Aerocapture Technology - 123SeminarsOnly

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Neptune Orbiter Aerocapture System Concept Mass margin provides opportunity for • Third probe • Increased aeroshell size for possible reduction in aeroheating rates/loads, TPS thickness requirements, surface recession Propulsive mission is too massive for Delta IV-H Aerocapture is ENABLING Orbiter 2.88 m Length Flattened Ellipsled Aeroshell 2 Probes Orbiter Reference: “Systems Analysis for a Neptune Aerocapture Mission”, NASA TM 2006-214300, May 2006 35% Dry Margin at Orbiter and SEP Level 5m Fairing Solar arrays SEP Prop Module 14
Total Heat Load (kJ/cm 2 ) 1.6 1.4 1.2 1.0 .8 .6 .4 .2 0 Neptune Aerocapture Challenges: Aeroheating, TPS Zone 4 (includes base) Low Zone 2 2.88 m Zone 2 – Wind TPS Sizing Radiative Convective Ref Med Zone 3 High Outside of Expected Range Zone 1 ~0.74 m 16 14 12 10 8 6 4 2 0 Total Peak Heat Rate (kW/cm 2 ) • TPS developments and interfaces will require a significant effort • No facility exists for testing these heating levels, or the combined convective/radiative environment • Manufacturing and shape change due to recession is challenging • New aerodynamic shape Total Heat Load (kJ/cm 2 ) 4.0 3.5 3.0 2.5 2.0 1.5 1.0 .5 0 Zone 1 – Nose TPS Sizing Radiative Convective Low Ref Med High Outside of Expected Range 40 35 30 25 20 15 10 5 0 Total Peak Heat Rate (kW/cm2 ) 15
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: Example Monte Carlo Simulation Resu
Page 17 and 18: ISPT’s Low-Risk Aeroshell Mass Im
Page 19 and 20: Power Supply Command & Telemetry Pr
Page 21 and 22: Destination Subsystem Atmosphere Go
Page 23 and 24: Resource Estimates for Aerocapture
Page 25: Aerocapture Development Summary •

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