An account is given of flight control system performance results for the X-29A forward-swept wing 'Advanced Technology Demonstrator' fighter aircraft, with attention to its software and hardware components' achievement of the requisite levels of system stability and desirable aircraft handling qualities. The Automatic Camber Control Logic is found to be well integrated with the stability loop of the aircraft. A number of flight test support software programs developed by NASA facilitated monitoring of the X-29A's stability in real time, and allowed the test team to clear the envelope with confidence.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    X-29A flight control system performance during flight test


    Contributors:
    Chin, J. (author) / Chacon, V. (author) / Gera, J. (author)

    Publication date :

    1987-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    X-29A flight control system performance during flight test

    CHIN, J. / CHACON, V. / GERA, J. | AIAA | 1987


    X-29.A flight control system performance during flight test

    Chin, J. / Chacon, V. / Gera, J. | Tema Archive | 1987


    Gemini flight control system performance during second unmanned flight

    Hanaway, J.F. / Carley, R.R. / Vernon, J.A. | Engineering Index Backfile | 1965


    Gemini flight control system performance during the second unmanned flight.

    Carley, R. R. / Hanaway, J. F. / Vernon, J. A. | NTRS | 1965


    Gemini Flight Control System Performance during the Second Unmanned Flight

    Vernon, J. A. / Hanaway, John F. / Carley, R. R. | SAE Technical Papers | 1965