基于解析控制律的太阳帆星际转移轨道控制  

Solar sail heliocentric transfer orbit control based on analytical control laws

作　　者：史晓宁[1] 郭继峰[1] 荣思远[1] 崔乃刚[1] 

机构地区：[1]哈尔滨工业大学航天工程系,哈尔滨150001

出　　处：《控制与决策》2013年第3期424-428,433,共6页Control and Decision

基　　金：国家自然科学基金项目(61005060)

摘　　要：太阳帆航天器可依靠反射太阳光子提供动力,因此较适用于远距离的星际转移任务.针对太阳帆航天器星际转移轨道控制问题,提出一种新的解析最优控制律,通过设定混合权重对各轨道根数进行联合控制.引入改进春分点轨道根数对解析控制律进行了优化推导,并以水星探测任务为背景进行了相应的仿真分析.仿真结果表明,该控制律计算速度较快,可对各个轨道根数进行联合控制,从而得到满足工程要求的太阳帆航天器星际转移轨道.Solar sail spacecrafts can provide motivation rely on reflecting the sun photons, so that it is suitable for long distance interstellar transfer task. Aiming at the problem of solar sail interstellar transfer orbit control, a new analytical control law is presented. This control law can realize the combination control of each orbit elements by setting the blending weights. The modified equinoctial orbital elements are introduced to the optimal derivation of the analytical optimal control law, and numerical simulations for the method are performed based on mercury exploration mission. Simulation results show that, the proposed control law has higher computational speed and the capability of realizing the combination control of each orbit elements, thus the solar sail interstellar transfer orbit can be obtained, which can satisfy the requirements of the project.

关 键 词：太阳帆航天器 日心转移轨道 解析法 最优控制律 轨道控制 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]