Actions for Performance of an Electro-Hydrostatic Actuator on the F-18 Systems Research Aircraft

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Performance of an Electro-Hydrostatic Actuator on the F-18 Systems Research Aircraft

Author
Navarro, Robert
Published
Oct. 1997.
Physical Description
1 electronic document
Online Version

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Summary
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.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19970034702.
Accession ID: 97N29943.
H-2210.
NAS 1.15:206224.
NASA/TM-97-206224.
Digital Avionics Systems; 26-30 Oct. 1997; Irvine, CA; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15647214