Integrated Guidance/Autopilot Design for Missiles With Impact Angle Constraints
A scheme of integrated guidance/autopilot design for missiles with impact angle constraints is studied in this paper. When the integrated guidance/autopilot model yaw plane is formulated, the guidance/control law with impact angel constraints is designed based on the backstepping idea and VSC theory. For the unavailable information of the maneuvering target, an estimating method is given. Finally, to verify the effectiveness and rightness of the integrated design scheme, the simulation of some missile has been made, the simulation results have shown that high accuracy of hitting target with impact angle constraints can be got.
Qingjiu Xu Jiandong Yu Jinyong Yu Xiuzhen Yang
Department of Automatic Control, Naval Aeronautical Engineering Institute, 264001, Yantai, .R.China Department of Management, Naval Aeronautical Engineering Institute, 264001, Yantai, .R.China
国际会议
2006 IEEE International Conference on Information Acquisition
山东威海
英文
75-79
2006-08-20（万方平台首次上网日期，不代表论文的发表时间）