Analysis of aircraft pitch axis stability augmentation system using sum of squares optimization

Author

Krishnaswamy, Kailash ; Papageorgiou, George ; GlavaSki, Sonja ; Papachristodoulou, Antonis

Author_Institution

Honeywell Labs., Minneapolis, MN, USA

fYear

2005

fDate

8-10 June 2005

Firstpage

1497

Abstract

In this paper, we use SOS (sum of squares) programming approaches to analyze the stability and robustness properties of the controlled pitch axis (6 state system) of a nonlinear model of an aircraft. The controller is a LTI dynamic inversion based control law designed for the short period dynamics of the aircraft. The closed loop system is tested for its robustness to uncertainty in the location of center of gravity along the body x-axis. Results in the form of stability regions about a trim point are computed and verified using simulations.

Keywords

aircraft control; closed loop systems; control system analysis; nonlinear control systems; stability; LTI dynamic inversion; aircraft pitch axis stability augmentation system; closed loop system; nonlinear model; sum of squares optimization; sum of squares programming; Aerospace control; Aircraft; Closed loop systems; Nonlinear control systems; Nonlinear dynamical systems; Robust control; Robust stability; Robustness; Stability analysis; System testing;

fLanguage

English

Publisher

ieee

Conference_Titel

American Control Conference, 2005. Proceedings of the 2005

ISSN

0743-1619

Print_ISBN

0-7803-9098-9

Electronic_ISBN

0743-1619

Type

conf

DOI

10.1109/ACC.2005.1470177

Filename

1470177