中国空间科学技术2011，Vol.31Issue(2)：16-24,78,10.DOI:10.3780/j.issn.1000-758X.2011.02.003
摄动椭圆参考轨道上的最优精确交会
Fuel-optimal Precise Rendezvous Guidance Law in Elliptical Reference Orbit with J2 Perturbation
荆武兴 1陈伟跃1
作者信息
- 1. 哈尔滨工业大学航天学院,哈尔滨150001
- 折叠
摘要
Abstract
For rendezvous near an elliptical reference orbit, a numerical gradient algorithm and a genetic algorithm for optimization were adopted to determine the optimal transfer time and impulses.The solutions for half-revolution and complete-revolution rendezvous were also given to eliminate the singularities.Based on the optimization algorithms, a two-impulse iteration method with linear gradient was proposed for rendezvous guidance to eliminate the impact of J2 perturbation on relative motion.The simulation results of rendezvous near reference orbit with different eccentricities show that the guidance algorithm is simple, feasible and can be used in remote rendezvous near circle and arbitrary elliptical reference orbit.关键词
线性梯度/迭代算法/轨道摄动/椭圆轨道/交会对接/航天器Key words
Linear gradient / Iterative algorithm / Orbit perturbation / Elliptical orbit/Rendezvous and docking / Spacecraft引用本文复制引用
荆武兴,陈伟跃..摄动椭圆参考轨道上的最优精确交会[J].中国空间科学技术,2011,31(2):16-24,78,10.
