| 电传飞行控制作动系统 |
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| 引用本文： | 张冰凌,张勇.电传飞行控制作动系统[J].飞机设计,2007,27(4):53-60. |
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| 作者姓名： | 张冰凌 张勇 |
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| 作者单位： | 1. 海军驻沈阳地区航空军事代表室,辽宁,沈阳,110035
2. 沈阳飞机设计研究所,辽宁,沈阳,110035 |
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| 摘 要： | YF-23A战斗机具有极大的静不安定性,在不开加力的情况下可以实现超声速巡航,其设计目标是在亚声速和超声速均具有优于对手的机动能力,上述要求使得飞行控制作动系统必须具有空前的能力和性能。其独特的飞行和机动包线要求其作动系统在低速时具有高的舵面偏转速率和大的行程,在超声速时要具有附加铰链力矩输出能力,为实现上述目标,开发出具有液压与电能守恒的作动系统。
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| 关 键 词： | 作动器 直接驱动阀 变面积作动 飞行控制 |
| 文章编号： | 1673-4599（2007）04-0053-08 |
| 收稿时间： | 2006-12-25 |
| 修稿时间： | 2006-12-252007-06-28 |
Fly-By-Wire Flight Control Actuation System for High Performance Fighter |
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| ZHANG Bing-ling,ZHANG Yong.Fly-By-Wire Flight Control Actuation System for High Performance Fighter[J].Aircraft Design,2007,27(4):53-60. |
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| Authors: | ZHANG Bing-ling ZHANG Yong |
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| Abstract: | The YF-23A Fighter was a revolutionary statically unstable aircraft that cruised at supersonic speeds without afterburner and was designed to outmaneuver opponents at subsonic and supersonic speeds.Combining these demanded a flight control actuation system of unprecedented power and performance.Its unique flight and maneuvering envelop required high surface rate and large actuator excursion at low flight speeds,as well as the power to generate increased hinge moments at supersonic speeds.To achieve these specifications,hydraulic flow and electrical power conservation techniques was utilized. |
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| Keywords: | actuator direct drive valve variable area actuation flight control |
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