摘要
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.
The while the non-linear unsteady and non-linear helicopter model of UH-60A was established, integrated helicopter/engine model was also constructed. Then, an augmented linear quadratic regulator （ALQR） method for the flight controller was designed. Simulative experiments on the integrated helicopter/engine model were conducted. Numerical simulation results and the comparison with H∞ controller demonstrate that the ALQR flight controller had its superiority of decoupling, command tracking and robustness. In addition, it was also found that the closed-loop system of engine could satisfy the need of power required by the helicopter in usual task, and the power turbine speed could meet the requirement of ADS-33E.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第2期471-476,共6页
Journal of Aerospace Power
基金
航空支撑科技基金(04B52006)
关键词
直升机/发动机综合仿真模型
飞行控制
增广LQR方法
解耦性
鲁棒性
integrated helicopter/engine model
flight controller
augmented linear quadratic regulator （ALQR）
decoupling
robustness
