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

2013 ◽  
Vol 302 ◽  
pp. 377-383 ◽  
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.

scholarly journals AERO DYNAMIC SHAPE OF TRANSPORT AIRCRAFT “FLYING WING” SCHEME WITH HIGH ASPECT RATIO

2014 ◽  
pp. 84-92
Author(s):  
Олег Львович Лемко ◽  
Євген О. Кушніренко
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Aerodynamic Characteristics ◽  
Design Parameters ◽  
Scientific Methods ◽  
Transport Aircraft ◽  
Research Problems ◽  
And Performance ◽  
Forming Methods ◽  
Dynamic Shape

"Normal" aerodynamic scheme despite the fact that it has become the dominant in global aviation, in terms of aerodynamics is not ideal. To create a lifting force only wing is just necessary. All other elements of aircraft glider - fuselage , horizontal and vertical tail exist only for the crew, passengers and cargo, ensuring the sustainability and management to provide a satisfactory landing characteristics. It became apparent that with the increasing size of the planes becomes possible and appropriate to place all the major part of their weight directly in the wing. This idea was expressed in aerodynamic scheme "flying wing".The purpose of the research is to form aerodynamic look of transport aircraft "flying wing" scheme with high aspect ratio, creating aerodynamic design that provides the greatest rate of return and optimal weight range and flight duration.Objectives of the study are: analysis of scientific sources on establishing LA scheme "flying wing", development of forming methods of the aerodynamic look of transport aircraft scheme "flying wing", based on a synthesis of existing methods for assessing the flight - the technical characteristics of the aircraft, studies and analyzes of theoretical methods of aerodynamic layouts transport aircraft "flying wing" scheme to determine the aerodynamic and flight characteristics.            Were used following scientific methods to solve the research problems:             1. Method of forming the aerodynamic characteristics of the freeform aircraft shape in the parameters of similarity and generalized design parameters.             2. Statistical methods for assessing the aerodynamic and performance characteristics.             3. Numerical methods.The practical value of my work: developed method allows you to create aerodynamic layout scheme aircraft "flying wing" of the great extension that allows you to fully realize the benefits of the scheme, developed and reasonable advices on the aircraft aerodynamic look of "flying wing" scheme of high aspect ratio.

A new jig-shape optimization method for the high aspect ratio wing

2018 ◽  
Vol 91 (1) ◽  
pp. 124-133
Author(s):  
Zhe Yuan ◽  
Shihui Huo ◽  
Jianting Ren
Keyword(s):  
Aspect Ratio ◽  
Shape Optimization ◽  
High Aspect Ratio ◽  
Optimization Design ◽  
Design Method ◽  
Aircraft Design ◽  
Optimization Method ◽  
Attack Angle ◽  
Structural Deformation ◽  
Content Type

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.

The aeroelastic characteristics of high aspect ratio wing

2016 ◽  
Vol 230 (14) ◽  
pp. 2543-2556
Author(s):  
Fan Yang ◽  
Zhufeng Yue ◽  
Lei Li
Keyword(s):  
Aspect Ratio ◽  
Large Deformation ◽  
High Aspect Ratio ◽  
Data Exchange ◽  
Stokes Equations ◽  
Great Influence ◽  
Aerodynamic Characteristics ◽  
Interface Problem ◽  
Numerical Result ◽  
Computational Structural Mechanics

Owing to the elasticity, the large deformation was brought in the high aspect ratio wing in the flight. The large deformation had a great influence on the flight performance. In this paper, the loosely coupled method was used for the research of high aspect ratio wing aeroelastic problems. The Navier–Stokes equations were solved for fluid domain computation, and the nonlinear finite element method was adopted for solid domain computation. The data exchange program and mesh regeneration progress were adopted for fluid–structure interface problem. Finally, the aerodynamic characteristics of high aspect ratio wing were obtained under different fly conditions. In addition, to validate the proposed method, the flutter analysis of AGARD 445.6 wing is carried out and compared with the experimental data. The numerical result validates the proposed computational fluid dynamics/computational structural mechanics method.

scholarly journals Loads analysis and structural optimization of a high aspect ratio, composite wing aircraft

2021 ◽  
Author(s):  
Kautuk Sinha ◽  
Thomas Klimmek ◽  
Matthias Schulze ◽  
Vega Handojo
Keyword(s):  
Aspect Ratio ◽  
Structural Optimization ◽  
Design Process ◽  
High Aspect Ratio ◽  
Structural Design ◽  
Composite Structures ◽  
Selection Process ◽  
Weight Ratio ◽  
Bending Moment ◽  
Composite Wing

AbstractComposite structures have shown a prominent impact in the aircraft structural design. With an increasing shift towards incorporating more composite materials in the primary aircraft structure it is imperative to have corresponding design tools to simplify the design process. In the present work, a simplified implementation for composite optimization has been developed within the DLR-AE (German Aerospace Centre, Institute of Aeroelasticity) automated aeroelastic structural design framework cpacs-MONA. This paper presents the results of structural optimization of a high aspect ratio composite wing aircraft model developed in the DLR project ATLAs. The generation of almost all involved simulation models for this study is done using the in-house DLR tool ModGen. An aeroelastic trim analysis is conducted for various manoeuvre and gust conditions. A load selection process is used to determine the most relevant sizing load cases. A comparison is made between the optimization results of a composite wing and an aluminium wing to demonstrate the more favourable strength to weight ratio of the composite wing. A manoeuvre load alleviation procedure has been introduced in the load calculation process. The results show further weight savings in the design process when load alleviation is utilized due to reduction in the span wise bending moment.

Conceptual design and analysis of an affordable truss-braced wing regional jet aircraft

2020 ◽  
pp. 095441002092306
Author(s):  
Saeed Hosseini ◽  
Mohammad Ali Vaziri-Zanjani ◽  
Hamid Reza Ovesy
Keyword(s):  
Aspect Ratio ◽  
Cost Analysis ◽  
High Aspect Ratio ◽  
Passenger Transport ◽  
Transport Aircraft ◽  
Aspect Ratios ◽  
The Cost ◽  
Bypass Ratio ◽  
Very High ◽  
Selection Of

A regional, turbofan-powered, 72-passenger, transport aircraft with very high aspect ratio truss-braced wings is developed with an affordable methodology from an existing 52 passenger, conventional twin-turboprop aircraft. At first, the ration behind the selection of the truss-braced wing configuration is discussed. Next, the methodologies for the sizing, weight, aerodynamics, performance, and cost analysis are presented and validated against existing regional aircraft. The variant configurations and their design features are then discussed. Finally, sensitivity analysis is carried out to investigate the effects of the wing aspect ratio and engine bypass ratio on the aircraft weight, aerodynamics, and cost. It has been found that the penalties associated with the wing weight will prevent the acceptable realization of the high aspect ratio wing benefits, but when it is combined with the very high bypass ratio engines, a 17% reduction in the mission fuel weight is achieved. In contrast, the cost analysis has revealed that the application of higher aspect ratio wings in the truss-braced wing configuration may increase the development and maintenance costs. Consequently, with aspect ratios higher than 24, eventually, these costs may outperform the associated fuel cost reductions.

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