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Diagnostics for Electrohydraulic Primary Flight Control Servoactuators
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English
Abstract
Primary, fly-by-wire, flight control servoactuators are complex components. They are incorporated into systems with many elements which interact to make correct failure diagnosis difficult. However, the power of the microprocessor has been enlisted to aid the experience the industry is building with test technique and sensor application. This paper examines on-aircraft diagnostic technique and includes as background the impact of the architecture chosen. It lists the types of failure covered, describes the way in which the techniques used in primary flight control servoactuators have evolved to become more electronic and less hydromechanical and concludes with some “lessons-learned”,
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Authors
Citation
Flavell, D., "Diagnostics for Electrohydraulic Primary Flight Control Servoactuators," SAE Technical Paper 932630, 1993, https://doi.org/10.4271/932630.Also In
References
- “Flight Control Actuation System for the B-2 Advanced Technology Bomber” Schaefer Inderhees Moynes April 1991 SAE Paper # 911112
- “Redundant Electrohydraulic Servoactuators” Thayer W.J. May 1976 Moog Technical Bulletin # 127
- “FBW Actuation System Descriptions” SAE AIR # 4253
- “Flight Control Servoactuators for the U.S. Space Shuttle” Thayer W.J. Sept 1977 Moog Tecchnical Bulletin # 100
- “LAVI Primary Flight Control Actuation” Flavell D.J. October 1988 Moog Technical Bulletin #152
- “V-22 Flight Control System” Mcmanus Bruce L. April 17, 1985 Bell-Boeing SAE A-6