Numerical method of static aeroelastic correction and jig-shape design for large airliners

• Published in: Science China. Technological sciences 2012-09, Vol.55 (9), p.2447-2452
• Main Authors: Huang, Wei, Lu, ZhiLiang, Guo, TongQing, Xue, Fei, Zhang, Miao
• Format: Article
• Language: English
• Subjects: Aeroelasticity; Commercial aircraft; Commercial planes; Design engineering; Engineering; Iterative methods; Mathematical analysis; Mathematical models; NS方程; Wings (aircraft); 外形设计; 多块结构化网格; 大型客机; 夹具; 数值方法; 空气动力学计算; 静气动弹性
• ISSN: 1674-7321; 1869-1900
• DOI: 10.1007/s11431-012-4936-0

In this paper, a coupled CFD-CSD method based on N-S equations is described for static aeroelastic correction and jig-shape design of large airliners. The wing structural flexibility matrix is analyzed by a finite element method with a double-beam model. The viscous multi-block structured grid is used in aerodynamic calculations. Flexibility matrix interpolation is fulfilled by use of a surface spline method. The load distributions on wing surface are evaluated by solving N-S equations with a paral- lel algorithm. A flexibility approach is employed to calculate the structural deformations. By successive iterations between steady aerodynamic forces and structural deformations, a coupled CFD-CSD method is achieved for the static aeroelastic cor- rection and jig-shape design of a large airliner. The present method is applied to the static aeroelastic analysis and jig-shape design for a typical large airliner with engine nacelle and winglet. The numerical results indicate that calculations of static aeroelastic correction should employ tightly coupled CFD-CSD iterations, and that on a given cruise shape only one round of iterative design is needed to obtain the jig-shape meeting design requirements.