• DocumentCode
    1722740
  • Title

    Optimal transfer orbit design based on multi-pulse thrust

  • Author

    Xu Limin ; Liu Han ; Zhang Tao

  • Author_Institution
    Dept. of Autom., Tsinghua Univ., Beijing, China
  • fYear
    2013
  • Firstpage
    5193
  • Lastpage
    5197
  • Abstract
    This paper studies the optimal transfer trajectory planning problem in the near-range closing phase for spacecraft rendezvous process. Based on C-W equation, an optimal programming model for fuel-cost minimization is created, and non-linear programming algorithms are used to solve the problem. Simulation results confirm the effectiveness of the algorithms.
  • Keywords
    aerospace control; nonlinear programming; space vehicles; trajectory control; CW equation; fuel cost minimization; multipulse thrust; near range closing phase; nonlinear programming algorithms; optimal programming model; optimal transfer orbit design; optimal transfer trajectory planning problem; spacecraft rendezvous process; Equations; Mathematical model; Navigation; Optimization; Orbits; Programming; Trajectory; Impulse thrust; Optimal transfer orbit; Rendezvous and docking;
  • fLanguage
    English
  • Publisher
    ieee
  • Conference_Titel
    Control Conference (CCC), 2013 32nd Chinese
  • Conference_Location
    Xi´an
  • Type

    conf

  • Filename
    6640342
    • Link To Document
    https://search.isc.ac/dl/search/defaultta.aspx?DTC=49&DC=1722740