M. Tayefi, J. Roshanian, and M. Bahrami
Aerospace launch vehicle, system identification, six degrees of freedom simulation, Kalman filter
The transfer functions of the aerospace launch vehicle can be extracted using well-known linearization methodology. This paper presents an alternative to obtain the transfer functions via closed-loop identification using six degrees of freedom nonlinear simulation software. The vehicle is characterized by high nonlinearity, open loop instability and time-varying behaviours. The model structure with some unknown parameters is obtained after mathematical modeling, thus the case of our problem is a parameter identification one. Time-variant parameters are estimated by Kalman filter approach with the aid of ARX model structure.
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