This paper is concerned with the estimation of stability and control parameters of a high performance fighter aircraft from data obtained from high angle of attack flight. The estimation process utilizes a maximum likelihood algorithm derived for the case of a nonlinear aerodynamic force and moment model. The aircraft used was a high speed variable sweep heavy weight fighter with twin vertical tails. Comparisons of results from the nonlinear analysis are made with linear theory and wind tunnel results when available.
Estimation of nonlinear aerodynamic derivatives of a variable geometry fighter aircraft from flight data
Mechanics and Control of Flight Conference ; 1974 ; Anaheim, CA
1974-08-01
Conference paper
No indication
English