有限推力航天器双主动交会的最优控制  

Optimal cooperative finite-thrust spacecraft out-of-plane rendezvous using direct collocation method

作　　者：潘伟[1] 路长厚[1] 冯维明[2] 葛培琪[1] 

机构地区：[1]山东大学机械学院,济南250061 [2]山东大学土建学院,济南250061

出　　处：《固体火箭技术》2009年第4期373-378,共6页Journal of Solid Rocket Technology

摘　　要：研究了两异面椭圆轨道的有限推力航天器在协同轨道机动以完成交会任务(双主动交会)时的最优控制问题。构造了有限推力航天器双主动交会的数学模型,讨论了其实现最优控制的必要条件。针对推进剂总消耗最少和有限推进剂约束下的最短时间交会2种不同情况,采用直接配置法和序列二次规划法求解了反平方力场中的最优控制数值解。考察了不同初始参数对双主动交会最优控制历程的影响,并将双主动交会形式与主被动交会形式进行了对比。结果表明,当两航天器质量接近时,双主动交会在减少燃料消耗或缩短交会所需时间方面具有明显优势。The out-of-plane rendezvous of two finite-thrust spacecraft is investigated. Both vehicles are active and provide thrust to complete the rendezvous. The necessary condition of the optimum control for cooperative finite-thrust rendezvous is discussed, and direct collocation with sequential quadratic programming method is used to obtain cooperative rendezvous solutions in an inverse square gravitational field. Minimum-fuel consumption rendezvous and fuel constrained minimum-time rendezvous are considered. Compared with optimal active-passive solutions, optimal cooperative rendezvous solutions has the advantage of the decrease of total fuel or time consumption evidently.

关 键 词：双主动交会 有限推力 最优控制 直接配置法 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]