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首页> 外文会议>AIAA international space planes and hypersonic systems and technologies conference >Four-Loop Feedback Control System with Integrator Design for Hypersonic Cruise Missile
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Four-Loop Feedback Control System with Integrator Design for Hypersonic Cruise Missile

机译：高超音速巡航导弹集成设计的四回路反馈控制系统

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Hypersonic Cruise Missile (HCM) generally adopts the air-breathing scramjet engine as the propulsion, which needs strict conditions of the missile attitude. Considering the difficulties of accurate measurement of angle of attack (AOA), the overload feedback controller is presented to achieve precision of AOA. A four-loop autopilot with overload integral is proposed to track the overload command with zero steady stated error. Firstly, longitudinal dynamics of the HCM is modeled and linearized. Then, the model is augmented and the integrator is introduced into the overload control. The four-loop integral control system for the HCM is obtained from the LQR optimal control theory. Lastly, simulation results show that the designed control system achieves good performance tracking overload commands which guarantees the high precision of AOA for Scramjet during flight envelop.
机译：高超音速巡航导弹（HCM）通常采用空气呼吸超燃冲压发动机作为推进器，这需要对导弹姿态有严格的要求。考虑到精确测量迎角角度的困难，提出了过载反馈控制器以达到AOA精度。提出了一种带有过载积分的四环自动驾驶仪，用于跟踪稳态指令误差为零的过载指令。首先，对HCM的纵向动力学进行建模和线性化。然后，对模型进行扩充，并将积分器引入到过载控制中。 HCM的四环积分控制系统是从LQR最优控制理论获得的。最后，仿真结果表明，所设计的控制系统具有良好的跟踪过载指令性能，保证了超音速飞机在包络过程中AOA的高精度。

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