An optimization design method for aerodynamic configuration of high aspect ratio wing

Purpose Computational efficiency is always the major concern in aircraft design. The purpose of this research is to investigate an efficient jig-shape optimization design method. A new jig-shape optimization method is presented in the current study and its application on the high aspect ratio wing is discussed. Design/methodology/approach First, the effects of bending and torsion on aerodynamic distribution were discussed. The effect of bending deformation was equivalent to the change of attack angle through a new equivalent method. The equivalent attack angle showed a linear dependence on the quadratic function of bending. Then, a new jig-shape optimization method taking integrated structural deformation into account was proposed. The method was realized by four substeps: object decomposition, optimization design, inversion and evaluation. Findings After the new jig-shape optimization design, both aerodynamic distribution and structural configuration have satisfactory results. Meanwhile, the method takes both bending and torsion deformation into account. Practical implications The new jig-shape optimization method can be well used for the high aspect ratio wing. Originality/value The new method is an innovation based on the traditional single parameter design method. It is suitable for engineering application.

Download Full-text

Mesh Regeneration Method for Jig-Shape Optimization Design of the High-Aspect-Ratio Wing

Advances in Mechanical Engineering ◽

10.1155/2013/513637 ◽

2013 ◽

Vol 5 ◽

pp. 513637 ◽

Cited By ~ 2

Author(s):

S. H. Huo ◽

F. S. Wang ◽

Z. Yuan ◽

Z. F. Yue

Keyword(s):

Aspect Ratio ◽

Shape Optimization ◽

High Aspect Ratio ◽

Optimization Design

Download Full-text

Static Aeroelasticity Analysis of High Aspect Ratio Wing and the Jig-Shape Design Based on Multi-Block Structural Grid

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.302.377 ◽

2013 ◽

Vol 302 ◽

pp. 377-383 ◽

Cited By ~ 2

Author(s):

Yan Liu ◽

Jun Qiang Bai ◽

Jun Hua

Keyword(s):

Aspect Ratio ◽

Design Process ◽

High Aspect Ratio ◽

Design Method ◽

Aerodynamic Characteristics ◽

Shape Design ◽

Transport Aircraft ◽

Mesh Motion ◽

Static Aeroelasticity ◽

Motion Method

The influence of structural elastic deformation on the aerodynamic characterisitcs of large transport aircraft has been researched. A method of static aeroelasticity based on multi-block structural grid of high aspect ratio wing has been established, and then a design method of jig-shape is developed. The technology of RBF interpolation is used to exchange the data of CFD/CSD. Based on RBF&Delaunay technology, a mesh motion method is developed to make the design process less time-consuming, which can be applied to large deformation of multi-block structural grid. The static aeroelastic deformation of a wing-body of large transport aircraft is analyzed. Then the wing-body's jig-shape is designed. Compared the aerodynamic characteristics between design cruise shape and target cruise shape, it shows that the aerodynamic characteristics of design cruise shape is almost equal to target cruise shape and the design process of jig-shape is feasible.

Download Full-text

A Strength Design Method of Cemented Backfill with a High Aspect Ratio

Advances in Civil Engineering ◽

10.1155/2020/7159208 ◽

2020 ◽

Vol 2020 ◽

pp. 1-11

Author(s):

Zhi-zhihui Wang ◽

Ai-xiang Wu ◽

Hong-jiang Wang

Keyword(s):

Aspect Ratio ◽

High Aspect Ratio ◽

Lateral Pressure ◽

Slip Surface ◽

Design Method ◽

Numerical Models ◽

Limit Equilibrium ◽

Friction Angle ◽

Aspect Ratios ◽

Cemented Backfill

To calculate the required strength of a cemented backfill with high aspect ratio, the confirmation of lateral pressure is fundamental and needs to be determined first. As for the backfill with a high aspect ratio of height to length, the shape of the slip surface is not straight when in the active state due to the limited space, which is different from the general backfill. For this reason, a formulation of the slip surface with a curved shape and a lateral pressure calculation method based on this curved slip surface were proposed. The proposed equation of the slip surface is affected by the geometry parameters of the backfill, internal friction angle of the backfill, and the friction angle of the backfill-rock interface. Then, by the combination of the minor principal stress trajectory method and the horizontal slice method, an ordinary differential equation of stresses was established and then solved numerically. Finally, the method based on Mitchell’s three-dimensional limit equilibrium model was used to calculate the required strength of the cemented backfill. The calculated results were compared with previous studies and validated with numerical models. The results showed good consistency for the backfills with high aspect ratios.

Download Full-text

Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation

Shock and Vibration ◽

10.1155/2017/2564314 ◽

2017 ◽

Vol 2017 ◽

pp. 1-16

Author(s):

Changchuan Xie ◽

Yang Meng ◽

Fei Wang ◽

Zhiqiang Wan

Keyword(s):

Aspect Ratio ◽

Large Deformation ◽

High Aspect Ratio ◽

Optimization Design ◽

Geometrical Nonlinearity ◽

Computing Time ◽

Wind Tunnel Test ◽

Lattice Method ◽

Wing Model ◽

Design Variables

This paper presents a framework of aeroelastic optimization design for high-aspect-ratio wing with large deformation. A highly flexible wing model for wind tunnel test is optimized subjected to multiple aeroelastic constraints. Static aeroelastic analysis is carried out for the beamlike wing model, using a geometrically nonlinear beam formulation coupled with the nonplanar vortex lattice method. The flutter solutions are obtained using the P-K method based on the static equilibrium configuration. The corresponding unsteady aerodynamic forces are calculated by nonplanar doublet-lattice method. This paper obtains linear and nonlinear aeroelastic optimum results, respectively, by the ISIGHT optimization platform. In this optimization problem, parameters of beam cross section are chosen as the design variables to satisfy the displacement, flutter, and strength requirements, while minimizing wing weight. The results indicate that it is necessary to consider geometrical nonlinearity in aeroelastic optimization design. In addition, optimization strategies are explored to simplify the complex optimization process and reduce the computing time. Different criterion values are selected and studied for judging the effects of the simplified method on the computing time and the accuracy of results. In this way, the computing time is reduced by more than 30% on the premise of ensuring the accuracy.

Download Full-text