Global optimization of gravity-assist trajectory with deep space maneuvers
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摘要: 借力飞行轨道设计是一个多变量强约束的非线性优化问题, 初始方案通常采用不需要初值猜测的全局优化算法进行优化, 但是借力点处的C3匹配原则等较强的约束条件极大影响了全局算法的收敛性能. 针对这一问题, 研究了附加深空机动的借力飞行模型, 在借力点处引入B平面和辅助转角, 推导了离开超越速度的解析表达式, 通过求解Lambert问题和轨道递推得到日心转移段的深空机动脉冲. 利用微分进化算法对问题进行优化, 结合木星探测算例, 对VEE (Venus-Earth-Earth), VEME (Venus-Earth-Mars-Earth)和VEVE (Venus-Earth-Venus-Earth)三种深空机动借力飞行方案进行优化, 给出了优化结果.Abstract: The problem of optimal design of a multi-gravity-assist space trajectory with deep space maneuvers is studied. Based on the zero-sphere-of-influence and patched conic hypothesis, the deep space trajectory is split into segments linked by deep space maneuvers and gravity assists. After introducing an auxiliary angle and B plane, the outgoing excess velocity could be expressed analytically. The deep space maneuver was computed by solving Lambert problem and trajectory propagation. The differential evolution algorithm is used to handle afore mentioned global optimization problem. Three cases to Jupiter, with gravity sequences of Venus-Earth-Earth (VEE), Venus-Earth-Mars-Earth (VEME) and Venus-Earth-Venus-Earth (VEVE) have been optimized.
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Key words:
- Deep-space exploration /
- Gravity-assists /
- Deep-space maneuvers /
- Differential evolution
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