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构建了UH-60A直升机六自由度非定常、非线性气动力模型以及完整的直升机/涡轴发动机非线性综合仿真模型.使用增广LQR方法设计了直升机飞行控制器,包线内大量仿真结果及与H∞控制器效果的对比表明该控制器解耦性能、指令跟踪性能优越,鲁棒性强.此外,该控制器设计过程简单和调参方便.借助上述综合仿真模型研究了发动机闭环系统与直升机的功率匹配关系,数字仿真表明:发动机能够满足直升机机常规飞行任务下的功率需求,功率涡轮转速下垂量满足直升机飞行操纵品质规范(ADS-33E)的要求.
A six-DOF unsteady nonlinear aerodynamic model of UH-60A helicopter and a complete nonlinear simulation model of helicopter / turboshaft engine are constructed. The augmented LQR method is used to design a helicopter flight controller with a large number of simulation results in the envelope Compared with the H∞ controller, it shows that the controller has decoupling performance, excellent command tracking performance and robustness.In addition, the design process of the controller is simple and convenient.According to the comprehensive simulation model above, the closed-loop system and The simulation results show that the engine can meet the power requirements of the helicopter under normal flight tasks, and the power turbine rotor sag satisfies the requirements of the Helicopter Flight Operations Quality Specification (ADS-33E).