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
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;
Conference_Titel :
Control Conference (CCC), 2013 32nd Chinese
Conference_Location :
Xi´an
