摘要
研究小推力电推进轨道优化问题，推力加速度量级为１０－２～１０－４，优化方法为间接法。利用末端横截条件反向积分伴随方程，避开伴随变量的初值猜测，运用迭代法数值求解了逃逸地心引力场轨道和低轨道变轨优化。计算结果表明，小推力作用下的最优转移轨道几乎为圆形，转移时间较长。小推力大小与作用时间成近似线性反比关系。小推力情况下，横向控制比最优控制更为合理。
The trajectory optimization for low thrust electric propulsion has been researched in the paper.The orders of the acceleration are of 10 -2 ～10 -4 .The indirect approach is used in optimization.The adjoint equations are integrated backword to avoid the initial guess of adjoint variables by means of the transversality condition.The earth escape trajectory and low orbit transfer optimization are numerically resolved by iteration method.The results show the optimal transfer orbits are almost circular,and transfer time is long.The magnitude of low thrust is inverse proportion.
出处
《中国空间科学技术》
EI
CSCD
北大核心
1998年第2期8-13,共6页
Chinese Space Science and Technology
基金
国家自然科学基金
