Abstract
An optimization procedure, based on the aerodynamic energy concept, is applied to the problem of flutter suppression using trailing-edge (T.E.) and tab control surfaces. A control law is assumed which allows the T.E.-tab system to be driven by both linear and rotational sensors, and the optimum control law parameters are determined. Results are presented which indicate the capability of the T.E.-tab control system to suppress flutter. A comparison is also made between the T.E.-tab and the leading-edge (L.E.)-T.E. control systems which shows their relative effectiveness, together with some aspects connected to the realization of the control law.
| Original language | English |
|---|---|
| Pages (from-to) | 757-762 |
| Number of pages | 6 |
| Journal | AIAA Journal |
| Volume | 14 |
| Issue number | 6 |
| DOIs | |
| State | Published - Jun 1976 |
| Externally published | Yes |
Bibliographical note
Funding Information:Presented as Paper 75-822 at the AIAA/ASME/SAE 16thStruc-tures, Structural Dynamics, and Materials Conference, Denver, Colo., May 27-29, 1975; submitted July 23, 1975; revision received Dec. 31, 1975. This work is part of a study supported by NASA under Grant NSG-7072. Index category: Aeroelasticity and Hydroelasticity. *Associate Professor. Now NRC-NASA Resident Research Associate, NASA Langley Research Center, Hampton, Va. Member AIAA.