Design and Analysis of a Three-loop Autopilot for Mixed Index and Hardware Constraint

摘要：

The static stability feature of missile airframe due to varied parameter was analyzed.The technologies transforming time-domain and frequency-domain mixed performance indexes into desired poles,as well as state feedback into output feedback were derived respectively.In view of the mixed index and hardware performance limitation,a general there-loop autopilot design procedure based on pole assignment and optimization was proposed.The analysis and simulation results show that static unstable missiles can be stabilized by a three-loop topology autopilot.However,the finite resource of actuator is the crucial limit factor dominating autopilot function,and proper distance from accelerometer to missile gravity center is benefit to improve system stability.

关键词： static unstable missile three-loop autopilot pole assignment mixed index optimization.

作者: FAN Jun-fang XIA Qun-li QI Zai-kang

作者单位: Department of Flying Vehicle Engineering,Beijing Institute of Technology,Beijing,100081,China

会议类型: 国际会议

会议名称: International Conference on Modelling,Identification and Control(模拟、鉴定、控制国际会议)

会议地点: 上海

会议语种:英文

在线出版日期: 2008-06-29（万方平台首次上网日期，不代表论文的发表时间）