Structural wing sizing for multidisciplinary design optimization of a strut-braced wing

被引:15
作者
Gern, FH
Naghshineh-Pour, AH
Sulaeman, E
Kapania, RK
Haftka, RT
机构
[1] Virginia Polytech Inst & State Univ, Dept Aerosp & Ocean Engn, Blacksburg, VA 24061 USA
[2] Univ Florida, Dept Aerosp Engn Mech & Engn Sci, Gainesville, FL 32611 USA
来源
JOURNAL OF AIRCRAFT | 2001年 / 38卷 / 01期
关键词
D O I
10.2514/2.2747
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
A structural and aeroelastic model for wing sizing and weight calculation of a strut-braced wing is described. The ming weight is calculated using a newly developed analysis accounting for the special nature of strut-braced wings. A specially developed aeroelastic model enables one to consider wing flexibility and spanwise redistribution of the aerodynamic loads during in-flight maneuvers. The structural model uses a hexagonal wing-box featuring skin panels, stringers, and spar caps, whereas the aerodynamics part employs a linearized transonic vortex lattice method. Thus, the wing weight may be calculated from the rigid or flexible wing spanload. The calculations reveal the significant influence of the strut on the bending material weight of the wing. The strut enables one to design a wing featuring thin airfoils without weight penalty. It also influences the spanwise redistribution of the aerodynamic loads and the resulting deformations. Increased weight savings are possible by iterative resizing of the wing structure using the actual design loads. As an advantage over the cantilever wing, the twist moment caused by the strut farce results in increased load alleviation,leading to further structural weight savings.
引用
收藏
页码:154 / 163
页数:10
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