摘要
针对某新型运载火箭的特点,建立发动机振动方程,分析发动机振动与全箭振动耦合关系,考虑气动参数以及弹性参数不确定性,建立全箭姿态动力学模型。采用鲁棒控制理论,进行运载火箭姿态控制系统设计,比较鲁棒控制器与PD控制仿真结果。仿真结果表明,所设计的控制器,能够实现考虑发动机振动在内的姿控系统稳定,且对参数不确定性具有良好的鲁棒性,适合工程应用。
Regarding the characteristics of certain launch vehicle,the engine vibration equations are induced. By considering the coupling between engine vibration and launch vehicle and the presence of large aerodynamic and vibrational uncertainties of parameters,a new attitude dynamics model is established.Based on the robust H∞technology,a new launch vehicle attitude control system is designed. Finally,the differences between the new control system and PD control system are discussed. The results show that the new method can satisfy the requirements of launch vehicle attitude control system design and has a better robust performance for parameter uncertainties.
出处
《航天控制》
CSCD
北大核心
2015年第5期12-16,21,共6页
Aerospace Control
关键词
运载火箭
姿控系统
参数不确定
鲁棒控制
Launch vehicle
Control system
Uncertain parameters
Robust control method
