Robust Control Design for Pole Assignment of Uncertain Systems

1997 ◽  
Vol 119 (3) ◽  
pp. 588-590
Author(s):  
Wen-Hua Chen
Keyword(s):  
Dynamic Systems ◽  
Flight Control ◽  
Uncertain Systems ◽  
Optimization Problem ◽  
Control Design ◽  
Pole Assignment ◽  
Flight Control System ◽  
Convex Optimization Problem ◽  
Uncertain Dynamic Systems ◽  
Robust Control Design

This Technical Brief addresses the problem of robust pole assignment for uncertain dynamic systems. A control design methodology is proposed to determine a fixed controller assigning all poles of uncertain systems in a pre-specified disk. The robust pole assignment problem is reduced to a convex optimization problem. The proposed method is applied in design of a flight control system for a small aircraft successfully.

Segmented Wing Aircraft Lateral Directional Flight Control Design With Minimum Drag Constraints

2003 ◽  
Author(s):  
Frank R. Chavez ◽  
Jerry Vogel
Keyword(s):  
Flight Control ◽  
Current Trend ◽  
Control Design ◽  
Flight Control System ◽  
Biologically Inspired ◽  
Trailing Edge ◽  
Yaw Control ◽  
Aerodynamic Model ◽  
Minimum Drag ◽  
Yaw Moment

Following the current trend for developing biologically inspired flight configurations, flight control system for a transport type aircraft with no vertical tail and segmented main wing is to be developed. The transport configuration is inspired by the fact that birds do not have vertical tails and their wings have various trailing edge feathers that serve to form independent wing segments for roll and yaw control. An aerodynamic model for a generic transport aircraft, modeled after the Boeing 747, is obtained using NASA’s PMARC software. The aircraft is modeled with no vertical tail and the main wing has several independently controlled trailing edge segments. A flight control design will be carried out to satisfy roll and yaw moment commands. These moment commands might come from desired roll or yaw rate commands from the pilot. In addition, for increased performance, it is desirable to maintain a minimum drag configuration. This will result in a reduction in fuel usage for maximum range, endurance, or maximum flight speed. The final controller will provide main wing segment deflection commands designed to meet desired roll and yaw moment commands while attaining a minimum drag configuration.

Analytic Loop Shaping Methods in Quantitative Feedback Theory

1994 ◽  
Vol 116 (2) ◽  
pp. 169-177 ◽  
Author(s):  
D. F. Thompson ◽  
O. D. I. Nwokah
Keyword(s):  
Uncertain Systems ◽  
Closed Loop ◽  
Design Method ◽  
Control Design ◽  
Quantitative Feedback Theory ◽  
Single Input Single Output ◽  
Single Output ◽  
Direct Design ◽  
Single Input ◽  
Robust Control Design

Quantitative Feedback Theory (QFT), a robust control design method introduced by Horowitz, has been shown to be useful in many cases of multi-input, multi-output (MIMO) parametrically uncertain systems. Prominent is the capability for direct design to closed-loop frequency response specifications. In this paper, the theory and development of optimization-based algorithms for design of minimum-gain controllers is presented, including an illustrative example. Since MIMO QFT design is reduced to a series of equivalent single-input, single-output (SISO) designs, the emphasis is on the SISO case.

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