Most light aircraft accidents occur during landing and takeoff because at these times the pilot must operate controls frequently and precisely and with more than average force. These operations are further complicated by the nose-high attitude of the aircraft, which interferes with a normal visual control reference. The purpose of the studies reported here was to design an aircraft that would fly at zero pitch angle and would require a minimum of pilot commands for satisfactory operation. Preliminary investigation showed that it would be possible to modify an existing airplane by providing a three-component control system, new wing with Fowler flaps for lift modulation, and additional longitudinal control power. The details of these modifications are described fully in this paper.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    A Flight Control System Providing A Simple-to-Fly, Constant Attitude Aircraft


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:

    Kongress:

    National Business Aircraft Meeting and Engineering Display ; 1971



    Erscheinungsdatum :

    1971-02-01




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch





    AIRCRAFT FLIGHT ATTITUDE DISPLAY DEVICE

    LIN HUNG-HSIN | Europäisches Patentamt | 2022

    Freier Zugriff

    AIRCRAFT FLIGHT ATTITUDE DISPLAY DEVICE

    LIN HUNG-HSIN | Europäisches Patentamt | 2020

    Freier Zugriff

    A design study for a simple-to-fly, constant attitude light aircraft

    Smetana, F. O. / Humphreys, D. E. / Montoya, R. J. et al. | NTRS | 1973


    A Design Study for a Simple-TO-Fly, Constant Attitude Light Aircraft

    F. O. Smetana / D. E. Humphreys / R. J. Montoya et al. | NTIS | 1973