Aerocapture Technology - 123SeminarsOnly

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Status of Aerocapture Technology • ISPT has made major strides in ground-based development over the past 8 years • GN&C Hardware-in-the-Loop Testbed (guidance coded in flight software) • Lighter, more robust structural and TPS concepts matured through arcjet, structural, and environmental testing and model validation, culminating in two 2-meter and larger aeroshell manufacturing demonstrations • Aerothermal and Atmospheric models greatly matured (better prediction capability) • High-fidelity statistical simulation capability applied to several destinations (same tool used for operational planetary entry missions) • Stoplight chart on next page show summary of “readiness” of each subsystem for key destinations 20
Destination Subsystem Atmosphere Goal: Capture Physics Aerodynamics Goal: Errors ! 2% GN&C Goal: Robust performance for 4-6 DOF simulations TPS Goal: Reduce SOA by 30%+, expand TPS choices Structures Goal: Reduce SOA mass by 25% Aerothermal Goal: Models match within 15% System Goal: Robust performance with ready technology Venus-GRAM (2004) based on world-wide VIRA. Heritage shape, well understood aerodynamics CA =±3%, CN =±5%, " TRIM =±2% APC algorithm captures 96% of corridor More testing needed on efficient mid-density TPS. Combined convective and radiative facility needed. High-temp systems will reduce mass by 31%. Convective models match within 20% laminar, 45% with turbulence. Radiative models agree within 50% Accomplishes 97.7% of !V to achieve 300 x 300 km orbit. Aerocapture Technology Subsystem Readiness Venus Earth Mars Titan Neptune Earth-GRAM (1974) validated by Space Shuttle Heritage shape, well understood aerodynamics CA =±3%, CN =±5%, " TRIM =±2% Small delivery errors. APC algorithm captures 97% of corridor Technology ready for ST9. LMA hot structure ready for arrivals > 10.5 km/s. High-temp systems will reduce mass by 14%-30%. Environment fairly wellknown from Apollo, Shuttle. Models match within 15% Accomplishes 97.2% of !V to achieve 300 x 130 km orbit. No known technology gaps. Mars-GRAM (1988) continuously updated with latest mission data. Heritage shape, well understood aerodynamics CA =±3%, CN =±5%, " TRIM =±2% Small delivery errors using !DOR. APC algorithm captures 99% of corridor ISPT investments have provided more materials ready for application to slow arrivals, and new ones for faster entries. High-temp systems will reduce mass by 14%- 30%. Convective models agree within 15%. Radiative: predict models will agree within 50% where radiation is a factor. Accomplishes 97.8% of !V to achieve 1400 x 165 km orbit. No known technology gaps. Titan-GRAM (2002) based on Yelle atmosp. Accepted worldwide to be updated with Cassini-Huygens data Heritage shape, well understood aerodynamics CA =±3%, CN =±5%, " TRIM =±2% Ephemeris accuracy improved by Cassini- Huygens. APC algorithm captures 98% of corridor ISPT investments have provided more materials ready for application. High-temp systems will reduce mass by 14%-30%. Convective models agree within 15%. Radiative no longer a concern. Accomplishes 95.8% of !V to achieve 1700 x 1700 km orbit. No known technology gaps. Ready for Infusion Some Investment Needed Significant Investment Needed Neptune-GRAM (2003) developed from Voyager, other observations New shape; aerodynamics to be established. CA =±8%, CN =±8%, " TRIM =±10% APC algorithm with " control captures 95% of corridor. Zoned approach for mass efficiency. Needs more investment. Complex shape, large scale. Extraction difficult. Conditions cannot be duplicated on Earth in existing facilities. More work on models needed. Accomplishes 96.9% of !V to achieve Triton observ. orbit. ENABLING 21
Page 1 and 2: Aerocapture Technology www.nasa.gov
Page 3 and 4: Atmospheric Drag Reduces Orbit Peri
Page 5 and 6: Aerocapture’s Advantages to Scien
Page 7 and 8: Titan Aerocapture Systems Study Con
Page 9 and 10: Trajectory Simulations Include Real
Page 11 and 12: ! ! ! ! ! ! ! Titan Aerocapture Tec
Page 13 and 14: Example Monte Carlo Simulation Resu
Page 15 and 16: Total Heat Load (kJ/cm 2 ) 1.6 1.4
Page 17 and 18: ISPT’s Low-Risk Aeroshell Mass Im
Page 19: Power Supply Command & Telemetry Pr
Page 23 and 24: Resource Estimates for Aerocapture
Page 25: Aerocapture Development Summary •

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