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)


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    FAULT TOLERANT ELECTRONIC CONTROL ARCHITECTURE FOR AIRCRAFT ACTUATION SYSTEM

    NEELY JOHN DAVID / SEELY STANLEY LAWRENCE / WHITE JOHN MENDENHALL | European Patent Office | 2016

    Free access

    FAULT TOLERANT ELECTRONIC CONTROL ARCHITECTURE FOR AIRCRAFT ACTUATION SYSTEM

    NEELY JOHN DAVID / SEELY STANLEY LAWRENCE / WHITE JOHN MENDENHALL | European Patent Office | 2016

    Free access

    Fault tolerant electronic control architecture for aircraft actuation system

    NEELY JOHN DAVID / SEELY STANLEY LAWRENCE / WHITE JOHN MENDENHALL | European Patent Office | 2018

    Free access

    Digital fault tolerant flight actuation systems

    Belmont, H.H. | Tema Archive | 1985


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    Kopp, J. | British Library Conference Proceedings | 2021