Mars EDL CubeSat Mars EDL CubeSat MissionMissionJekan ThangaJekan Thanga11, Jim Bell, Jim Bell

11Space and Terrestrial Robotic Exploration Space and Terrestrial Robotic Exploration LaboratoryLaboratory

School of Earth and Space Exploration School of Earth and Space Exploration (SESE)(SESE)

Arizona State UniversityArizona State University

Introduction How to utilize one of the 6 25 kg

tungsten blocks on Mars 2020 EDL to carry a 3U CubeSat

Obtain high res surface imagery (science data) covering niche not covered by current or future Mars assets

Demonstrate airfoil technology for developing future Mars aircraft.

Better characterize the Martian atmosphere

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Motivation MSL can traverse 1 km/sol.

Estimating visual coverage of 0.05 km2/sol

MRO can resolve 0.9 m object on surface.

There is a gap between the two. Need for higher pixel scale images that helps rover planning and where to go next

What is over the next hill ? What is at the bottom of the cliff ? What is beyond the next crater ?

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Mission Objectives Primary: Obtain 0.1 m/pixel resolutions

images or higher of an area 10 km x 10 km near the Mars 2020 landing zone.

Secondary: Demonstrate powered glide and characterize Martian atmosphere using experimental airfoil. Early airfoil technology demonstrator for

possible future Mars “aircraft.” Tertiary: Track and video Mars 2020 landing

sequence or high-speed impact to expose Martian terrain of interest tracked by MRO.

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System Concept

System Concept

Melt nichrome wire that swings tail into deployed config.

Concept of Operations

Impact

Glide Science

Separate

Deploy

(1) Separate. System separates with tungsten blocks. Protected by heat shield.

Initially travelling at 125 m/second

(2) Deploy. Release tail, transform into shuttle cock Achieve a 2 km separation distance from main reentry

vehicle

(3) Glide. Uses cold gas propulsion at high altitude Airfoil, shuttle cock for steering, shallow glide last 2-3

km

(4) Science. – take ground images and if possible Mars 2020 and sky crane landing(5) Impact. – Max propulsion thrust, feather into dive

Concept of Operations

Ensuring shallow controlled dive Shuttle cock design is the preferred solution Redundancy using 3-axis reaction wheel with cold-gas Parachute if needed

Ensuring steady camera view Reaction wheels Gimbaled pan-tilt unit

Dealing with unsteady flow and disturbances Determining steering limits of shuttle-cock tail Find the optimal dive angle to get camera images

Option: Impact at high velocities

Challenges and Strengths

Space flight heritage for all components except the actuated shuttle cock frame design.

Pan-tilt unit would be developed using Mars heritage components.

Power from LiSoCl2 – Mars Pathfinder heritage. 400 Whr total energy from battery

Cold gas propulsion with v = 250 m/s

Feasibility

Early separation with tungsten blocks at 8 km altitude

Flight heritage for all components except shuttle cock frame

Triple redundancy for attitude control Cold-gas propulsion Ensure shallow dive using parachute

assist.

Minimizing Risk

1) Detailed feasibility analysis Selection of airfoil Parachute sizing Control authority limits Structural analysis of frame How “shallow” a dive How many pictures and video possible ?

2) Miniature wind tunnel tests to prove shuttle cock design for Mars.

3) Representative demonstration

Required Next Steps

Proposed an innovative 3U CubeSat that would deployed during EDL with tungsten blocks

Most selected components have space flight heritage

Would take images with resolution and area range not possible with current Mars assets

Demonstrate technologies for future Mars aircraft

Triple redundant attitude control and descent

Conclusions

Thank You!

Questions ?