The application of system identification methods to high-bandwidth rotorcraft flight control system design is examined. Flight test and modeling requirements are illustrated using flight test data from a BO-105 hingeless rotor helicopter. The proposed approach involves the identification of nonparametric (transfer function and state space) model identification. Results for the BO-105 show the need for including coupled body/rotor flapping and lead-lag dynamics in the identification model structure to allow the accurate prediction of control ssytem bandwidth limitations.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    System identification requirements for high-bandwidth rotorcraft flight control system design


    Contributors:

    Conference:

    1991 American Control Conference ; 1991 ; Boston, MA, United States


    Publication date :

    1991-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    System identification requirements for high-bandwidth rotorcraft flight control system design

    TISCHLER, MARK B. / U.S. Army / Aeroflightdynamics Directorate et al. | AIAA | 1990



    Flight requirements for operation of rotorcraft

    Scanlon, J. | Engineering Index Backfile | 1963



    Towards an Advanced Nonlinear Rotorcraft Flight Control System Design

    Njaka, C. E. / Cheng, V. H. L. / Menon, P. K. et al. | British Library Conference Proceedings | 1994