摘要
针对拦截机动目标问题,提出了一种新的具有强鲁棒性的非线性变结构末制导律。基于弹目相对运动学的非线性关系,将目标机动作为系统扰动,建立了弹目相对运动的数学模型。并基于零化弹目视线角速率的思想,利用一种新的双幂次趋近律设计方法,得到了非线性变结构末制导律。该方法利用Lyapunov稳定理论,严格证明了制导系统的全局渐近稳定性。数字仿真结果表明,所设计的制导律与比例导引律相比,对高速大机动目标具有很强的鲁棒性和适应性,并能获得良好的制导精度。
For the case of intercepting a maneuvering target,a new nonlinear sliding mode guidance law with robustness is proposed.The mathematic model was built according to the nonlinear relationship between missile and target whose acceleration as disturbance was introduced.Based on the method of zeroing the rate of line-of-sight angle,a global variable control strategy was contrived to obtain the nonlinear terminal guidance law by introducing a new two-power reaching law.The stability of guidance system was strictly proven by the Lyapunov stability theory.An illustrative example is given to show that the new guidance law is more robust and suitable to the missile for intercepting the target with high velocity and high maneuver than the proportional navigation law,and the better precision of guidance law is obtained.
出处
《飞行力学》
CSCD
北大核心
2010年第5期55-58,共4页
Flight Dynamics
基金
航天支撑基金资助(N8XW0001)
