Previous attempts to identify aircraft stability and control derivatives from flight test data, using three-degrees-of-freedom (3-DOF) longitudinal or lateral-directional perturbation equation-of-motion models, suffer from the disadvantage that the coupling between the longitudinal and lateral-directional dynamics has been ignored. In this paper, the identification of aircraft stability parameters is accomplished using a more accurate 6-DOF model which includes this coupling. Hierarchical system identification theory is used to reduce the computational effort involved. The 6-DOF system of equations is first decomposed into two 3-DOF subsystems, one for the longitudinal dynamics and the other for the lateral-directional dynamics. The two subsystem parameter identification processes are then coordinated in such a way that the overall system parameter identification problem is solved. Next, a six-subsystem decomposition is considered. Computational considerations and comparison with the unhierarchically structured problem are presented.


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    Title :

    Identification of Aircraft Stability and Control Parameters Using Hierarchical State Estimation


    Contributors:
    Fry, C.M. (author) / Sage, A.P. (author)

    Published in:

    Publication date :

    1974-03-01


    Size :

    3732282 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English