以滑翔制导炸弹为背景,利用最优控制理论,结合求解状态转移矩阵的方法,推导了一种具有末端姿态角约束的最优末制导律。该末制导律保证了脱靶量和控制能量消耗最小的性能指标,适用于攻击地面固定目标。通过数字仿真,并与有末端姿态角约束的修正比例导引律进行对比。仿真结果表明该最优末制导律在满足制导精度要求下提高了末端入射角。

Based on a kind of gliding guidance bomb, an optimal terminal guidance law with constraint on terminal impact angle was deduced by using the optimal control theory and the method of state transition matrix. This method guarantees the minimum of miss distance and energy consumption. It is suitable for attacking the fixed ground target. The digital simulation was compared with the proportional guidance law of terminal angular constraint. The simulation results prove that the proposed optimal terminal guidance law can improve the terminal impact angle with precise guidance.