Small body sample return mission candidates at ESA David Agnolon, Denis Rébuffat, Jens Romstedt 10th International Planetary Probe Workshop 19th June 2013

Why? Outstanding science case for a primitive asteroid and Phobos 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

Some things just can’t be done in-situ Why? Some things just can’t be done in-situ

Why? Phobos-Grunt mission Credit: Roscosmos Stardust, Credit: NASA Hayabusa, Credit: JAXA Philae/Rosetta lander OSIRIS-REX, Credit: NASA Hayabusa 2, 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: Mars robotic exploration programme: 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” (Credit: Nakamura et al./Okayama University) (Credit: JAXA) “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…”

MarcoPolo-R Side view of the solar system, Credit: NASA/JPL-Caltech 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 Solar system planar view

MarcoPolo-R Asteroid data available (shape model, temperature, etc.) 400 meter diameter ~ µg’s 3.7 h rotation period

Transfer to and from 2008 EV5, Credit: ESOC MarcoPolo-R 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 Launch Earth fly-by Asteroid arrival Earth return Transfer to and from 2008 EV5, Credit: ESOC

MarcoPolo-R Soyuz launch from Kourou 4.5 year mission Astrium Ltd 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 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

Phootprint 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

Mission key capabilities Get to the surface Get the sample Get back to Earth See presentation tomorrow on Earth re-entry capsule development Credit: JAXA

Mission key capabilities 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 GNC testbed, GMV platform®, Credit: GMV Navigation camera breadboard, Credit: Astrium

Mission key capabilities 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 GNC testbed, GMV platform®, Credit: GMV Navigation camera breadboard, Credit: Astrium

Mission key capabilities 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 Touch and go/transfer system Planetary touch and go test facility candidate, Credit: DLR MarcoPolo-R earlier design

Mission key capabilities Landing 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 Planetary touch and go test facility candidate, Credit: DLR Landing leg test, Credit: SENER

Mission key capabilities 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 2014 Brush-wheel sampler concept, Credit: AVS Bucket sampler concept, Credit: Selex Galileo Bucket sampler early breadboarding, Credit: Selex Galileo Novespace

Mission key capabilities 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 2014 + rotating corer Rotating corer tests, Credit: SENER Rotating corer, Credit: Astrium Robotic arm Novespace

Mission key capabilities Sampling system Involve the best expertise there is !!

Missions’ specifics Financial: Technical: Programmatics: 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

https://www.oca.eu/MarcoPolo-R/Cartoon/MarcoPolo-R_Cartoon.html

Questions? https://www.oca.eu/MarcoPolo-R/Cartoon/MarcoPolo-R_Cartoon.html