1 / 17

10 th International Planetary Probe Workshop 17-20 June 2013, San Jose

HIAD Earth Atmospheric Reentry Test. Flexible Thermal Protection Systems Trade Studies for HIAD Earth Atmospheric Reentry Test Vehicle. 10 th International Planetary Probe Workshop 17-20 June 2013, San Jose.

akando
Download Presentation

10 th International Planetary Probe Workshop 17-20 June 2013, San Jose

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. HIAD Earth Atmospheric Reentry Test Flexible Thermal Protection Systems Trade Studies for HIAD Earth Atmospheric Reentry Test Vehicle 10th International Planetary Probe Workshop 17-20 June 2013, San Jose 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 Joseph.A.DelCorso@nasa.gov

  2. HIAD Overview Mission Infusion Flexible TPS (F-TPS) Development and Qualification System Demonstration Sub-Orbital Flight Testing Robotic Missions IRVE-II Earth Return IRVE-3 HIAD Earth Atmospheric Re-entry Test (HEART) DoD Applications Inflatable Re-entry Vehicle Experiments Tech Development & Risk Reduction 2012 2013 F-TPS advances (combination of ground and flight testing) readies technology for mission infusion

  3. F-TPS Background F-TPS is modular in that it utilizes different materials for each function • Outer high temperature fabric • Insulation • Impermeable gas barrier 3

  4. The HEART Concept HEART8 to 10 m Diameter IRVE-33 m Diameter HEART Dramatically Increases HIAD Scale, Entry Mass and Entry Environment Capabilities 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 Objectives Demonstrate manufacturing processes of a large-scale HIAD. Demonstrate successful operation of a large-scale HIAD throughout the planned operational environments. Validate HIAD predictive tools (structural, thermal, flight dynamics).

  5. HEART Launch-to-Flight Configurations CruiseConfiguration(to and from ISS) Pressurized Cargo Module (PCM, Orbital Sciences) Flexible Thermal Protection System(LaRC) Stowed HEART HIADModule (LaRC) Enhanced Antares Fairing(Orbital Sciences) InterstageStructure(Orbital Sciences) Interstage to PCM Separation Plane(Orbital Sciences) Cygnus Service Module(Orbital Sciences) Antares to Cygnus Separation Plane(Orbital Sciences) ReentryConfiguration Inflatable Structure(LaRC) LaunchConfiguration

  6. OML Trade Study Background Baseline HEART OML is 55-deg cone with non-spherical nose Aerothermal analyses indicate peak heat rate (and resultant surface temperature) could exceed current understood limit of the baseline F-TPS outer layer, and place more demands of the insulative layer. Options: change OML (cone diameter, cone angle, nose radius, shoulder radius), switch to advanced (Gen2) F-TPS materials, or reduce entry mass

  7. HEART OML Configurations Matrix Additional length available with the Cygnus spacecraft allows spherical nose--function of vehicle diameter (D) 20 OML configurations initially considered 7-m configuration quickly eliminated due to excessive heating, flow impingement and aero stability concerns

  8. OML Trade Study Re-entry Trajectories • POST2 3 degree-of-freedom simulation • 5500 kg entry vehicle • 55 to 70 degcone half angle • 8 to 10 m diameter • Ballistic entry (0° angle of attack) • Newtonian drag coefficients • Deorbit from 421x180 km orbit • 50 km perigee target

  9. Aerothermal Analysis Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA) CFD code utilized 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. Radiativeheating 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

  10. Surface Temperature Results Approximate Temperature Limits: Nextel–1723K, SiC–2023K 10

  11. Ground Testing at Large-Core Arc TunnelThe Boeing Company • LCAT – Huels arc heater • 18” and 27” cathodes with secondary air and 12” mixing section • Heat flux range 5-150 W/cm2 • Surface pressure range 1-9 kPa • Shear range 30-270 Pa • Reacting flow • Facility Ground Testing • Test coupon samples at stagnation and shearing conditions • Test at relevant mission profile heat flux and pressure Arc 11

  12. Nominal Trajectory (Vehicle Stagnation Point)Profile Test Conditions Initial Heating 17 W/cm2 Peak Heating 50 W/cm2 20 W/cm2 30 W/cm2 40 W/cm2 Side View

  13. Baseline F-TPS Sample Performance HEART Baseline Nextel 440 BF-20 Pyrogel 2250 Pre-Test Post-Test KKL Sting Arm 2 13

  14. Option A F-TPS Sample Performance Option A SiC Post-Test Post-Test Pyrogel 2250 KKL Sting Arm 2 Sting Arm 1 14

  15. Option B F-TPS Sample Performance Post-Test Post-Test Option B SiC Saffil 96 Pyrogel 2250 Sting Arm 1 Sting Arm 2 KKL 15

  16. Ongoing F-TPS Development within HIAD Project • Advancing second generation materials Developing 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 thermophysicalcharacteristics 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 development Polyimides (GRC), OFI (Miller Inc.), APA (GRC) 16

  17. 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. 17

More Related