Design of Control Laws for Flutter Suppression Based on the Aerodynamic Energy Concept and Comparisons With Other Design Methods
Nissim, E. (1990) Design of Control Laws for Flutter Suppression Based on the Aerodynamic Energy Concept and Comparisons With Other Design Methods. Technical Report NASA TP-3056, Research Engineering, NASA Dryden Flight Research Center.
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Abstract
The aerodynamic energy method is used to synthesize control laws for NASA's drone for aerodynamic and structural testing-aerodynamic research wing 1 (DAST-ARW1) mathematical model. The performance of these control laws in terms of closed-loop flutter dynamic pressure, control surface activity, and robustness is compared with other control laws that appear in the literature and that relate to the same model. A control law synthesis technique that makes use of the return difference singular values is developed in the present work. It is based on the aerodynamic energy approach and is shown to yield results that are superior to those results given in the literature and are based on optimal control theory. Nyquist plots are presented, together with a short discussion regarding the relative merits of the minimum singular value as a measure of robustness as compared with the more traditional measure involving phase and gain margins.
| EPrint Type: | NASA Technical Publication |
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| Keywords: | Active controls, Aeroservoelasticity, Flutter suppression |
| Subjects: | Aircraft/Project: DAST (31 - 39) Engineering: (39) Structural Mechanics |
| ID Code: | 343 |
| Deposited On: | 23 August 2004 |
| Additional Information: | 59 pages. This research was undertaken while Eli Nissim held a National Research Council–NASA (Ames Research Center, Dryden Flight Research Facility) Research Associateship. The author was on leave from Technion–Israel Institute of Technology. A part of this report was presented as AIAA-89-1212. |
