| 非定常条件下大迎角机动控制 |
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| 引用本文： | 叶辉,吴庆宪,陈谋. 非定常条件下大迎角机动控制[J]. 哈尔滨工业大学学报, 2016, 48(4): 84-90 |
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| 作者姓名： | 叶辉 吴庆宪 陈谋 |
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| 作者单位： | 南京航空航天大学 自动化学院, 210016 南京 ;江苏省物联网与控制技术重点实验室南京航空航天大学, 210016 南京,南京航空航天大学 自动化学院, 210016 南京 ;江苏省物联网与控制技术重点实验室南京航空航天大学, 210016 南京,南京航空航天大学 自动化学院, 210016 南京 ;江苏省物联网与控制技术重点实验室南京航空航天大学, 210016 南京 |
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| 基金项目： | 国家自然科学基金(2,2)；江苏省自然科学基金(SBK20130033). |
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| 摘 要： | 针对推力矢量飞机在非定常气动影响下的机动控制问题,提出一种大迎角俯仰机动的控制器设计方案.采用干扰观测器方法对机动过程中的非定常俯仰力和力矩进行估计,并在控制端进行俯仰力矩补偿以及适当的升力补偿,建立了统一参数下飞机线性参变(LPV)模型和外部干扰LPV模型,并基于LPV模型设计了标称控制器和干扰观测器.从大迎角机动仿真中可以看出,控制系统能够控制迎角较好地跟踪输入指令,同时对机动过程中存在的非定常干扰能进行有效地抑制.仿真结果表明利用干扰观测器的方法较其他方法具有更好的控制性能.
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| 关 键 词： | 机动飞行控制 大迎角 非定常气动力 干扰观测器 线性参变系统 |
| 收稿时间： | 2014-12-25 |
Control of high angle of attack maneuver under unsteady aerodynamic condition |
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| YE Hui,WU Qingxian and CHEN Mou. Control of high angle of attack maneuver under unsteady aerodynamic condition[J]. Journal of Harbin Institute of Technology, 2016, 48(4): 84-90 |
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| Authors: | YE Hui WU Qingxian CHEN Mou |
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| Affiliation: | College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, 210016 Nanjing, China ;Jiangsu Key Laboratory of Internet of Things and Control TechnologiesNanjing University of Aeronautics and Astronautics, 210016 Nanjing, China,College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, 210016 Nanjing, China ;Jiangsu Key Laboratory of Internet of Things and Control TechnologiesNanjing University of Aeronautics and Astronautics, 210016 Nanjing, China and College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, 210016 Nanjing, China ;Jiangsu Key Laboratory of Internet of Things and Control TechnologiesNanjing University of Aeronautics and Astronautics, 210016 Nanjing, China |
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| Abstract: | This paper presents a flight control scheme for the aircraft with thrust vectoring to perform the pitch maneuver at high angle of attack under unsteady aerodynamic condition. The scheme employs a disturbance observer to estimate the unsteady aerodynamic disturbances emerging in maneuvers. Complete pitching moment compensation and proper lift amendment are added to the control signals. In order to design the nominal controller and the disturbance observer, linear parameter varying (LPV) models of the aircraft and external disturbances with identical scheduling parameters are established. Maneuvers simulations show that the proposed method has excellent track to the command and effective rejection to the unsteady aerodynamic disturbance. |
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| Keywords: | maneuver control high angle of attack unsteady aerodynamics disturbance observer linear parameter varying system |
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