The optimal control problem arising in coplanar, orbital transfer employing aeroassist technology is addressed. The maneuver involves the transfer from high Earth orbit to low Earth orbit. A performance index is chosen the minimize the fuel consumpltion for the transfer. Simulations are carried out for establishing a corridor of entry conditions which are suitable for flying the spacecraft through the atmosphere. A highlight of the paper is the application of an efficient multiple shooting method for taming the notorious nonlinear, two-point, boundary value problem resulting from optimization procedure.


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    Title :

    Guidance and control strategies for aerospace vehicles


    Contributors:

    Publication date :

    1988-07-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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