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Space Shuttle guidance for multiple main engine failures during first stageThis paper presents contingency abort guidance schemes recently developed for multiple Space Shuttle main engine failures during the first two minutes of flight (first stage). The ascent and entry guidance schemes greatly improve the possibility of the crew and/or the Orbiter surviving a first stage contingency abort. Both guidance schemes were required to meet certain structural and controllability constraints. In addition, the systems were designed with the flexibility to allow for seasonal variations in the atmosphere and wind. The ascent scheme guides the vehicle to a desirable, lofted state at solid rocket booster burnout while reducing the structural loads on the vehicle. After Orbiter separation from the solid rockets and the external tank, the entry scheme guides the Orbiter through one of two possible entries. If the proper altitude/range/velocity conditions have been met, a return-to-launch-site 'Split-S' maneuver may be attempted. Otherwise, a down-range abort to an equilibrium glide and subsequent crew bailout is performed.
Document ID
19870063207
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Sponaugle, Steven J.
(McDonnell-Douglas Astronautics Co. Houston, TX, United States)
Fernandes, Stanley T.
(McDonnell Douglas Astronautics Co. Houston, TX, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1987
Subject Category
Space Transportation
Report/Patent Number
AIAA PAPER 87-2398
Accession Number
87A50481
Funding Number(s)
CONTRACT_GRANT: NAS9-17650
Distribution Limits
Public
Copyright
Other

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