National Aeronautics and Space Administration Entry and ... · FAR - 30 September - 3 October 2019,...
20
1 FAR - 30 September - 3 October 2019, Monopoli, Italy [email protected] National Aeronautics and Space Administration Entry and Thermal Protection Systems Developments at NASA for Missions to Moon, Mars and Beyond Presented by Dr. Ellerby on behalf of Ethiraj Venkatapathy NASA’s Senior Technologist for Entry System Technology Colleagues that contributed to the developments highlighted in this talk: M. Barnhardt, A. Cassell, M. Cheatwood, D. Ellerby, J. Feldman, P. Gage, M. Stackpoole J. Vander Kam, P. Wercinsk and M. Wright October, 3, 2019 International Conference on Flight Vehicle, Aerothermodynamics and Re-entry Missions and Engineering https://ntrs.nasa.gov/search.jsp?R=20190031938 2020-06-17T00:49:36+00:00Z
Transcript of National Aeronautics and Space Administration Entry and ... · FAR - 30 September - 3 October 2019,...
1FAR - 30 September - 3 October 2019, Monopoli, Italy
National Aeronautics and
Space Administration
Entry and Thermal Protection Systems Developments at NASA
for Missions to Moon, Mars and BeyondPresented by Dr. Ellerby on behalf of
Ethiraj Venkatapathy NASA’s Senior Technologist for Entry System Technology
Colleagues that contributed to the developments highlighted in this talk:M. Barnhardt, A. Cassell, M. Cheatwood, D. Ellerby, J. Feldman, P. Gage,
M. Stackpoole J. Vander Kam, P. Wercinsk and M. Wright
October, 3, 2019International Conference on Flight Vehicle, Aerothermodynamics and
Re-entry Missions and Engineering
https://ntrs.nasa.gov/search.jsp?R=20190031938 2020-06-17T00:49:36+00:00Z
2FAR - 30 September - 3 October 2019, Monopoli, Italy
What is this talk about?
• NASA has a long history of innovations and contributions towards enabling both robotic in situ science and human missions
• This talk highlights some of the recent innovations in thermal protection materials and systems, and in entry technologies that are enabling current missions and laying the ground work for future scientific and human exploration missions.
3FAR - 30 September - 3 October 2019, Monopoli, Italy
Ames’ Heritage and Continuing Contributions to NASA Missions
NASP
BLUNT BODY
CONCEPT(H. Allen)
PAET
X-33
X-34 X-37
SHARP B1 & B2
APOLLO
SPACE SHUTTLE
SHUTTLE UPGRADES
MARS DS-2VIKING
PIONEER-VENUS GALILEO
MER
MAGELLAN
MSL
PHOENIX
STARDUST
MARS
PATHFINDER
1960
1970
19801990
2000
20102014
EFT-1
OSIRIS-REx
INSIGHT
Shuttle Operations
CCP
HIAD
ORION
ADEPT
MARS 2020
* H. Julian Allen and Al Eggers, “A Study of the Motion and Aerodynamic Heating of Ballistic Missiles Entering the Earth’s Atmosphere at High Supersonic Speeds,” NACA-RM-A53D28, 1953 / NACA-TR-1381, 1958.
4FAR - 30 September - 3 October 2019, Monopoli, Italy
NASA Ames Entry Systems Related Inventions
1960 1970 1980 1990 2000 2010 2020
Blunt Body Concept*
(1951)
TUFROC
PICA
SIRCAConstricted Arc Heater
3DMAT
RCG, LI-2200FRCI, AFRSIAETB, TUFI
HEEET
ADEPT
FIAT
Advanced Entry Heating Simulator
Laser-Enhanced IHF
5FAR - 30 September - 3 October 2019, Monopoli, Italy
Hypervelocity Entry is a hard Challenge!
• Atmospheric drag is the most efficient way to slow down but need protection from entry heating .
• Fail-safe and mass efficient thermal protection system design requires comprehensive understanding of the hypervelocity, reacting flow (aerothermodynamics), and selection, design, testing and verification of thermal protection materials and system as part of the integrated system.
Entry System, especially Thermal Protection, has to be fail-safe, mass efficient and robust
Credit: Tom Horwath, NASA LaRC
6FAR - 30 September - 3 October 2019, Monopoli, Italy
Remainder of the Talk –Highlighting Recent Innovations
3-D Multi-functional Ablative TPS (3-D MAT) enabling
Orion Lunar return
Adaptive Deployable Entry Placement Technology
(ADEPT)
Heatshield for Extreme Entry Environment Technology (HEEET)
Materials and Entry System Development
Modeling and Simulation of Entry Systems Arc Jet TestingHypersonic Inflatable Aerodynamic Decelerator
(HIAD)
8FAR - 30 September - 3 October 2019, Monopoli, Italy
New Materials and Systems Innovation – 3-D WeavingEnabling Human and Robotic Science Missions
Woven TPS CIF
Heatshield for Extreme Entry
Environment Technology (HEEET)
Ap
ril 2
01
1
Jan
. 20
12
Jun
e, 2
01
2
Oct
, 20
13
• Enable missions to Venus, Saturn and Ice-Giants ( ~ 3500 W/cm2, 5 atm.)
• DoD: Leveraging NASA Investment
Woven TPS GCDP 1st BAA
HEE
ET a
t TR
L 6
(0
5/1
9)
Multifunctional Ablative TPS (3D-MAT)
3 years and ~$3M
Enabling Orion with Lunar Capable Compression Pad
EM1 (2020) and Beyond
SimplexDiscovery
New Frontiers
MSR EEV (2026)(Option for Heatshield)
• Human Mars and Heavy Payload
• Small Spacecraft
• Drag Modulated Aerocapture
Adaptable Deployable Entry and Placement Technology (ADEPT)
Woven TPS CIF
Partnered with BRM
9FAR - 30 September - 3 October 2019, Monopoli, Italy
Orion EFT-1 Vehicle
Compression Pad Locations (6)
Orion compression pads are the interface between Crew Module (CM) & Service Module (SM) Required to withstand:
• Launch, ascent and in-space • structural loads
• Pyro-shock (CM/SM separation event)
• Earth re-entry (high heating, ablation)
Launch Abort
System
Crew Module
Service Module
3-D Multi-functional Ablative TPS (3-D MAT) for
Orion Compression Pad
EFT-1 carbon phenolic pads contained
inter-laminar cracks (post-flight observation)
10FAR - 30 September - 3 October 2019, Monopoli, Italy
Technical Challenges – Weaving and Resin Infusion
Quartz Yarn 3D Preform
3D Weaving
3D Composite Billet
Final Machining
ResinInfusion
• Challenge: Establishing partnership with industry (weaving and resin infusion), experimenting, testing, design assessment and demonstrating the capability for mission adoption in less than 36 months and $3M.
• 3-D MAT has been adopted for 18 different locations/use on the Orion Spacecraft, in addition to the compression pad application.
11FAR - 30 September - 3 October 2019, Monopoli, Italy
Arc Jet testing of 3-D Multifunctional Ablative TPS (3-D MAT)
12FAR - 30 September - 3 October 2019, Monopoli, Italy
Laser-Enhanced Arc Jet (IHF) Facility• Primarily designed for Orion Lunar Return heatshield certification
Shock layer radiation is a significant percentage of entry heating• Understanding the ablative TPS material/system response
Orion Block Avcoat Heatshield
• 200,000 W Laser power addition required major facility upgrades including modifications to the plenum, new nozzle (9”), large wedges and overall operational safety.
13FAR - 30 September - 3 October 2019, Monopoli, Italy
Avcoat Exploratory Results(Acknowledgement: Geoff Cushman and Antonella Alunni)
13
• Exploratory Avcoat test results imply differences between radiative, convective and combined heating
Convective (Ref:160 W/cm2) Radiative (168 W/cm2) Combined (88 C + 83 R W/cm2)
Acknowledgement: Geoff Cushman and Antonella Alunni1
14FAR - 30 September - 3 October 2019, Monopoli, Italy
NASA Invented TPS Technologies: Mission Infusion into MSR EEV
• Passive, ballistic entry
• 1.3 m diameter, 60° sphere-cone
• 63 – 85 kg depending on TPS choice
Earth Entry Vehicle
Hot Structure (Carbon-Carbon)
Cold Structure Ablative TPS
Cold Structure - Ablative TPS Options
15FAR - 30 September - 3 October 2019, Monopoli, Italy
Modeling and Simulation: Core Investment Areas
Predictive Materials ModelingAdvanced models for PICA, Avcoat and woven TPS; Micro- to engineering-scale analysis tools; Detailed
material characterization and model validation
Shock Layer Kinetics and RadiationRadiation databases and models for Earth entry and other destinations of interest; High-fidelity coupled
analysis tools
Guidance, Navigation, and ControlEntry guidance methods to enable precision landing of
large robotic and human Mars missions
AerosciencesParachute dynamics; Free-flight CFD; Magnetic
suspension wind tunnels; Experimental validation; Roughness, Advanced computational methods
16FAR - 30 September - 3 October 2019, Monopoli, Italy
Modeling and Simulation: High Fidelity 6-DOF CFD Simulation
SR-1 Flight Trajectory Simulations - Free Flight CFD
• We first validate our simulations with ground test facility and then do our “simulations as we fly” – Advances in Computational tools allow us to do this
17FAR - 30 September - 3 October 2019, Monopoli, Italy
Exo-BrakeThe Exo-Brake is essentially a tension device which retains its shape during the higher dynamic pressures close to entry interface.- Enables targeted propellent-less deorbit from
LEO
- Targeting accuracy (at entry interface) of 50km via predictor-corrector control, drag modulation, and timed release (200km demonstrated to date)
• Flight History:- Four successful deorbits from ISS (one
modulated)
- Next spacecraft (TES-7) on orbit now (scaling)
• Potential Applications:- On demand sample return, debris deorbit,
stage separation, planetary net-landers
Exo-Brake Deployed After NanoRacks Launch
Scalability for Deorbit from 250km
18FAR - 30 September - 3 October 2019, Monopoli, Italy
ADEPT: Scalable Entry System
23m: Mars Exploration
6m: Venus Lander 1m: “Nano” ADEPT
19FAR - 30 September - 3 October 2019, Monopoli, Italy
Inflatable: HIAD and LOFTID (NASA Langley Leading and NASA Ames supporting )
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 (FTPS) employed to
protect the entry vehicle through hypersonic atmospheric entry.
6m Inflated Entry System Flight Test Mar 2022
T1
T2
T3
T4
T
5
T
6
T5.
5
T
7
T8
20FAR - 30 September - 3 October 2019, Monopoli, Italy
Concluding Remarks
• NASA’s focus on science missions including Mars sample return and in-situ investigation of Ice Giants, and human missions to the Moon and Mars in the coming decades are the drivers for focused development in
– Thermal protection materials and systems
– Novel entry system technologies
– Innovations in modeling and simulation
– Improved ground and flight testing
• Some of these technologies have already been, or are close to, mission infusion, while others are making great progress.
