Flexible Thermal Protection Systems Trade Studies for HIAD Earth Atmospheric Reentry Test Vehicle Joseph A. Del Corso, John A. Dec, Alireza Mazaheri, Aaron D. Olds, Nathaniel J. Mesick, Walter E. Bruce III, Stephen J. Hughes, Henry S. Wright, F. McNeil Cheatwood NASA Langley Research Center [email protected]10 th International Planetary Probe Workshop 17-20 June 2013, San Jose HIAD Earth Atmospheric Reentry Test
17
Embed
10 th International Planetary Probe Workshop 17-20 June 2013, San Jose
This document is posted to help you gain knowledge. Please leave a comment to let me know what you think about it! Share it to your friends and learn new things together.
Transcript
Flexible Thermal Protection Systems Trade Studies for HIAD Earth Atmospheric Reentry
Test Vehicle
Joseph A. Del Corso, John A. Dec, Alireza Mazaheri, Aaron D. Olds, Nathaniel J. Mesick, Walter E. Bruce III, Stephen J.
10th International Planetary Probe Workshop17-20 June 2013, San Jose
HIAD Earth Atmospheric Reentry Test
HIAD Overview
RoboticMissions
EarthReturn
DoD Applications
Tech Development & Risk Reduction
Flexible TPS (F-TPS) Development and
Qualification
Sub-Orbital Flight Testing
System Demonstration
F-TPS advances (combination of ground and flight testing) readies technology for mission infusion
Inflatable Re-entry Vehicle Experiments
HIAD Earth AtmosphericRe-entry Test
(HEART)
20132012
Mission Infusion
IRVE-II
IRVE-3
2
F-TPS is modular in that it utilizes different materials for each function
– Outer high temperature fabric– Insulation– Impermeable gas barrier
F-TPS Background
3
The HEART HIAD is a proposed secondary payload on the Orbital Sciences Cygnus spacecraft.
• Enhanced Antares launch vehicle, but paired with a Standard Pressurized Cargo Module (change to CRS contract)
• ISS utilization and mission implementation via the Cargo Resupply Services (CRS) contract require very early mission definition, interface development, and planning.
HEART Mission Goal• Develop and demonstrate a relevant-scale HIAD system in an
operational environment.
HEART Mission Objectives1. Demonstrate manufacturing processes of a large-scale
HIAD.
2. Demonstrate successful operation of a large-scale HIAD throughout the planned operational environments.
• Only ballistic entry conditions considered (no lift).• Surface assumed fully-catalytic with the temperature-dependent
emissivity. Radiative equilibrium surface temperature assumed.• Solutions obtained for both laminar and fully-turbulent (Cebeci-Smith)
flows.• Radiative heating computations obtained with 11-species, 2-
temperature non-equilibrium air models. Only laminar flow was simulated for radiative heating estimation.
• Flight indicators (laminar and fully-turbulent) were generated for the solid nose cap and the inflatable portion of each configuration, and then implemented in POST2.
• For each flight heating indicator, corresponding arc-jet heater settings were defined based on the computed flight-to-ground correlations
Run Performance Well behaved and was tested for the entire duration.
Sting Arm 1 Sting Arm 2
Post-Test Post-Test
15
Option B
Saffil 96Pyrogel 2250
KKL
SiC
Ongoing F-TPS Development within HIAD Project
– Advancing second generation materialsDeveloping advanced SiC weaving, and investigating manufacturing, and handle-ability
– FTPS investigating graphite and carbon felt insulators at LCAT• Material manufacturing processes are consistent and
repeatable• Materials have thermophysical characteristics similar to Saffil• Materials are mechanically viable for packing• Materials are similar to pyrogel in mechanical durability and
handling (carbon slightly more susceptible to shearing tearing loads) but no particulates
– Investments in third generation insulator developmentPolyimides (GRC), OFI (Miller Inc.), APA (GRC)
16
Conclusions
• Increased cone angle and nose radius offers the lowest peak heating solution for the aeroshell, however, structural stability concerns need to be addressed for cone angles greater than 60 deg.
• For HEART, the aeroshell diameter should be greater than 8 meters to minimize payload impingement, reduce forebody heat rates, and improve aero stability.
• Due to its relatively low emissivity, F-TPS configurations using the Nextel BF-20 fabric realize higher surface temperatures than experienced by SiC (which has a higher emissivity).
• F-TPS designs using Nextel BF-20 fabric may be possible for configurations with low peak heating. However, design margin may be unacceptable.
• F-TPS designs using SiC fabric are suitable for all HEART configurations considered in the study with an expectation of acceptable design margin.
• Arc-jet test results for HEART representative heating profiles verify that our selection for F-TPS materials will survive expected re-entry conditions at the design back-face temperature.