Problems associated with on-board trajectory optimization and with the synthesis of guidance laws are addressed for ascent to LEO of an air-breathing, single-stage-to-orbit vehicle. A multimode propulsion system is assumed which incorporates turbojet, ramjet, scramjet, and rocket engines. An energy-state approximation is applied to a four-state dynamic model for flight of a point mass over a spherical nonrotating earth. An algorithm for generating fuel-optimal climb profiles is derived via singular perturbation theory. This algorithm results from application of the minimum principle to a low-order dynamic model that includes general functional dependence on angle of attack and a normal component of thrust. Switching conditions are derived which, under appropriate assumptions, govern optimal transition from one propulsion mode to another. The use of bank angle to modulate the magnitude of the vertical component of lift is shown to improve the index performance. Numerical results illustrate the nature of the resulting fuel-optimal climb paths.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Optimal guidance and propulsion control for transatmospheric vehicles


    Contributors:

    Publication date :

    1989-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Optimal guidance and propulsion control for transatmospheric vehicles

    CORBAN, J. / CALISE, A. / FLANDRO, G. | AIAA | 1989


    Transatmospheric vehicles

    RAND; Project AIR FORCE | British Library Conference Proceedings | 1997


    Space and Transatmospheric Propulsion Technology

    C. Merkle / M. L. Stangeland / J. R. Brown et al. | NTIS | 1994



    Airbreathing Propulsion for Transatmospheric Flight

    G. Andrei / U. Borio / M. Maiurano | NTIS | 1990