摘要
为了对以X-51A为代表的临近空间高超声速飞行器实施有效拦截,提出一种新的具有强鲁棒性的非线性H∞制导律。首先,将目标机动作为系统扰动,建立拦截弹—目标相对运动学数学模型;根据几何方法拦截策略分析,提出以离心加速度的均方根为扰动输出;引入Hamilton函数并基于最优控制理论,得到非线性H∞制导律。该方法利用Lyapunov稳定性理论严格证明了制导系统的全局渐近稳定性,且无需求解Hamilton-Jacobi-Issacs(HJI)偏微分方程。仿真结果表明,该制导律不仅具有很强的鲁棒性也能获得良好的制导精度。
In order to implement effective intercept of the near space hypersonic vehicle such as X -51A, a new continuous nonlinear H∞ guidance law with robustness is proposed .First, the mathematic mode is built according to the relationship between the missile and the target whose acceleration is intro -duced as disturbance .The root mean square of the centrifugal acceleration as the disturbance output is proposed based on the intercept strategic analysis by the geometric relationship .The nonlinear H∞ guid-ance law are obtained by Hamilton function and the optimal control theory .The asymptotic stability of the guidance system is strictly proved by Lyapunov stability theory , and applying this method , it is unnecessa-ry to solve the Hamilton-Jacobi-Iasscs（ HJI） partial differential equation .The simulation results show that the guidance law not only has strong robustness but also get good guidance accuracy .
出处
《航空兵器》
2014年第4期8-11,共4页
Aero Weaponry
