太阳帆航天器地球逃逸轨道解析最优控制律  

Solar sail analytical optimal control law for earth escape transfer orbit

作　　者：史晓宁[1] 李立涛[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2期253-258,共6页Control and Decision

基　　金：国家自然科学基金项目(40776051;60940018)

摘　　要：针对太阳帆航天器地球逃逸轨道控制问题,给出一种新的解析最优控制律.该控制律可使航天器在逃逸过程中轨道能量变化速率最大,从而保证逃逸时间最短.考虑到地球逃逸轨道形状,引入改进春分点轨道根数对航天器运动学方程进行描述,并给出了地球逃逸轨道最优控制律的推导过程.仿真分析表明,该控制律计算速度较快,而且可以根据航天器状态实时计算姿态控制角,因此比较适用于未来太阳帆航天器在轨自主控制系统.Aiming at orbit control problem for escaping the earth with solar sail,a new analytical optimal control law is presented.This approach maximizes the instantaneous rate of the increase of the total orbital energy in the process of escaping the earth,so as to ensure the shortest escape time.The equations of motion for the trajectory are expressed in modified equinoctial orbital elements,which are well behaved as the trajectory going from elliptic to hyperbolic during escape.Furthermore,the derivation of escaping the earth optimal control law is given.Simulation analysis shows that the control law has higher computational speed,and can real-timely calculate the attitude control angle according to the state of spacecraft by the simulation analysis,hence the control law is suitable for the application in future on-orbit solar sail autonomous control system.

关 键 词：太阳帆航天器 逃逸轨迹 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]