Problems of onboard trajectory optimization and synthesis of suitable guidance laws for ascent to low Earth orbit of an air-breathing, single-stage-to-orbit vehicle are addressed. A multimode propulsion system is assumed which incorporates turbojet, ramjet, Scramjet, and rocket engines. An algorithm for generating fuel-optimal climb profiles is presented. This algorithm results from the application of the minimum principle to a low-order dynamic model that includes angle-of-attack effects and the normal component of thrust. Maximum dynamic pressure and maximum aerodynamic heating rate constraints are considered. Switching conditions are derived which, under appropriate assumptions, govern optimal transition from one propulsion mode to another. A nonlinear transformation technique is employed to derived a feedback controller for tracking the computed trajectory. 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 :

    A real-time guidance algorithm for aerospace plane optimal ascent to low earth orbit


    Contributors:

    Conference:

    1989 American Control Conference ; 1989 ; Pittsburgh, PA, United States


    Publication date :

    1989-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Optimal Ascent Trajectory and Guidance Law for Aerospace Plane

    Suzuki, H. / Fushimi, H. / Matsumoto, Y. et al. | British Library Conference Proceedings | 1999


    Optimal ascent trajectory and guidance law for aerospace plane

    Suzuki, Hirokazu / Fushimi, Hidenobu / Matsumoto, Yoshiaki et al. | AIAA | 1999


    Aerospace plane ascent guidance considering aeropropulsive interactions

    Kremer, Jean-Paul / Mease, Kenneth | AIAA | 1995