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Solid rocket booster thermal radiation model, volume 1A solid rocket booster (SRB) thermal radiation model, capable of defining the influence of the plume flowfield structure on the magnitude and distribution of thermal radiation leaving the plume, was prepared and documented. Radiant heating rates may be calculated for a single SRB plume or for the dual SRB plumes astride the space shuttle. The plumes may be gimbaled in the yaw and pitch planes. Space shuttle surface geometries are simulated with combinations of quadric surfaces. The effect of surface shading is included. The computer program also has the capability to calculate view factors between the SRB plumes and space shuttle surfaces as well as surface-to-surface view factors.
Document ID
19760017262
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Watson, G. H. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Lee, A. L. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1976
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-144300
LMSC-HREC-TR-D496763-VOL-1
Accession Number
76N24350
Funding Number(s)
CONTRACT_GRANT: NAS8-31310
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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