Flight test design for efficient extraction of aircraft parametersThis paper considers the design of flight control inputs which result in a minimization of the nonuniqueness problem of parameter identification due to statistical correlation. The performance index for the control design is taken as a linear weighted sum of the squares of the correlation coefficients of the aerodynamic stability and control derivatives as computed from the Cramer-Rao lower bound matrix. An optimal input design is demonstrated for an F-8 aircraft with supercritical wing. Reduced correlations are noted and corresponding estimates and confidence levels presented.
Document ID
19760053946
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Wells, W. R. (Cincinnati Univ. OH, United States)
Ramachandran, S. (Cincinnati, University Cincinnati, Ohio, United States)