A design optimization study of a composite wing box for the civil tiltrotor transport aircraft based on a reduced wing maximum-thickness-to-chord ratio is considered. The wing box is designed for minimum structural weight subject to local constraints according to material strength and minimum gage requirements and global constraints based on wing primary natural frequencies and overall buckling strength. Six loading conditions corresponding to airplane, helicopter, and conversion flight modes have been considered. The continuous design variables include the ply orientation angle and thickness in each skin panel, the web thicknesses of the spars and ribs, and the cross-sectional areas of spar caps and stringers. In addition, the number of stringers is considered as a discrete design variable. The structural analysis is based on finite-element method, and the optimization solution is based on the method of modified feasible directions. The results of this investigation reveal that it is possible to minimize the structural weight, and arrive at a set of feasible wing designs, based on the number of stringers used, at a reduced maximum-thickness-to-chord ratio. The results further indicate that the loads corresponding to the airplane mode along with the wing torsion natural frequency have the greatest influence on the design.
A thin tailored composite wing box for a civil tiltrotor transport aircraft
Ein dünner, individuell hergestellter Verbundflügelkasten für ein Schwenkrotor-Ziviltransportflugzeug
1996
11 Seiten, 4 Tabellen, 8 Quellen
Aufsatz (Konferenz)
Englisch
A Thin Tailored Composite Wing Box for a Civil Tiltrotor Transport Aircraft
British Library Conference Proceedings | 1996
|Thin Tailored Composite Wing for Civil Tiltrotor
NTIS | 1994
|Thin tailored composite wing for civil tiltrotor
NTRS | 1994
|Wing design for a civil tiltrotor transport aircraft
NTRS | 1994
|