Jennifer Trosper NASA Hq. ESMD Frank Jordan Manager Advanced Studies Mars Program Office

1. Session 7: Human Precursor Missions Thoughts on Mars Human Precursor Discussion Jennifer Trosper NASA Hq. ESMD Frank Jordan Manager Advanced StudiesMars Program Office

2. Advent of Human Precursor Activities • In addition to the approval of the next decade science-driven robotic Mars Program, the new President/national initiative in 2004 resulted in an augmented budget to allow the Mars program to contribute to the preparation for human exploration • Human precursor activities can bridge the gap between the capabilities developed by the science missions and some capabilities/measurements needed for the beginning of the human era • Here we cover • New requirements on robotic missions as human precursors • Illustrative examples of possible robotic mission advances in: - Landing accuracy and - Heavier mass to the surface. 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

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4. Objectives for Mars Human Precursors • Perform measurements, technology demonstrations, and infrastructure emplacement in order to: • Reduce cost • Reduce risk • Enhance overall mission success of future human exploration missions 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

5. Development of Mars Human Precursor Requirements • • Based on the previously discussed objectives, ESMD tasked the Mars Program Office to assist in the definition of the required mission set. • • The task was led by Frank Jordan with sub-group leadership by Dave Beaty (Measurement sub-group chair) and Noel Hinners (Technology & Infrastructure sub-group chair). • • MEPAG members supported this task as well as additional experts from NASA centers, academia, and industry. • 90 scientists and 25 engineers participated • • Two workshops, separated by two month’s of sub-group telecons over two months • • The task was kicked-off at the late June MEPAG meeting and will complete 1/15/2005. 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

6. Guidelines for the Task • Aim for human mission to Mars in the century’s 4th decade, 2030 • First dedicated precursor opportunity -- 2011 • Consider only activities that should be performed at Mars (additional requirements for earth, space-station or Lunar based activities will be included in a later task) • Science robotic missions will continue; synergy between science mission and robotic precursors will be sought • Infrastructure associated with science missions, e.g., 2009 Telecom Orbiter, is available • Perform qualitative analysis of cost, risk, and performance effects based on expert opinion. Inadequate data on human missions to Mars exists for a quantitative analysis. • Consider requirements with major architectural impacts (i.e. system of systems) higher priority than those without. 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

7. Mars Environment Measurements Dust properties Effects on humans and mechanisms Traction and cohesion Biohazards in atmosphere, on surface, subsurface Atmosphere characterization Electrical effects Dust storms • Find and characterize accessible water Summary of FindingsHigh-Priority, Early-Action Recommendations 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

8. Technology and Infrastructure Early Phase (Launches ~ 2011, 2013, 2016) • Atmosphere/regolith ISRU demos • Instrument (pressure, temp, etc.) all atmospheric flight missions • Aerocapture (70˚ cone) demo Summary of FindingsHigh-Priority Recommendations 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

9. Mid Phase (Launches ~ 2018, 2020, 2022) • Subscale demonstration of a human-scalable landing system • Pinpoint Landing • Subscale demonstration of a human-scalable ISRU surface system • Radiation shielding properties of regolith Late Phase (Launches ~ 2024, 2026, 2028) • Detailed surface reconnaissance of a selected first human landing site • Full-scale “dress rehearsal” of the human mission key systems: – Landing – ISRU – Ascent • Infrastructure Emplacement e.g: • Telecom orbiters • Landed infrastructure systems Summary of FindingsHigh-Priority Recommendations (cont’d.) Technology and Infrastructure 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

10. Some Observations • Science Program, as it is, is a strong contributor to human exploration needs • Current Decades Program • Contribute to search and characterization of accessible water • Odyssey Neutron Spectrometer • MARSIS Radar (MEX) • SHARAD Radar (MRO) • Phoenix Ground Truth • Neutron Spectrometer (MSL) • Next Decades Program • Can host some key measurements and demonstrations • Biohazards MSR may be the only credible approach • Dust MSR, AFL • Pinpoint Landing MSL, MSR • Aerocapture ST-9, MSR 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

11. Some Observations (cont’d.) • Some Human Precursor measurement needs contribute fundamentally to expanded science knowledge • Dust • Biohazards • Water characterization • Some Human Precursor engineering demonstration needs are likely distinct from the science program • ISRU and accessible water characterization • Human-scalable Landing System • Program synergy is possible and preferable, but there needs to be some dedicated precursor missions 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

12. An Integrated Mars Science Program with MHP Activities MSL Scout AFL MSR Scout Phoenix MTO MTO 2 Mars Science Missions Environmental Measurements MET Stations ISRU Pinpoint Landing Aerocapture Human Landing System Auto Rendezvous Instrumented EDL MHP Development Program Testbed Testbed Testbed MHP Flight Testbed Missions 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

13. Results of Recent System Studies 1) How do we increase the accuracy of landing on the surface of Mars? – Goal:Increase accuracy by 2 orders of magnitude to ~ 100 m (Work by A. Wolf, L. Miller, etc. – JPL) 2) How do we increase the landed mass on the surface of Mars? – Goal:Double today’s capability to ~ 4 metric tons (Work by J. Cruz, R. Powell – LaRC) 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

14. Pinpoint Landing2011 Tech Demo Reference Concept •2011 mission envisioned as an initial “test flight” under “benign” conditions (daylight landing, moderate winds,..) • Systems study assessed technological approach for this demo mission – Optical Nav on approach • Achieve 2 km knowledge at entry ~130 km alt. – Hypersonic entry guidance • Bank-angle control with IMU • Achieve 2 km control accuracy ~ at 10 km alt. – Parachute without guidance • Vulnerable to wind drift up to 4 km ~ 5 km alt. – Optimal descent imaging • Recovers knowledge to 100 m ~ 5 km alt. – Powered descent guidance • Achieves landing to 100 m control accuracy 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

15. Feed-Forward for Pinpoint Landing 2000 2020 2010 Surface Images MGS ODY MRO New Tech Approach Camera MRO Demo 2-way s/c-to- s/c Doppler Phoenix Demo Bank-Angle Aeroguidance Phoenix MSL Descent Imaging MSL Demo Continuing use in program End-to-End Pinpoint Landing Testbed Demo MSR System Studies Technology 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

16. Increase Landed Mass • Future missions, both manned and robotic will require delivery of increased payload mass to the surface of Mars • The objective of this task is to identify high pay-off technologies that will open the way to achieving this goal with an eye towards human precursor missions • Phase 1 (2004) robotic science mission (x 2 mass increase factor) • Phase 2 (2005, 2006) human precursor (scalability to x 25) 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

17. New EDL Concepts Technologies & Costs (FY04 $’s) 2X Current Viking-Heritage Approach • Improved Thermal Protection System Development • Introduce Large Subsonic Parachute Qualification • Technology Investment: $10 - 20M Inflatable Aeroshell • Inflatable Aeroshell Development and Qualification for hypersonic phase • Introduce Large Subsonic Parachute Qualification • Technology Investment: $80 - 90M MID L/D Entry Vehicle • Mid L/D Entry Vehicle Develop- ment and Qualification • Inflatable Supersonic Decelerator (Hypercone) Development and Qualification • Introduce large Subsonic Parachute Qualification • Improved Thermal Protection System Development • Technology Investment: $160 - 180M Aerocapture and Entry from Orbit • Aerocapture Demo • Introduce large Subsonic Parachute Qualification • Mach 3 Supersonic Decelerator (Parachute, etc.) Development and Qualification • Technology Investment: $50 - 60M 17 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

18. Suggestions for Consideration Mars Landing Systems • Initiate a human-scale landing system configuration study before defining a subscale demonstration at Mars and its supporting technology development program Inflatable Aeroshells Supersonic Deceleration Methods Hypersonic Deceleration Methods? Higher Mach Parachutes Deployables Alternative Decelerators Slender Body Aeroshells Propulsion • Define the configuration for demonstration and supporting technology program • Include guidance concepts and pin-point landing Soft Landing Impact Attenuation Configuration 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3

19. Program Feed-Forward for Heavier Mass Landed on Mars System Studies Technology 2010 2000 Ballistic 1 Chute MER .4MT L/D ~ .2 1 Chute .4MT Phoenix L/D ~ .2 1 Chute Throttle Engines MSL 1.1MT MSR Orbiter ST-9 Demo Aerocapture MidL/D? N chutes? 3-4 MT L/D ~ .2 2 Chutes MSR Lander 1.4MT MidL/D? TBD number of chutes 3-4 MT Scalable to human mission Testbed 2004/Frank04/Dec04/To Cary and Firouz//Summer_04_Rqts_Stdy_3