Indirect optimization is used in this paper to compute fuel-optimal earth escapetrajectory. By shooting backward in time we convert the unknowns from initialLagrange multipliers to orbit states at the final time. The three-dimensionallong-time fuel-optimal escape trajectory with control constraint is designed byfirst solving a two-dimensional short-time fuel-optimal escape trajectory withoutcontrol constraint; then using a curve fitting technique to generate initialguess for the final state. This accuracy and efficiency of the proposed methodis demonstrated on a low thrust escape trajectory optimization problem.
展开▼
