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Space Shuttle First Stage Ascent Design
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English
Abstract
The first stage ascent trajectory of the space shuttle uses an open-loop guidance scheme. A reference trajectory profile is designed preflight and loaded into the onboard general purpose computers. The reference trajectory is a trade-off among aerodynamic loads, heating constraints, and payload requirements.
In the space shuttle flights after Space Transportation System (STS) 51-L, the ascent design has been mission specific. As the program continues to mature, a standardization of ascent design will be pursued to reduce resource requirements for each flight. A day-of-launch (DOL) ascent trajectory, designed only hours before launch and based on real-time wind and atmosphere conditions, is currently being studied and will be tested in early 1990.
Citation
Bowers, D., "Space Shuttle First Stage Ascent Design," SAE Technical Paper 892268, 1989, https://doi.org/10.4271/892268.Also In
References
- “Shuttle Systems Design Criteria,” Shuttle Performance Assessment Databook I April 1989
- “Functional Subsystem Software Requirements Guidance, Navigation, and Control,” Part A, Guidance Ascent/RTLS, NASA STS 83-0002B June 1987
- Olson, L. M. “Postflight Evaluation of the Shuttle Guidance, Navigation, and Control During Powered-Ascent Flight Phase,” AIAA August 1982