【摘要】 针对采用双脉冲发动机的防空导弹拦截临近空间高速目标的多约束中制导问题,设计了一种基于逆轨拦截且满足过载收敛的预测-校正制导方法。该算法在基于由最优控制理论推导的满足终端位置、速度约束的ZEM-ZEV算法基础上,以具有航迹角约束的零控拦截流形作为交班条件,采用数值预测方法对剩余飞行时间进行高精度求解,通过在线动态生成初-中制导交班的速度方向和II脉冲发动机的开机时刻来降低中制导段需用过载。蒙特卡洛打靶仿真结果表明本文所提出的中制导算法能够满足带航迹角约束的零控拦截条件,对模型的参数偏差和不确定性具有强鲁棒性,具备重要的理论意义和工程应用价值。更多还原

【Abstract】 For the multi-constraint problem in midcourse guidance stage of an interceptor which intercepts a near space target with double-pulse motor, a predictor-corrector guidance method based on head-on interception is proposed which can meet the overload convergence. In terms of the optimal control theory, the ZEM-ZEV guidance law is derived which can satisfy both the position and velocity constraints. The method uses the zero-effort-intercept manifold with the track angle constraint as the transfer conditions of the midcourse-to-terminal guidance. The numerical prediction method is used to solve the time-to-go with high accuracy. The velocity direction in the handover of initial-to-midcourse guidance and the ignition time of the second-pulse motor are introduced which can reduce the overload in the midcourse guidance stage. The results of the Monte Carlo simulation demonstrate that the proposed midcourse guidance algorithm can meet the requirements of the zero-effort-intercept manifold with the track angle constraint. It has strong robustness and excellent performance to the deviations and uncertainties of the model parameters. The algorithm has important theoretical significance and certain reference value for practical engineering applications.更多还原