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研究了具有大离轴角及越肩发射能力的敏捷导弹初始段敏捷转弯的控制方法,用反作用喷气控制系统来提供大角度敏捷转弯时大攻角飞行的控制力矩。首先利用时标分离的思想将导弹姿态控制系统的运动学部分和动力学部分分别视为慢变子系统和快变子系统,然后应用动态逆和变结构控制相结合来设计各子系统的控制律;最后,在考虑了导弹各个环节非理想因素的情况下,对导弹进行全耦合状态下三通道联合仿真。仿真结果表明所提出的控制方法,能够有效消除敏捷导弹大角度姿态机动时的结构参数变化以及各种外部干扰的影响,可以很好地控制导弹的大迎角机动飞行,鲁棒性强,简单易行,具有一定的实用性。
The control method of agile turning in the initial stage of agile missile with large off-axis angle and over-shoulder launch capability is studied. The reaction torque control system is used to provide the control moment of large-angle agile turning at large angle of attack. First of all, using the idea of time-scale separation, the kinematics and dynamics of missile attitude control system are regarded as slow-moving subsystem and fast-changing subsystem respectively. Then, the control of each subsystem is designed by combining dynamic inverse and variable-structure control Finally, considering the non-ideal factors in all aspects of the missile, the three-channel joint simulation of the missile in full coupling state is carried out. The simulation results show that the proposed control method can effectively eliminate the influence of various external disturbances on the structural parameters of the agile missile during maneuvering at high angle and can control the maneuvering flight of the missile at high angles of attack with high robustness and simplicity Easy to operate, with some practicality.