摘要
应用双时标的假设 ,将导弹动力学分离为快变状态动力学和慢变状态动力学。然后 ,对慢变动力学和快变动力学分别进行反馈线性化设计。考虑到空气动力系数具有较大的不确定性 ,进一步 ,对期望的慢变动力学和快变动力学进行鲁棒控制设计。
Based on the two timescale assumption,the dynamics of the BTT missile are separated into two parts:the dynamics of fast state and the dynamics of slow state.Then,the dynamics of fast state and the dynamics of slow state are linearized respectively.Furthermore,considering the uncertainty of the aerodynamic coefficient of the BTT missile,the desired dynamics of fast state and the dynamics of slow state are designed based on Lyapunov stability theory.Six degree of freedom simulation results have shown the rightness and effectiveness of the proposed scheme.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2002年第2期89-91,共9页
Journal of Astronautics
基金
航空科学基金资助项目 No.99D12 0 0 1。
