摘要
Abstract
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 .关键词
临近空间拦截弹/H∞制导律/Lyapunov方法Key words
near-space interceptor/H∞ guidance/Lyapunov methods分类
军事科技
