The fault-tolerant actuation system uses 4 active electrical control paths to control a dualized hydraulic actuator. A simple failure management system operates in conjunction with some of the inherent features of the basic system to provide a failure tolerance level of dual fail-operate for the electrical control paths. The concept is characterized by its fundamental simplicity and inherent ability to tolerate failures. The concept has application to fixed wing as well as rotary wing aircraft. (Author)
Fault-Tolerant Actuation Concept for a Research Test Aircraft
1980
103 pages
Report
No indication
English
Hydraulic & Pneumatic Equipment , Aircraft , Hydraulic actuators , Electrohydraulic valves , Faults , Redundant components , Failure , Management , Servovalves , Hydraulic servomechanisms , Flight control systems , Automatic , Circuits , Dual mode , Research aircraft , Fly by wire control , Power supplies , Electric power , Hydraulic power , Helicopters , Fixed wing aircraft , Manual operation , Fault tolerant actuators , EHSV(ElectroHydraulic ServoValves)
FAULT TOLERANT ELECTRONIC CONTROL ARCHITECTURE FOR AIRCRAFT ACTUATION SYSTEM
European Patent Office | 2016
|FAULT TOLERANT ELECTRONIC CONTROL ARCHITECTURE FOR AIRCRAFT ACTUATION SYSTEM
European Patent Office | 2016
|Fault tolerant electronic control architecture for aircraft actuation system
European Patent Office | 2018
|Digital fault tolerant flight actuation systems
Tema Archive | 1985
|FAULT TOLERANT INDIVIDUAL BLADE ACTUATION SYSTEM
British Library Conference Proceedings | 2021
|