Implications of Maneuvering-Range Constraints on Lifting-Vehicle Design.

J. Lau

Expert InsightsPublished 1966

An investigation of the effects of decreases in the maneuvering range angle on the design parameters for a lifting maneuverable spacecraft performing orbital plane changes aerodynamically. Results indicate that the parameters considered-- velocity or propulsion requirements, heat transfer, accelerations, and total time of flight for the maneuvering range decreases. Specified limits on these parameters and constraints on the maneuvering range can be superimposed graphically on a single chart, thus defining an allowable maneuvering region. Such composite charts indicate that to expand the operational region and fully use the vehicle's extensive maneuvering capabilities for small-range-angle maneuvers, the spacecraft must be designed for large propellant capacity, high g-loading, and sophisticated heat-protection systems. 28 pp. Ref.

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Lau, J., Implications of Maneuvering-Range Constraints on Lifting-Vehicle Design. Santa Monica, CA: RAND Corporation, 1966. https://www.rand.org/pubs/papers/P3424.html.
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