Effects of decreases in maneuvering-range angle on design parameters for lifting maneuverable spacecraft performing orbital plane changes aerodynamically are investigated; parameters are velocity or propulsion requirements, heat transfer, accelerations, and total time of flight for maneuver; specified limits on parameters andconstraints on maneuvering range can be superimposed graphically on single chart, thus defining allowable maneuvering region; to extend maneuvering capabilities for small range angles, vehicle must be designed for high propellant capacity, high g loading, and heat-protection systems.
Implications of maneuvering-range constrains on lifting-vehicle design
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 5 ; p 639-643
1967
5 pages
Article (Journal)
English
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