Results of a predevelopment program for Fly by Wire (FBW) flight control systems in civil aircraft are presented. The concept is based on requirements for certification of safety-critical functions, capacity of the computer systems to implement active control function (gust load alleviation, variable camber wing control etc) and a cockpit standard with mini-stick and digital display and operation systems. The experimental system consists of a quad-redundant, fault-tolerant multicomputer system and a quadruplex Actuator Electronic Unit (AEU) providing the redundancy management and force synchronization of parallel-active electrohydraulic servoactuators. The computer-interlane communication is by fiber optics. By A300/310 flight simulator-investigations the control laws with command and flight envelope protections are validated. The experimental system was tested in a rig with aircraft-simulation in the loop. The control and redundancy management-concept for the AEU's and parallel-redundant actuator configurations are verified by test results.
Electrical Primary Flight Control System (Fly by Wire). Flight Control Systems of New Technology
1988
202 pages
Report
Keine Angabe
Englisch
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