考虑功率约束的太阳能电推进轨道优化设计  

Trajectory design for a solar electric propulsion spacecraft constrained by the solar power

作　　者：陈杨[1] 宝音贺西[1] 李俊峰[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《清华大学学报（自然科学版）》2013年第10期1498-1502,1508,共6页Journal of Tsinghua University(Science and Technology)

基　　金：国家自然科学基金重点项目(10832004);国家自然科学基金项目(10722122)

摘　　要：电推进航天器通常由太阳能电池阵供电,因而实际深空探测任务中发动机的推力工况受到星日距离的限制。该文研究了功率约束下电推进航天器的轨道优化设计问题。首先推导太阳能电池阵功率对发动机最大推力的约束。采用间接法将电推进轨道的燃料最优控制问题转化为两点边值问题。求解过程中提出了适应太阳能电推进轨道优化的星日距离检测并应用了同伦迭代、开关函数检测等求解技术,能够准确、快速地得到满足太阳能电池阵功率约束的设计轨道。算例表明,该设计方法具有良好的可行性和工程实用价值。The electricity for an electric propulsion spacecraft is provided by the solar arrays, so the working conditions of the electric thruster are constrained by the radius of the spacecraft from the sun in deep space exploration missions. The trajectory design of a solar electric propulsion spacecraft constrained by the solar power is studied here. The power constraint is formed as a constraint on the thrust. An indirect method is then used to solve the two-point boundary-value problem （TPBVP） derived from the fuel optimal control problem. The heliocentric distance is used in solving the solar electric propulsion problem. Effective techniques, such as the homotopic approach and switch detection, are used to find the designed trajectory satisfying the power constraint. A case study shows that this algorithm is effective and may be widely used in engineering problems.

关 键 词：轨道设计 太阳能电推进 最优控制 间接法 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]