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Performance of an Electro-Hydrostatic Actuator on the F-18 Systems Research AircraftAn 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.
Document ID
19970034702
Acquisition Source
Armstrong Flight Research Center
Document Type
Technical Memorandum (TM)
Authors
Robert Navarro (Armstrong Flight Research Center Rosamond, California, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1997
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA/TM-97-206224
H-2210
NAS 1.15:206224
Meeting Information
Meeting: 16th Digital Avionics Systems Conference
Location: Irvine, CA
Country: US
Start Date: October 26, 1997
End Date: October 30, 1997
Accession Number
97N29943
Funding Number(s)
PROJECT: RTOP 529-31-14-00-36
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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