| 基于直升机/发动机非线性综合仿真模型的增广LQR控制器设计 |
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| 引用本文： | 孙立国,孙健国,张海波,王健康.基于直升机/发动机非线性综合仿真模型的增广LQR控制器设计[J].航空动力学报,2010,25(2):471-476. |
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| 作者姓名： | 孙立国 孙健国 张海波 王健康 |
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| 作者单位： | 南京航空航天大学,能源与动力学院,南京,210016 |
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| 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.
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| 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 |
| 收稿时间： | 2009/1/17 0:00:00 |
| 修稿时间： | 2009/6/15 0:00:00 |
Augmented linear quadratic regulator controller design based on non-linear integrated helicopter/engine model |
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| SUN Li-guo,SUN Jian-guo,ZHANG Hai-bo and WANG Jian-kang.Augmented linear quadratic regulator controller design based on non-linear integrated helicopter/engine model[J].Journal of Aerospace Power,2010,25(2):471-476. |
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| Authors: | SUN Li-guo SUN Jian-guo ZHANG Hai-bo and WANG Jian-kang |
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| Affiliation: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | The unsteady and non-linear helicopter model of UH-60A was established, while the non-linear integrated helicopter/engine model was also constructed. Then, an aug-mented linear quadratic regulator (ALQR) method for the flight controller was designed. Simulative experiments on the integrated helicopter/engine model were conducted. Numeri-cal simulation results and the comparison with H_∞ controller demonstrate that the ALQR flight controller had its superiority of decoupling, command tracking and robustness. In ad-dition, 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 require-ment of ADS-33E. |
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| Keywords: | integrated helicopter/engine model flight controller augmented linear quadratic regulator (ALQR) deeoupling robustness |
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