摘要
主要研究中继星快速机动时的控制问题。设计多输入多输出特征模型的自适应控制律,结合逻辑微分控制律、逻辑积分控制律,进行卫星本体快速机动和天线指向跟踪控制;利用由Newton-Euler方法建立的挠性多体卫星的混合坐标方程动力学简化模型进行数学仿真,仿真结果表明,特征模型的自适应控制器能够保证卫星和天线的快速机动性和控制稳定性,并与传统的PD控制方法相比有更好的控制精度,同时系统参数改变时具有很强的鲁棒性。
In this paper,the control method for rapid maneuver of TDRS was studied.Adaptive control law based on the characteristic model of MIMO system,with logic derivative control law and logic integral control law,was designed and used for satellite rapid maneuver and antenna point tracing.The simplified dynamics of multi -body satellites with flexibility based on Newton-Euler method and expressed in hybrid coordinate equations were used in numerical simulations.The results of simulations were given to show that the adaptive control law based on the characteristic mode can satisfy the maneuver and stability of satellite and antenna.Compared with traditional PD controller,the designed controller has better performance and very strong robustness when parameters of system are changed.
出处
《计算机仿真》
CSCD
北大核心
2013年第7期87-91,共5页
Computer Simulation
关键词
中继星
快速机动
天线指向
特征模型
自适应控制
TDRS
Rapid maneuver
Antenna point
Characteristic model
Adaptive control
