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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 the problem of orbit control of solar sail spacecraft, a new analytic optimal control law is given, which can make the rate of change of orbital energy of the spacecraft reach the maximum during the escape so as to ensure the shortest escape time. Orbit shape, introducing the improved ornithological orbit root number to describe the kinematic equation of the spacecraft, and gives the derivation process of the optimal control law for the earth’s orbit. Simulation results show that the control law is fast and can be calculated according to spacecraft State real-time calculation of attitude control angle, it is more suitable for future solar sail spacecraft in-orbit autonomous control system.