Normal acceleration command following of the F-16 using optimal control methodologies: a comparison

Author

Mracek, C.P. ; Ridgeley, D.B.

Author_Institution

Dept. of Aeronaut. & Astronaut., Air Force Inst. of Technol., Wright-Patterson AFB, OH

fYear

1992

Firstpage

602

Abstract

Three types of control design method are compared for tracking performance and robustness. The three types are H₂, H_∞, and mixed H₂/H_∞. The tracking problem is a command-following system subject to noises and uncertainties. The plant model is unstable and non-minimum-phase. Specifically, an F-16 is modeled at Mach 0.6, sea level, with normal acceleration being measured and commanded. The best tracking performance is obtained by only looking at the tracking problem with plant uncertainties and using H_∞ optimization. The best noise suppression is obtained by considering only the noise and using H₂ optimization

Keywords

aircraft control; control system synthesis; military systems; optimal control; optimisation; stability; tracking; F-16 fighter aircraft; H_∞ optimization; H₂ optimization; aircraft control; command-following system; control design; normal acceleration; optimal control; robustness; tracking; uncertainties; Acceleration; Accelerometers; Aircraft; Control design; Delay effects; Elevators; Equations; Optimal control; Sea level; Servomechanisms;

fLanguage

English

Publisher

ieee

Conference_Titel

Control Applications, 1992., First IEEE Conference on

Conference_Location

Dayton, OH

Print_ISBN

0-7803-0047-5

Type

conf

DOI

10.1109/CCA.1992.269781

Filename

269781