A preliminary theoretical investigation has been made of the short-period longitudinal and steady-rolling (inertia coupling) stability of a hypersonic glider configuration for center-of-gravity locations rear-ward of the airplane neutral point. Such center-of-gravity positions for subsonic flight would improve performance by reducing supersonic and hypersonic static margins and trim drag. Results are presented of stability calculations and a simulator study for a velocity of 700 ft/sec and an altitude of 401,000 feet. With no augmentation, the airplane was rapidly divergent and was considered unsatisfactory in the simulator study. When a pitch damper was employed as a stability augmenter, the short-period mode became overdamped, and the airplane was easily controlled on the simulator. A steady-rolling analysis showed that the airplane can be made free of rolling divergence for all roll rates with an appropriate damper gain.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Effect of Artificial Pitch Damping on the Longitudinal and Rolling Stability of Aircraft with Negative Static Margins


    Beteiligte:
    M. T. Moul (Autor:in) / L. W. Brown (Autor:in)

    Erscheinungsdatum :

    1959


    Format / Umfang :

    26 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch








    Static and Dynamic Pitch Stability of Outboard-Horizontal-Stabilizer Aircraft

    Kentfield, J. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2009