| タイトル | Aeroservoelastic Testing of a Sidewall Mounted Free Flying Wind-Tunnel Model |
| 本文（外部サイト） | http://hdl.handle.net/2060/20080033678 |
| 著者（英） | Vetter, Travis K.; Scott, Robert C.; Coulson, David A.; Penning, Kevin B.; Heeg, Jennifer |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2008-08-18 |
| 言語 | eng |
| 内容記述 | A team comprised of the Air Force Research Laboratory (AFRL), Northrop Grumman, Lockheed Martin, and the NASA Langley Research Center conducted three j wind-tunnel tests in the Transonic Dynamics Tunnel to demonstrate active control technologies relevant to large, exible vehicles. In the rst of these three tests, a semispan, aeroelastically scaled, wind-tunnel model of a ying wing SensorCraft vehi- cle was mounted to a force balance to demonstrate gust load alleviation. In the second and third tests, the same wing was mated to a new, multi-degree-of-freedom, sidewall mount. This mount allowed the half-span model to translate vertically and pitch at the wing root, allowing better simulation of the full span vehicle's rigid-body modes. Gust Load Alleviation (GLA) and Body Freedom Flutter (BFF) suppression were successfully demonstrated. The rigid body degrees-of-freedom required that the model be own in the wind tunnel using an active control system. This risky mode of testing necessitated that a model arrestment system be integrated into the new mount. The safe and successful completion of these free-flying tests required the development and integration of custom hardware and software. This paper describes the many systems, software, and procedures that were developed as part of this effort. |
| NASA分類 | Fluid Mechanics and Thermodynamics |
| レポートNO | AIAA Paper 2008-7186 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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