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.


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    Title :

    Implications of maneuvering-range constrains on lifting-vehicle design


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Lau, J. (author)

    Published in:

    Publication date :

    1967


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :