Performance of an Electro-Hydrostatic Actuator on the F-18 Systems Research Aircraft
Performance of an Electro-Hydrostatic Actuator on the F-18 Systems Research Aircraft
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发表时间：
1997-10
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通讯作者：
R. Navarro
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作者：
R. Navarro
在位于加州爱德华兹的NASA德莱登飞行研究中心对一种电动静液压作动器进行了评价。测试该作动器系统的主要目的是在主飞行控制面上进行电传技术的飞行演示。电动静液压致动器使用电动机来驱动液压泵，并依赖于局部液压系统进行力传递。该作动器取代了F-18系统研究飞机上的F-18标准左副翼作动器，并在整个系统研究飞机飞行包线内进行了评估。截至1997年7月24日，电动静液压作动器已累计飞行23.5小时。本文介绍了电动静液压作动器系统的配置和部件说明、地面和飞行试验计划、地面和飞行试验结果以及经验教训。该作动器的性能与标准作动器一样好，并且具有比位于密苏里州圣路易斯的McDonnell-道格拉斯飞机公司的副翼作动器规范所要求的更大的负载能力。电动静液压作动器系统通过了所有的地面试验，除了在空载动态循环期间的一次断电试验。
An electro-hydrostatic actuator was evaluated at NASA Dryden Flight Research Center, Edwards, California. The primary goal of testing this actuator system was the flight demonstration of power-by-wire technology on a primary flight control surface. The electro-hydrostatic actuator uses an electric motor to drive a hydraulic pump and relies on local hydraulics for force transmission. This actuator replaced the F-18 standard left aileron actuator on the F-18 Systems Research Aircraft and was evaluated throughout the Systems Research Aircraft flight envelope. As of July 24, 1997 the electro-hydrostatic actuator had accumulated 23.5 hours of flight time. This paper presents the electro-hydrostatic actuator system configuration and component description, ground and flight test plans, ground and flight test results, and lessons learned. This actuator performs as well as the standard actuator and has more load capability than required by aileron actuator specifications of McDonnell- Douglas Aircraft, St. Louis, Missouri. The electro-hydrostatic actuator system passed all of its ground tests with the exception of one power-off test during unloaded dynamic cycling.