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针对空地导弹末制导段终端角约束问题,根据滑模控制理论,设计了加速度控制指令垂直于弹目视线方向的制导规律。从建立末制导过程中导弹和目标间的动力学方程入手,推导出以视线角和视线角速度为状态量的状态方程,构建了一个滑模面,在这个滑模面上弹目视线角和期望的终端角之差与弹目视线角速度为零。又引入Lyapunov函数驱动系统达到所设计的滑模面,综上推导出控制加速度的表达形式。该导引律在满足终端角要求的同时,能进一步增大导弹击顶速度。最后,在MATLAB环境下构建了几种仿真场景,仿真结果表明该制导律的有效性。
Aiming at the terminal corner constraint of the final guidance section of air-to-ground missile, according to the sliding mode control theory, the guidance law of the acceleration control command perpendicular to the line of sight of the projectile is designed. Starting with the establishment of the dynamic equation between missiles and targets in the course of missile guidance, the equation of state based on the line-of-sight and the line-of-sight angular velocities is deduced. A sliding mode surface is established on which the visual line angle and the expected The difference between the terminal angle and the projectile line of sight angular velocity is zero. The Lyapunov function driving system is also introduced to achieve the designed sliding surface, and the expression of control acceleration is derived. The guidance law can meet the terminal angle requirements at the same time, can further increase missile speed. Finally, several simulation scenarios are constructed under the MATLAB environment, and the simulation results show the effectiveness of the guidance law.