This paper will present a complete formulation of the optimal control problem for atmospheric ascent of rocket powered launch vehicles subject to usual load constraints and final condition constraints. We shall demonstrate that the classical finite difference method for two-point-boundary-value-problems (TPBVP) is suited for solving the ascent trajectory optimization problem in real time, therefore closed-loop optimal endoatmospheric ascent guidance becomes feasible. Numerical simulations with a the vehicle data of a reusable launch vehicle will be provided.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Closed-Loop Endoatmospheric Ascent Guidance


    Contributors:
    Lu, Ping (author) / Sun, Hongsheng (author) / Jackson, Scott (author)

    Conference:

    2002 AIAA GN and C Conference ; 2002 ; Monterey, CA, United States


    Publication date :

    2002-01-01


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English




    Closed-Loop Endoatmospheric Ascent Guidance

    Ping Lu / Hongsheng Sun / Bruce Tsai | AIAA | 2003


    Closed-Loop Endoatmospheric Ascent Guidance

    Lu, P. | Online Contents | 2003


    Endoatmospheric Ascent Optimal Guidance with Analytical Nonlinear Trajectory Prediction

    Shilei Zhao / Wanchun Chen / Liang Yang | DOAJ | 2022

    Free access

    Closed-Loop Endo-Atmospheric Ascent Guidance

    Lu, Ping / Sun, Hongsheng / Tsai, B. | AIAA | 2002


    All attitude guidance and control for endoatmospheric intercepts

    STRAUSS, B. / GRAVINA, R. / HASENZHL, C. et al. | AIAA | 1993