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Status of two studies on active control of aeroelastic response
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Sandford, M. C. Abel, I. |
| Copyright Year | 1973 |
| Description | The application of active control technology to the suppression of flutter has been successfully demonstrated during two recent studies in the Langley transonic dynamics tunnel. The first study involved the implementation of an aerodynamic-energy criterion, using both leading- and trailing-edge controls, to suppress flutter of a simplified delta-wing model. Use of this technique has resulted in an increase in the flutter dynamic pressure of approximately 12 percent for this model at a Mach number of 0.9 Analytical methods used to predict the open- and closed-loop behavior of the model are also discussed. The second study, was conducted to establish the effect of active flutter suppression on a model of the Boeing B-52 Control Configured Vehicle (CCV). Some preliminary results of this study indicate significant improvements in the damping associated with the critical flutter mode. |
| File Size | 7528472 |
| Page Count | 32 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730022132 |
| Archival Resource Key | ark:/13960/t8dg1hj28 |
| Language | English |
| Publisher Date | 1973-09-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Aircraft Stability Wind Tunnel Tests Transonic Speed Flutter Analysis Flight Control Aerodynamic Characteristics Aircraft Control B-52 Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
