论文部分内容阅读
近地卫星偏离标称轨道的过程可以表示为该卫星和一个在标称轨迹上运行的“虚”卫星的相对运动,服从Hill方程。在此基础上建立一种在线控制方法,利用模型预测控制(MPC)进行轨道优化和偏差消除,使用多变量优化的控制算法,将控制量的大小与轨道器的轨道偏差联系起来,形成反馈系统,通过给出开环和前馈-反馈闭环两种形式的控制方程,建立基于甚小推力发动机多次点火的轨道控制方法,从而确定控制量将卫星轨道实时保持在偏差管道内。
The process of a near-Earth satellite's departure from a nominal orbit can be expressed as the relative motion of the satellite and an “imaginary” satellite operating on a nominal trajectory, subjecting to the Hill equation. On the basis of this, an on-line control method is established, which uses the model predictive control (MPC) to track optimization and deviation elimination. Multivariable optimization control algorithm is used to correlate the control amount with the orbit deviation of the orbiter to form a feedback system The trajectory control method based on multi-ignition of very small thrust engine is established by giving two kinds of control equations of open-loop and feedforward-feedback closed-loop, so that the control volume can keep the satellite orbit in the deviation pipeline in real time.