NASA NTRS · 19860015275
Advanced orbit transfer vehicle propulsion system study
Abstract
A reuseable orbit transfer vehicle concept was defined and subsequent recommendations for the design criteria of an advanced LO2/LH2 engine were presented. The major characteristics of the vehicle preliminary design include a low lift to drag aerocapture capability, main propulsion system failure criteria of fail operational/fail safe, and either two main engines with an attitude control system for backup or three main engines to meet the failure criteria. A maintenance and servicing approach was also established for the advanced vehicle and engine concepts. Design tradeoff study conclusions were based on the consideration of reliability, performance, life cycle costs, and mission flexibility.
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Cathcart, J. A., Cooper, T. W., Corringrato, R. M., Cronau, S. T., Forgie, S. C., Harder, M. J., Mcallister, J. G., Rudman, T. J., Stoneback, V. W.. 1985-02-01. Advanced orbit transfer vehicle propulsion system study. https://ntrs.nasa.gov/citations/19860015275
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