The problem of optimization of the heliocentric segment of the interplanetary trajectory between two planets of a spacecraft with a limited thrust engine is considered. The description of homotopy between the optimal trajectory with limited power or Keplerian trajectory (solution of Lambert's problem) and the optimal trajectory with limited thrust is given. The thrust minimization problem is introduced, by means of which the existence domain of the solution is calculated. The problem of joint optimization of control, main trajectory and design parameters of a spacecraft with a limited thrust engine is considered. Numerical examples of optimal trajectories are given.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Thrust-limited optimal three-dimensional spacecraft trajectories

    Pourtakdoust, Seid / Jalali, Mir | AIAA | 1995



    Interplanetary spacecraft using fusion-powered thrust

    DREXLER JEROME | European Patent Office | 2019

    Free access


    INTERPLANETARY SPACECRAFT USING FUSION-POWERED THRUST

    DREXLER JEROME | European Patent Office | 2018

    Free access