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Abort separation of the shuttleA sensitivity analysis of the factors which affect a successful abort maneuver following a space shuttle launching is presented. Wind tunnel tests were conducted using optimum simulation techniques and data acquisition procedures. Static stability, dynamic stability, and local loads were investigated. It is concluded that parallel abort separation of the space shuttle components is possible at both high and low dynamic pressures. Successful separation is dependent upon configuration, Mach number, rocket exhaust impingement and relative position and attitude of the stages.
Document ID
19720013235
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Decker, J. P. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Blackwell, K. L. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Sims, J. L. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Burt, R. H. (ARO Huntsville, Ala., United States)
Strike, W. T., Jr. (ARO Huntsville, Ala., United States)
Andrews, C. D. (Lockheed Missiles and Space Co. Huntsville, Ala., United States)
Baker, L. R., Jr. (Lockheed Missiles and Space Co.)
Rampy, J. M. (Northrop Corp.)
Date Acquired
August 6, 2013
Publication Date
February 1, 1972
Publication Information
Publication: Space Shuttle Aerothermodyn. Tech. Conf., vol. 4 p1105-1164 (SEE N72-20880 11-31)
Subject Category
Space Sciences
Accession Number
72N20885
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19720013230Collected WorksSpace Shuttle Aerothermodynamics Technology Conference. Volume 4: Operational flight mechanics
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