An integrated aircraft longitudinal flight control system uses a generalized thrust and elevator command computation (38), which accepts flight path angle, longitudinal acceleration command signals, along with associated feedback signals, to form energy rate error (20) and energy rate distribution error (18) signals. The engine thrust command is developed (22) as a function of the energy rate distribution error and the elevator position command is developed (26) as a function of the energy distribution error. For any vertical flight path and speed mode the outerloop errors are normalized (30, 34) to produce flight path angle and longitudinal acceleration commands. The system provides decoupled flight path and speed control for all control modes previously provided by the longitudinal autopilot, autothrottle and flight management systems.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Total energy based flight control system


    Contributors:

    Publication date :

    1985-08-20


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    Flight testing TECS - The Total Energy Control System

    Kelly, James R. / Person, Lee H., Jr. / Bruce, Kevin R. | NTRS | 1986


    Flight Testing TECS — The Total Energy Control System

    Kelly, James R. / Bruce, Kevin R. / Person, Lee H. | SAE Technical Papers | 1986


    NASA B737 flight test results of the Total Energy Control System

    Bruce, K. R. / Kelly, J. R. / Person, L. H., Jr. | NTRS | 1986


    Total Energy Control System for Helicopter Flight/Propulsion Integrated Controller Design

    Sheng-Wen Chen / Pang-Chia Chen / Ciann-Dong Yang et al. | AIAA | 2007