National Aeronautics and Space Administration HIAD Mission Infusion

National Aeronautics and Space Administration HIAD Mission Infusion: Technology Development & Potential Utilization Dr. F. Mc. Neil Cheatwood Stephen Hughes Dr. Anthony Calomino NASA Langley Research Center IPPW-12 Presentation June 16, 2015

What is a HIAD? A Hypersonic Inflatable Aerodynamic Decelerator (HIAD) is a deployable aeroshell consisting of an Inflatable Structure (IS) that maintains shape during atmospheric flight, and a Flexible Thermal Protection System (F-TPS) employed to protect the entry vehicle through hypersonic atmospheric entry. 2

Background: Why a HIAD? Entry mass at Mars (and other destinations with atmospheres) is limited by launch vehicle shroud size. u At Mars, increased capability needed for higher mass and/or higher altitude, eventual human missions. u Inflatable technologies allow larger aeroshell to be stowed inside launch shroud. u ü Inflation of Inflatable Structure (IS) occurs prior to atmospheric entry. ü Flexible Thermal Protection System (F-TPS) protects IS and payload from entry environments. u NASA La. RC has been developing Inflatable Aeroshell technology for over 10 years. 3

HIAD Technology Development Cadence u Systematic and stepwise technology advancement ü Ground Test: Project to Advance Inflatable Decelerators for Atmospheric Entry (PAI-DAE)—Softgoods technology breakthrough ü Flight Test: Inflatable Reentry Vehicle Experiment (IRVE), 2007: LV anomaly—no experiment ü Flight Test: IRVE-II, 2009—IRVE “build-to-print” re-flight; first successful HIAD flight ü Ground Test: HIAD Project improving structural and thermal system performance (Gen-1 & Gen-2)—Extensive work on entire aeroshell assembly ü Flight Test: IRVE-3, 2012—Improved (Gen-1) 3 m IS & FTPS, higher energy reentry; first controlled lift entry u Next Steps Ground Effort: Gen-3 F-TPS, advanced structures, packing, manufacturability at scale >10 m, controllability, and demonstrated staging to secondary decelerator. Prepares for large-scale flight test and readiness for Mars mission. Flight Test Possibilities: United Launch Alliance (ULA) flight test and/or booster recovery at scale and environments relevant to Mars Human EDL Pathfinder. 4

Flexible TPS Inflatable Structure HIAD Ground-Based Development To Date Manufacturing Testing Performance Modeling • Define large-scale fabrication methods • Optimize packed volume and density requirements • Establish manufacturing processes and quality control standards • Quantify aerodynamic structural response • Verify load reaction and structural integrity • Establish structural performance limits • Qualify structural materials performance capability • Establish handling and stowage requirement • Define design methods and safety margins • Validate non-linear structural modeling capability • Establish structural design procedures and standards • Define system weight, stiffness, and strength options Torus Stacking and Alignment Torus Compression/ Torsion Tests • Establish large-scale fabrication methods • Define manufacturing processes and quality control standards • Determine handling and stowage requirements • Characterize mechanical and thermal physical properties • Define mission-cycle performance capability • Establish F-TPS material performance limits Fabrication Stagnation Static Loading • Extend F-TPS materials performance capability • Qualify thermal and aeroelastic response • Define system integration metrics and requirements Dynamic Response • Validate a multi-physics thermal response model • Establish design requirements and safety margins • Verify integrated system load response Structural Contribution Multi-Physics Model

IRVE-3: A Fully Successful Flight Test Apogee 366 s, 474 km Aeroshell Release 429 s, 457 km Start Aeroshell Inflation 433 s, 455 km Check out the video at: http: //youtu. be/7 JGa. Ov. C 1 s. V 4 Coast… ACS Reorientation 587 s, 266 km (40 s duration) Eject Nose Cone 102 s, 177 km NIACS damps rates 91 s, 152 km (10 s duration) Separate RV & Nose Cone From Brant & Transition 90 s, 152 km Yo-Yo De-Spin, 80. 0 s Brant Burnout, 56. 9 s Brant Ignition, 23. 0 s Taurus Separation 21. 0 s Taurus Burnout, 18. 5 s Taurus Ignition, 15. 0 s Talos Burnout, 6. 4 s Spin Motor Ignition, 0. 9 s Leaves Rail, 0. 5 s Talos Ignition, 0 s Launch on Black Brant-XI from WFF 940 lb payload, El 84 deg, Az 155 deg Actuate CG offset system 628 s, 181 km (1 s duration) Atmospheric Interface, 25 Pa (666 s, ~86 km) RV Peak Heat Rate 14 -17 W/cm 2 680 s, 50 km, Mach 7 (peak Mach 10. 2) RV Peak Dynamic Pressure 685 s, 41 km, 20. 8 g’s Reentry Experiment Complete at Mach < 0. 7 (709 s, 27 km) CG Offset Maneuvers LOS by land radar & TM 12 -29 km altitude Vent NIACS and Inflation System Gas RV splashdown at 30 m/s 383 km downrange (1193 s) Recovery Attempt 6

THOR: The One That Got Away… 7

Potential HIAD Mission Infusion u Robotic missions to any destination with an atmosphere (including sample return to Earth) u High mass delivery to high altitudes at Mars (including humans to Mars) u Lower cost access to space through launch vehicle asset recovery (for example, ULA’s booster module) u ISS down mass (without Shuttle, the U. S. has no large-scale down mass capability) 8

Evolvable Mars Campaign – Capability & Mission Extensibility Mars EDL Pathfinder 70+ MT SLS 105+ MT SLS Staying Exploration Augmentation Module Space Station ace EDL / Lander Asteroid Redirect Vehicle Capabiliti es International Surf Advanced Propulsion Healthy 130+ MT SLS Tra Long Duration Habitat nsp ort Wo rkin g In atio Long Duration Surface Systems n Spa ce ISRU All Paths Through Mars Orbit EM-X Crewed Missions in Cis -lunar space Mars 2020 Asteroid Proving Ground Missions to Redirect Robotic Returned Asteroid & EAM for Mission Mars risk reduction ISS Deep Space & Mars Risk Reduction Missions Deep Space Mars Preparation Mars Moon First Human Mission to Long Duration Human 9

Evolvable Mars Campaign – Capability & Mission Extensibility Mars EDL Pathfinder 70+ MT SLS 105+ MT SLS Staying Exploration Augmentation Module Space Station ace EDL / Lander Asteroid Redirect Vehicle Capabiliti es International Surf Advanced Propulsion Healthy 130+ MT SLS Tra Long Duration Habitat nsp ort Wo rkin g In atio Long Duration Surface Systems n Spa ce ISRU HIAD Future Path Development Activity Ground-Based Efforts All Paths Through Mars Orbit Performance EM-X Crewed Missions in Cis -lunar space Asteroid Redirect Robotic Scalability Mars 2020 Mission ISS Deep Space & Mars Risk Reduction Controllability Missions Staging from HIAD Human Precursor Mission at Mars Proving Ground Missions to Returned Asteroid & EAM for Mars risk reduction Flight Deep Space Mars Preparation Testing Mars Moon First Human Mission to Long Duration Human 10

ULA’s Planned Utilization of a HIAD Image courtesy ULA 11

Development Path for 2024 Mars Demo, Utilizing ULA 14 15 16 17 18 19 20 21 22 23 24 25 26 Full-Scale Capability Pathfinder PDR CDR Launch EDL Architecture Study IRVE-3 HIAD Gen-1 complete “HIAD-2” (ground-based) Project Gen-2 & Gen-3 15 m-class HIAD ½-Scale Orbital Flight Test Gen-2 6 m-class IRVE-S Sounding Rocket Flight Test effort Ground Test effort Earth flight test Cascade Decelerator HIAD Full-Scale Orbital Flight Test Gen-2/3 12 m-class TBD Launch ULA Infusion 12

HIAD Similitude IRVE-3 Scale TPS ½-Scale Demo Full-Scale Centaur Recovery ULA Booster Recovery Mars 2024 EDL Pathfinder 5 -6 m 10 -12 m Si. C 3 X carbon felt Pyrogel Si. C 5 X carbon felt 3 X carbon felt Pyrogel Parafoil & Recover of Device(s) X Cascade Decelerator X Similar Con. Ops X X X 13