摘要
针对一类带有特殊气动参数不确定性的导弹,研究其自动驾驶仪的设计问题。根据导弹俯仰面动力学方程和多项式形式的气动参数,建立系统控制模型。采用基于Nussbaum增益的非线性自适应控制理论,设计导弹俯仰通道的控制器,控制律无需不确定参数的上下界信息,增强了系统的适应性和鲁棒性。该算法使闭环系统所有信号有界,同时保证了跟踪误差收敛于零。数字仿真结果表明,在考虑了各种不确定性的情况下,攻角仍能很好的跟踪指令信号,验证了控制律的正确性和有效性。
The autopilot design for missiles with highly nonlinear in aerodynamics was presented. Firstly,a nonlinear model for the missile in the pitch plane was established. Then,the controller of the missile in the pitch plane,which was based on the nonlinear adaptive control theory with nussbaum gain,was proposed. A priori knowledge of the uncertainty bounds was not required,which enhanced the system robustness. It is proved that all the system signals were bounded and the tracking error converged to zero. Finally,Numeri-cal simulation shows that the angel of attack can track the reference signal very well with system uncertain-ties. The simulation result verifies the correctness and effectiveness of the presented control law.
出处
《电机与控制学报》
EI
CSCD
北大核心
2010年第5期104-108,共5页
Electric Machines and Control
基金
总装备部武器装备预研项目(9140A01010108HT0136)
