| 保持飞行迎角恒定的飞行/推力综合控制 |
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| 引用本文： | 杨一栋,江驹.保持飞行迎角恒定的飞行/推力综合控制[J].航空学报,1996,17(4):460-464. |
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| 作者姓名： | 杨一栋 江驹 |
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| 作者单位： | 南京航空航天大学三系,南京,210016 |
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| 摘 要： | 迎角恒定的飞行 /推力综合控制能明显地改善飞机机动能力 ,使飞行轨迹对姿态有快速精确响应。论述了具有迎角恒定动力补偿系统的工作原理 ,研究其控制规律及设计方法 ,并与速度恒定的动力补偿系统进行比较。以舰载飞机自动进近着舰系统的动力补偿为例 ,给出了仿真验证的结果。
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| 关 键 词： | |
| 收稿时间： | 1993-10-25; |
| 修稿时间： | 1995-10-06 |
INTEGRATED FLIGHT/THRUST CONTROL SYSTEM WITH CONSTANT ANGLE OF ATTACK |
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| Yang Yidong,Jiang Ju.INTEGRATED FLIGHT/THRUST CONTROL SYSTEM WITH CONSTANT ANGLE OF ATTACK[J].Acta Aeronautica et Astronautica Sinica,1996,17(4):460-464. |
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| Authors: | Yang Yidong Jiang Ju |
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| Institution: | Dept.of Automation, Nanjing University of Aeronautics and Astronautics, Nanjing,210016 |
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| Abstract: | The integrated flight/thrust control system with constant angle of attack can significantly improve the aircraft maneuverability. It will enable the flight path to respond to the change of attitude speedily and accurately. This paper is to state the philosophy of approach power compensator system (APCS) with constant angle of attack, study its control law and present briefly the design method of parameters. Also evaluated is its performance by comparing it with APCS at constant air speed. The numerical simulation of the APCS for the automatic carrier landing system shows that the analysis presented by this paper is feasible. |
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| Keywords: | integrated flight/thrust control constant angle of attack power compensation control law |
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