Abstract
A modified stepwise regression procedure employing several selection criteria used in the identification of an aircraft model structure from flight test data is presented. The aircraft equations of motion are evaluated in general form, expressing the force and moment coefficients as polynomials in state and control variables. Nonlinear aerodynamic parameters are represented by spline functions in one or two variables. Results from the analysis of both simulated and real flight test data utilising the regression algorithm are discussed briefly. The accuracy of the algorithm is first assessed using simulated flight data, then a real flight test case is analysed with a focus on estimating the nonlinear spoiler contribution. The resultant simulated response is compared with both the flight data and the response obtained through a linear maximum likelihood procedure
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