Abstract:
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.