Parameter identification applied to aircraft

All three steps in the identification, namely characterization parameter estimation and verification are considered and applied to the determination of aircraft parameters from flight data. The estimation procedure includes the equation error method and the output error method with the weighted least squares, maximum likelihood and Bayesian estimation technique. The problems concerning accuracy and identifiability are also discussed. A general computing algorithm is developed covering all estimation * techniques described. It is applicable to linear as well as nonlinear systems and is flexible enough for the solution of various identifiability problems. Using this algorithm the computing program has been compiled in general terms to enable the user to achieve the objectives mentioned. â R ' As examples, the results of the identification of aircraft parameters and aerodynamic derivatives for four different aircraft are presented. They include the analysis of flight data from the Basset variable stability aircraft and from the M.S. 760 Paris aircraft, the simulated data for a nonlinear model of the F-100 aircraft, and the flight data from the longitudinal motion of the HP-115 slender delta flowing research aircraft. The report is completed by the recommendation for future work in the area of aircraft parameter identification.