Missile Autopilot Design and Analysis Based on Backstepping
The tactical missile autopilot design process is detailed from a backstepping control perspective. Wherein, two autopilot topologies are proposed, i.e. the angle of attack (AOA) autopilot and acceleration autopilot. A set of new parameters is presented to simplify the expression of AOA control law and show that the positive real requirement on control parameters during step by step design has an unfavorable effect on closed loop system performance. An acceleration autopilot as a tracking problem is then set up and developed. Two control gains, i.e. k1 and k2, are determined on the basis of step and sine command tracking. The results show that k1 affects mainly system steady state error, and k2 affects mainly response speed. Moreover, k1 is bounded and its upper bound has less relevance with k2. The nonlinear acceleration autopilot based on a backstepping approach exhibits excellent tracking performance and robustness. In spite of good performance, the application of nonlinear autopilot is limited owing to a lack of physical meaning and complex engineering implementation.
FAN Jun-fang SU Zhong CHENG Zhen-xuan
Beijing Information Science & Technology University,Beijing,China Department of Control Engineering,Beijing Information Science & Technology University China Academy of Ordnance Science.
国际会议
哈尔滨
英文
1052-1056
2010-01-08（万方平台首次上网日期，不代表论文的发表时间）