基于倾斜开关曲线的小推力器姿态控制方法分析与准极限环控制方法

Attitude control using thrusters based on slantwise on-off switching line and modified limit circle control

研究了利用小推力器进行航天器姿态控制问题。从理论上推导了在给定姿态控制精度、小推力器参数以及倾斜开关曲线参数的前提下,能够形成理想极限环控制效果的充分必要条件。对相关文献中倾斜开关曲线设计方法不能形成理想极限环的情况进行了理论分析,提出了一种新的基于倾斜开关曲线的准极限环控制方法,并推导了其控制精度。研究对于航天器应用小推力器实现高精度姿态控制具有较大的工程应用价值。

The attitude control problem of a satellite using small thrusters was investigated. With a simulation example, the drawbacks of control method using slantwise on-off switching line proposed in the relevant reference were discussed. A necessary and sufficient condition for an ideal limit circle was deduced theoretically in the case that the desired attitude precision and the parameters of thrusters and slantwise on-off switching line were known previously. Analysis on the case that the ideal limit circle cannot be formed was also conducted. Based on these analyses, a new control method called ＂ Modified Limit Circle Control＂ was proposed as well as its design procedure. This study can provide meaningful reference for some relevant engineering applications.