Abstract
Abstract : The effects of decreases in the maneuvering range angle on the design parameters for a lifting maneuverable spacecraft performing orbital plane changes aerodynamically are investigated. The design parameters considered here are the velocity or propulsion requirements, the heat transfer, accelerations, and total time of flight for the maneuver. The results indicate that these parameters become more critical as the maneuvering range decreases. Specified limits on these design parameters and constraints on the maneuvering range can be superimposed graphically on a single chart, thus defining an allowable maneuvering region. The high heating rates resulting from small-range-angle maneuvers severely restrict the extent of the maneuverability envelope. In order to extend the maneuvering capabilities for small range angles, the vehicle must be designed for high propellent capacity, high g-loading, and sophisticated heat-protection systems. (Author)
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