Linearized equations of motion of rolling bisymmetric aircraft formulated, using body axes; it is shown that (a) rate of change of angle of attack is vector, (b) linearized form of downwash lag terms is valid only if downwash-roll angle be small, and (c) such linearized form must use vector relations of (a); as result, stability criteria are derived independent of rolling of reference axis system.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Response of bisymmetric aircraft to small combined pitch, yaw, and roll control actions


    Weitere Titelangaben:

    J Aeronautical Sciences


    Beteiligte:
    Davis, R.A. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1957


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    OPTIMIZED PITCH AND ROLL CONTROL APPARATUS FOR AN AIRCRAFT

    ELLIOTT JOSEPH E / SONES ANDREW / STANDLEY JOHN | Europäisches Patentamt | 2021

    Freier Zugriff

    OPTIMIZED PITCH AND ROLL CONTROL APPARATUS FOR AN AIRCRAFT

    ELLIOTT JOSEPH E / SONES ANDREW / STANDLEY JOHN | Europäisches Patentamt | 2018

    Freier Zugriff

    OPTIMIZED PITCH AND ROLL CONTROL APPARATUS FOR AN AIRCRAFT

    ELLIOTT JOSEPH E / SONES ANDREW / STANDLEY JOHN | Europäisches Patentamt | 2020

    Freier Zugriff

    Optimized pitch and roll control apparatus for an aircraft

    ELLIOTT JOSEPH E / SONES ANDREW / STANDLEY JOHN | Europäisches Patentamt | 2019

    Freier Zugriff

    Control Mapping Methodology for Roll, Pitch, and Yaw Control on Morphing-Wing Aircraft

    Montgomery, Zachary S. / Hunsaker, Douglas F. | AIAA | 2022