摘要
面向空间交会对接和停靠的任务需求,将航天器相对制导控制系统视为离散时间控制系统.利用系统状态转移模型外推预测相对运动状态偏差,在每个控制周期中推力恒定的假设下,根据轨控作用对系统状态的影响规律,采用广义逆方法反演得到交会对接制导控制序列.对时间约束下的基于空间相对运动状态转移预测与反演的相对制导控制律进行设计,讨论该方法在实际应用中的一些特点.预测与反演制导控制中的控制输出直接表示为轨控加速度,更符合工程实际情况.近圆轨道的交会对接仿真结果表明,所提出的方法能够实现精度更高、更为柔顺平滑的交会对接,在轨控速度增量和推力器输出上也具有更好的工程适用性.
For mission requirements of space rendezvous and docking, the spacecraft relative guidance and control system is considered as a discrete-time control system. The deviation of relative motion state is predicted by using the model prediction method. Under the assumptions that thrusts are constant and limited in each control cycle, according to the influence of orbit control act on system states, the relative guidance control sequence is obtained by using the generalized inverse method. A relative guidance and control law based on spatial relative motion state transition prediction and inversion is designed. Some characteristics of this method in application are discussed. In predictive and inversive guidance control, the control output is directly expressed as orbit control acceleration, which is more in line with the actual situation of the practice. Simulation results show that the proposed method can achieve more higher accuracy, more smooth rendezvous and docking, and also has better engineering applicability in speed increment and thruster output.
作者
谭天乐
TAN Tian-le(Shanghai Aerospace Control Technology Institute,Shanghai 201109,China;Shanghai Key Laboratory of Space Intelligent Control Technology,Shanghai 201109,China)
出处
《控制与决策》
EI
CSCD
北大核心
2019年第4期793-798,共6页
Control and Decision
关键词
交会对接
状态转移
模型预测与反演控制
多脉冲制导
离散时间控制系统
航天器
rendezvous and docking
state transition
model predictive and inversive control
multiple impulses guidance
discrete-time control system
spacecraft
