Regression techniques for aircraft parameter identification from noisy measurements in maneuvering flight

Author

Chandler, P. ; Pachter, M. ; Mears, M. ; Sheldon, S.

Author_Institution

Flight Dynamics Lab., Wright-Patterson AFB, OH, USA

fYear

1992

fDate

1992

Firstpage

2311

Abstract

System identification for reconfigurable flight control is proposed. System identification using using linear regression where the highest derivatives are measured is analyzed. Knowledge of the stability and control derivatives is incorporated into the linear regression algorithm through ridge regression and mixed estimation methods. The example problem is a linearized fourth-order model of the F-16 pitch channel, and includes appropriate measurement (sensor) noise. The results show that even during periods of low excitation, the short period parameter estimates are improved by utilizing prior Phugoid information

Keywords

aircraft control; parameter estimation; stability; statistical analysis; F-16; aircraft; control derivatives; flight control; linear regression; linearized fourth-order model; parameter identification; pitch channel; prior Phugoid information; stability; Aerospace control; Aircraft; Laboratories; Linear regression; Noise measurement; Nonlinear equations; Parameter estimation; Stability; System identification; Taylor series; Testing;

fLanguage

English

Publisher

ieee

Conference_Titel

Decision and Control, 1992., Proceedings of the 31st IEEE Conference on

Conference_Location

Tucson, AZ

Print_ISBN

0-7803-0872-7

Type

conf

DOI

10.1109/CDC.1992.371379

Filename

371379