A discussion is presented of fly-by-wire flight control systems in which vehicle motion is the controlled parameter. Electrical signal transmission is employed from the pilot's station to the electrohydraulic servomechanism. An experimental laboratory model fly-by-wire control system is designed, constructed, tested, and evaluated for performance to demonstrate the feasibility and capability of the fly-by-wire system. Aircraft analysis of the B-47 is made to determine the artificial feel requirements for this application. Reliability calculations and failure mode analysis are discussed. Peripheral equipment required (such as a side arm controller, preflight automatic self-test equipment, and the pilot's control panel) is designed, constructed, and described. (Author)
A Prototype Fly-by-Wire Flight Control System
1969
189 pages
Report
Keine Angabe
Englisch
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