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研究了考虑太阳引力影响的地-月系统中绕L2点轨道的保持问题。在地-月系统圆形限制性三体问题的基础上,考虑太阳的影响,先用微分修正法得到飞行器的初始状态,然后根据方程的对称性,分别沿时间的负向、正向积分,得到绕L2点的闭合轨道。以该闭合轨道为目标轨道,根据模型的动力学特点,设计变结构滑膜控制律。仿真结果表明,该控制律能很快消除飞行器入轨时位置、速度的偏差,使飞行器在目标轨道上稳定飞行。该文的结果可应用于对月球背面的定点观测或中继站。
The problem of preserving the orbit around L2 at the ground-moon system, which is affected by the solar attraction, is studied. On the basis of the circular restricted three-body problem of the earth-moon system, considering the influence of the sun, the initial state of the aircraft is obtained by the differential correction method. Then according to the symmetry of the equation, Get a closed orbit around point L2. With the closed orbit as the target orbit, according to the dynamic characteristics of the model, the variable structure synovial law is designed. The simulation results show that the control law can quickly eliminate the deviation of position and velocity of the vehicle when entering the orbit, and make the aircraft fly stably on the target orbit. The result of this paper can be applied to the observation of the moon or the relay station.