The current roll maneuver to the flight azimuth following lift-off is achieved by commanding roll attitude using a linear profile with no roll rate command. The linearity of this command profile implies an infinite acceleration to a constant roll rate; the vehicle cannot instantaneously achieve this rate, so the actual roll attitude lags the command attitude throughout the maneuver. The roll attitude error which thus develops can be reduced by augmenting the attitude command with a rate command and utilizing finite slopes on the rate command to give the vehicle time to accelerate. Results obtained from commanding various roll attitude and rate combinations to perform the maneuver are presented. (Author)


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Roll Maneuver Evaluation


    Beteiligte:
    W. W. Webb (Autor:in)

    Erscheinungsdatum :

    1975


    Format / Umfang :

    22 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Roll maneuver evaluation

    Webb, W. W. | NTRS | 1975


    Rotorcraft Pitch-Roll Decoupling Requirements from a Roll Tracking Maneuver

    Blanken, C. L. / Ockier, C. J. / Simmons, R. C. et al. | British Library Conference Proceedings | 1994


    Rotorcraft pitch-roll decoupling requirements from a roll tracking maneuver

    Blanken, C.L. / Ockier, C.J. / Pausder, H.J. et al. | Tema Archiv | 1997



    Flexible Composite Wing with Internal Actuation for Roll Maneuver

    Khot, N.S. / Zweber, J.V. / Veley, D.E. et al. | British Library Conference Proceedings | 2000