling…”

(Credit: Nakamura et al./Okayama University)

(Credit: JAXA)


MarcoPolo-R

150 millions of asteroids > 100

meters in the solar system

10,000 near-Earth objects

Why this very one target?

Scientifically outstanding

Technically very attractive

In red: 67P/Churyumov–

Gerasimenko, Rosetta’s target,

1.2 – 5.7 AU

In green: 2008 EV5, 0.88 – 1.03

AU

Side view of the solar system, Credit: NASA/JPL-Caltech

Solar system planar view


MarcoPolo-R

Asteroid data available

(shape model,

temperature, etc.)

400 meter diameter

~ µg’s

3.7 h rotation period


Soyuz launch from Kourou

4.5 year mission

6-month science (proximity) ops

Electric propulsion transfer

Landing in Woomera, Australia

1100 kg maximum dry mass

1600 kg launch mass

Key capabilities: Touch and Go sampling + passive re-entry capsule

MarcoPolo-R

Transfer to and from 2008 EV5, Credit: ESOC

Launch

Earth return

Earth fly-by

Asteroid arrival


Soyuz launch from Kourou

4.5 year mission

6-month science (proximity) ops

Electric propulsion transfer

Landing in Woomera, Australia

1100 kg maximum dry mass

1600 kg launch mass

Key capabilities: Touch and Go sampling + passive re-entry capsule

MarcoPolo-R

Astrium Ltd

Thales Alenia Space


Phootprint

Phobos data available (shape

model, temperature, etc.)

18 x 22 x 27 km

100’s µg’s

7.5 h rotation period

Tidally locked with Mars

Credit: HIRIS/NASA


Phootprint

Ariane 5 launch from

Kourou

3 year mission

9 month Phobos

characterisation

Chemical transfer

Landing in Woomera,

Australia


1200 kg dry mass

4000 kg launch mass

Key capabilities:

Landing on Phobos (up

to 3 Phobos days)

Sampling decoupled from

landing

Passive re-entry capsule

Phootprint


Mission key capabilities

1. Get to the surface 2. Get the sample 3. Get back to Earth

Credit: JAXA

See presentation tomorrow on Earth re-entry capsule

development


GNC system (descent/sampling) Top-level requirements:

Touchdown accuracy of 15 meters,

Touchdown velocities of 10 cm/s vertical (nominal) and 5 cm/s lateral (maximum),

Mostly relies on classic AOCS + small camera (classic APS sensor + FPGA), altimeter and specific GNC and image processing algorithms

Simulations fit requirements

Real-time system tests with hardware in the loop end of 2013


Navigation camera breadboard, Credit: Astrium

GNC testbed, GMV platform®, Credit: GMV


GNC system (descent/sampling) Top-level requirements:

Touchdown accuracy of 100 meters,

Touchdown velocities of 50 cm/s vertical (nominal) and 10 cm/s lateral (maximum),

Mostly relies on classic AOCS + small camera (classic APS sensor + FPGA), altimeter and specific GNC and image processing algorithms

Simulations fit requirements

Real-time system tests with hardware in the loop will build on MarcoPolo-R’s


Navigation camera breadboard, Credit: Astrium

GNC testbed, GMV platform®, Credit: GMV


Touch and go system Top-level requirements:

Keep spacecraft away from the surface,

Absorb the energy resulting from touchdown velocities,

(Transfer the sample to the capsule.)

System simulations fit requirements

Breadboarding + testing to be initiated within next months

Planetary touch and go test facility candidate, Credit: DLR

MarcoPolo-R earlier design

Touch and go/transfer system



Landing leg test, Credit: SENER


Planetary touch and go test facility candidate, Credit: DLR


Sampling system Top-level requirements:

Get > 100 g sample in 3-5 seconds,

Compatible with soil properties,

Keep it “clean”.

Ongoing parallel sampling tool development/tests:

Brush-wheel

Grab bucket

Both will be breadboarded and tested in 1-g

0-g parabolic flight testing in 2014Novespace

Brush-wheel sampler concept, Credit: AVS

Bucket sampler early breadboarding, Credit:

Selex Galileo

Bucket sampler concept, Credit: Selex

Galileo



NovespaceRobotic arm

Rotating corer, Credit: Astrium

Rotating corer tests, Credit: SENER



Sampling system

Involve the best expertise there is !!



Missions’ specifics

Financial:

Ariane 5 vs Soyuz drives the propulsion system selection

Higher budget constraint on MarcoPolo-R: Touch and go?

Technical:

Solar panel size: Touch and go required for MarcoPolo-R

Gravity differences + Mars environment: ~ touchdown accuracy/velocities

Landing/touchdown velocities: 10 cm/s vs 50 cm/s Touch and go only affordable for MarcoPolo-R

Programmatics:

Phootprint part of MREP A little more room for technology

Sampling on the surface with longer stay, e.g. robotics/sample handling

To be further studied (e.g. increased autonomy for surface ops, descent & landing)


Conclusions

Both missions deemed feasible within design and programmatic constraints

All key technologies are well on their way to reach TRL 5 by SRR or did already (i.e. heat shield material)

Focus on the sample return objectives (payload ~ 20 kg)

Opportunity for collaboration (ongoing discussions with JAXA and NASA for MarcoPolo-R)

Small body sample return high priority in Europe: Exciting science + strategic technology capabilities

Very high visibility to the public

In 2014, the fate of MarcoPolo-R and Phootprint will be known … stay tuned

25 Science and Robotic Exploration (SRE)https://www.oca.eu/MarcoPolo-R/Cartoon/MarcoPolo-R_Cartoon.html

26 Science and Robotic Exploration (SRE)https://www.oca.eu/MarcoPolo-R/Cartoon/MarcoPolo-R_Cartoon.html

1 science and robotic exploration (sre) small body sample return mission candidates at esa david...

Documents