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Preliminary design of the thermal protection system for solar probeA preliminary design of the thermal protection system for the NASA Solar Probe spacecraft is presented. As presently conceived, the spacecraft will be launched by the Space Shuttle on a Jovian swing-by trajectory and at perihelion approach to three solar radii of the surface of the Earth's sun. The system design satisfies maximum envelope, structural integrity, equipotential, and mass loss/contamination requirements by employing lightweight carbon-carbon emissive shields. The primary shield is a thin shell, 15.5-deg half-angle cone which absorbs direct solar flux at up to 10-deg off-nadir spacecraft pointing angles. Secondary shields of sandwich construction and low thickness-direction thermal conductivity are used to reduce the primary shield infrared radiation to the spacecraft payload.
Document ID
19820048360
Document Type
Conference Paper
Authors
Dirling, R. B., Jr. (Science Applications, Inc. Irvine, CA, United States)
Loomis, W. C. (Science Applications, Inc. Irvine, CA, United States)
Heightland, C. N. (Science Applications, Inc. Irvine, CA, United States)
Date Acquired
August 10, 2013
Publication Date
June 1, 1982
Subject Category
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
AIAA PAPER 82-0897
Meeting Information
Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference(St. Louis, MO)
Funding Number(s)
CONTRACT_GRANT: NAS2-10914
Distribution Limits
Public
Copyright
Other