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The effects of flow separation on shuttle dynamics and aeroelastic stabilityThe effects of flow separation on the dynamic and aeroelastic stability of various shuttle configurations have been investigated. Flow separation is shown to affect the aeroelastic stability of the 747/Orbiter yaw modes, the orbiter dynamic stability and possibly the aeroelastic stability of the wing torsional mode, and to dominate both the dynamic and aeroelastic stability of the launch configuration. Limit cycle oscillations of certain launch configuration modes are the result of sudden flow separation. The limit cycle oscillations threaten the structural integrity in two ways: (1) by outright overstressing of the structure due to large modal deflection, (2) by fatigue due to the continued flexing of the structure. Fatigue is a more significant consideration for the reusable (100 flights) shuttle than it has been for previous space boosters.
Document ID
19770036986
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Reding, J. P. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Ericsson, L. E. (Lockheed Missiles and Space Co., Inc. Sunnyvale, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1977
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 77-116
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Los Angeles, CA
Start Date: January 24, 1977
End Date: January 26, 1977
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
77A19838
Funding Number(s)
CONTRACT_GRANT: NAS8-30652
Distribution Limits
Public
Copyright
Other

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