| タイトル | Integrated aerodynamic-structural-control wing design |
| 著者（英） | Rais-Rohani, M.; Haftka, R. T.; Unger, E. R.; Grossman, B. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1992-01-01
1992 |
| 言語 | eng |
| 内容記述 | The aerodynamic-structural-control design of a forward-swept composite wing for a high subsonic transport aircraft is considered. The structural analysis is based on a finite-element method. The aerodynamic calculations are based on a vortex-lattice method, and the control calculations are based on an output feedback control. The wing is designed for minimum weight subject to structural, performance/aerodynamic and control constraints. Efficient methods are used to calculate the control-deflection and control-effectiveness sensitivities which appear as second-order derivatives in the control constraint equations. To suppress the aeroelastic divergence of the forward-swept wing, and to reduce the gross weight of the design aircraft, two separate cases are studied: (1) combined application of aeroelastic tailoring and active controls; and (2) aeroelastic tailoring alone. The results of this study indicated that, for this particular example, aeroelastic tailoring is sufficient for suppressing the aeroelastic divergence, and the use of active controls was not necessary. |
| NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 93A20307
AIAA PAPER 92-4694 |
| 権利 | Copyright |
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