1. SOAREX/TechEdSat-N/Atromos Team NASA/ARC-RD Atromos Exploring the Martian Surface with Nano-Sat Technology M. Murbach P. Papadopoulos D. Atkinson J. Muylaert A. Colaprete 20 November 2014

2. SOAREX/TechEdSat-N/Atromos Team NASA/ARC-RD WHY COMPANION MISSIONS…? Permits augmentation of main-line missions at small cost, compartmental ‘risk’ Large potential ROI Technical, Educational, Scientific, Public Outreach… Pursuing a NEW Paradigm: Problem with the good work on the 55M DS-2 missions… The Initial ‘companion’ mission Need to compartmentalize ‘risk’ : MarsPod (analog to PPOD) Robust system design/COM ‘Gentle’ EDL Evolvable design topology Incremental flight test approach

3. SOAREX/TechEdSat-N/Atromos Team NASA/ARC-RD Simple I/F and Probe Release Example Mars Entry Annulus Jettison from MarsPod Release Phase COM ~ hourly Entry-Landing Phase  =10kg/m2  = 10-20 q conv (max)= 20w/cm 2 Operation Concept Surface Science Phase 2W Transceiver MarsRadio Evolvable Science/Technology Strategy Tier 1: Non-targeted Tier 2: Targeted Tier 3: Targeted, long duration (2+ RHU power generators)

4. SOAREX/TechEdSat-N/Atromos Team NASA/ARC-RD Probe Deployment and Mission Sequence Probe Key Attributes: Large static margin Self-orienting ‘badminton birdie’ Low ballistic coefficient (order 10 kg/m2) Compact stowage with simple interfaces to Carrier Spacecraft (‘Mars-POD’ concept) Arc-jet test of materials (first material screening) Sub-orbital flight test (SOAREX-7 Initial Validation) Mission Sequence: Deployed 20+ days from Mars Carrier Spacecraft Mars entry commences with rapid self-orientation Low ballistic coefficient permits high altitude parachute deployment Compact airbag attenuates impact Orientation independent design Telemetry established with Mars Communication Relays Initial mW Generator Fits at the core of the Baseline Science Station Cubesat Compatible Spine (Science Station Baseline)

5. SOAREX/TechEdSat-N/Atromos Team NASA/ARC-RD Example Science Mission Proposed in SALMON Mars Southern Polar Cap Asymmetry Two regional weather systems formed by winds blowing through Hellas Basin Western hemisphere – strong low-pressure system causes CO 2 snow Eastern hemisphere – strong high-pressure system causes CO 2 ground frost Mars Global Dust Storms Ten global scale storms reported since 1877 Tend to originate on the northeast rim of Hellas Basin Can raise surface temperatures as much as 40º K Can last for months 10º temperature differential from bottom to rim causes updrafts Dust storm formation theory: o Dust particles absorb sun’s heat warming local atmosphere o Warm pockets of air attracted to colder air o Resulting winds lift more dust o Needs Validation!

6. SOAREX/TechEdSat-N/Atromos Team NASA/ARC-RD TechEdSat-N and SOAREX Flight Series Evolving technology/capability… All successful flights TechEdSat-1 TechEdSat-2 TechEdSat-3 TechEdSat-4 TechEdSat-5/6 Active Flight Development

7. SOAREX/TechEdSat-N/Atromos Team NASA/ARC-RD M-POD Prototype (Al version incorporated into the 12.077 flight) Multi-Architecture/COM experiments SOAREX-8 Payload/12.077 SOAREX-8 Payload and MPOD Development (Flight 12.077 April, 2014)

8. SOAREX/TechEdSat-N/Atromos Team NASA/ARC-RD Summary - Companion Missions could be – perhaps should be – part of all future Mars Missions. - Compartmentalization of RISK = lower inclusion costs (e.g., MarsPod, MarsRadio, ‘gentle EDL’, incrementalism…) - Evolvable Science/Technology Strategy Tier 1: Non-targeted Tier 2: Targeted Tier 3: Targeted, long duration (2+ RHU power generators) - Cost: Half to Full SALMON - Large potential ROI for the Mars programs (NASA/ESA) Lastly – Incremental development and TDRV flight test: SOAREX-7 flight test: https://www.youtube.com/watch?v=Crfm7CwsXyc