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针对末攻击段飞行器快速响应及突防的要求,研究了飞行器基于块对角控制理论的制导控制一体化设计方法。通过分析飞行器与目标的相对运动关系,建立了弹目相对运动方程;结合飞行器自身姿态层方程及角速度方程所具有的块对角结构,建立了制导控制一体化块对角模型;针对该模型中各子系统的结构特点,分别采用解析逆方法求解相对运动层方程、滑模控制方法求解姿态层和角速度层方程;采用模糊控制方法逼近系统矩阵和增益矩阵,构成块对角组合控制算法。最后,通过仿真验证了方法的有效性。
In order to meet the requirements of rapid response and penetration of final attack aircraft, the integrated design method of guidance control based on block diagonal control theory is studied. Based on the analysis of the relative motion between the aircraft and the target, the relative motion equations of the projectile are established. Based on the self-attitude equation of the aircraft and the diagonal structure of the angular velocity equation, a guidance and control integrated block diagonal model is established. The structural characteristics of each subsystem are solved by using the analytical inverse method to solve the equations of relative motion. The sliding mode control method is used to solve the attitude layer and the angular velocity layer equations. The fuzzy control method is used to approximate the system matrix and gain matrix to form the block diagonal combination control algorithm. Finally, the effectiveness of the method is verified by simulation.