| 地-空导弹自适应最优制导律初探 |
| |
| 引用本文： | 胡建和,李忠应.地-空导弹自适应最优制导律初探[J].北京航空航天大学学报,1991(3):101-110. |
| |
| 作者姓名： | 胡建和 李忠应 |
| |
| 作者单位： | 北京航空航天大学宇航学院
(胡建和)，北京航空航天大学宇航学院(李忠应) |
| |
| 摘 要： | 本文从自适应控制的基本思想出发,利用最优控制理论,在建立地-空导弹最优制导律的基础上,考虑导弹质心的动力学方程,建立了扩维的系统状态方程和测量方程。再利用最优控制理论和非线性系统扩维Kalman滤波理论,推导出地-空导弹自适应最优制导律,进行数字计算,得到了比较满意的结果,为进一步探讨地-空导弹的自适应最优制导律提供了有价值的参考。
|
| 关 键 词： | 面对空导弹 最优制导律 自适应控制 |
A STUDY ON REMOTE MISSILE ADAPTIVE OPTIMAL GUIDANCE LAW |
| |
| Hu Jianhe Li Zhongyin.A STUDY ON REMOTE MISSILE ADAPTIVE OPTIMAL GUIDANCE LAW[J].Journal of Beijing University of Aeronautics and Astronautics,1991(3):101-110. |
| |
| Authors: | Hu Jianhe Li Zhongyin |
| |
| Institution: | Shool of Astronautics |
| |
| Abstract: | From the point of adaptive control view .the paper obtains a remote missile optimal guidance law by applying optimal control theory. Above this basis, considering the dynamics equation of the missile mass' center,the extended dimension system state equation is established. And it obtains a remote missile adaptive optimal guidance law by applying again optimal control theory and nonliner system extended dimension kalman filt theory. The numerical computations confirm The results are staisfactory. the paper gives valuble reference for further researching a remote missile adaptive optimal guidance law. |
| |
| Keywords: | adaptive control optimal control guidance law nonliner filt |
| 本文献已被 CNKI 维普 等数据库收录！ |
|
