An extended Kalman filter algorithm for aerodynamic parameter identification from missile postflight data is developed and verified for realistic test conditions. The algorithm includes a general purpose six-degrees-of-freedom missile airframe model suitable for representing a variety of missile configurations. Verification studies consider low order linear aerodynamic models and higher order models with extensive nonlinear and pitch-yaw coupling effects. The sensitivity of filter performance to initial conditions, measurement data rate and accuracy, input selection, and modeling errors is investigated. A structure identification technique is used to select the most probable aerodynamic model for a given data set from a group of candidate models. In addition, actual flight test data from a complex aerodynamically controlled vehicle is processed with the filter algorithm. The resulting identified model is shown to be an improvement over the preflight model. (Author)


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    Title :

    Missile Aerodynamic Parameter and Structure Identification from Flight Test Data


    Contributors:
    J. E. Kain (author) / C. M. Brown (author) / J. G. Lee (author)

    Publication date :

    1977


    Size :

    203 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English