Fuel efficiency optimization of high-aspect-ratio aircraft via variable camber technology considering aeroelasticity

2020 ◽  
pp. 095441002095996
Author(s):  
Liqiang Guo ◽  
Jun Tao ◽  
Cong Wang ◽  
Miao Zhang ◽  
Gang Sun
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Fuel Efficiency ◽  
Free Form ◽  
Deformation Method ◽  
Grid Deformation ◽  
Computational Structural Dynamics ◽  
Control Matrix ◽  
Nonlinear Static ◽  
Original Configuration

In this study, variable camber technology is applied to improve the fuel efficiency of high-aspect-ratio aircraft with aeroelasticity considered. The nonlinear static aeroelastic analyses are conducted for CFD/CSD (computational fluid dynamics/computational structural dynamics) numerical simulations. The RBF (radial basis function) method is adopted for the transmission of aerodynamic loads and structural displacements, the diffusion smoothing method is employed for grid deformation in each iteration of CFD/CSD coupling, and the FFD (free-form deformation) method is introduced for the parameterization of variable camber wing. Based on the aerodynamic characteristic curves under different cambers, the discrete variable camber control matrix for the high-aspect-ratio aircraft during the cruise phase is established. The Fibonacci method is employed to optimize the fuel efficiency by utilizing the control matrix. The results indicate that the drag during the cruise phase is reduced obviously and the fuel efficiency is improved evidently comparing to the original configuration.

scholarly journals Analytic free-form lens design for imaging applications with high aspect ratio

2012 ◽  
Author(s):  
Fabian Duerr ◽  
Pablo Benítez ◽  
Juan Carlos Miñano ◽  
Youri Meuret ◽  
Hugo Thienpont
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Free Form ◽  
Lens Design

scholarly journals Potential benefits of free-form optics in on-axis imaging applications with high aspect ratio

2013 ◽  
Vol 21 (25) ◽  
pp. 31072 ◽  
Author(s):  
Fabian Duerr ◽  
Youri Meuret ◽  
Hugo Thienpont
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Free Form ◽  
Potential Benefits

High-aspect-ratio, free-form patterning of carbon nanotube forests using micro-electro-discharge machining

2010 ◽  
Vol 19 (11) ◽  
pp. 1405-1410 ◽  
Author(s):  
Waqas Khalid ◽  
Mohamed Sultan Mohamed Ali ◽  
Masoud Dahmardeh ◽  
Yongho Choi ◽  
Parham Yaghoobi ◽  
...  
Keyword(s):  
Carbon Nanotube ◽  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Free Form ◽  
Electro Discharge Machining ◽  
Carbon Nanotube Forests

scholarly journals Effect of ply angle on nonlinear static aeroelasticity of high-aspect-ratio composite wing

2020 ◽  
Vol 22 (4) ◽  
pp. 959-970
Author(s):  
Junli Wang ◽  
Shuai Lei ◽  
Tuolei Li ◽  
Wensheng Zhang ◽  
Zhigui Ren ◽  
...  
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Static Aeroelasticity ◽  
Nonlinear Static ◽  
Composite Wing

scholarly journals Nonlinear Static Aeroelasticity of High-Aspect-Ratio-Wing Aircraft by Finite Element and Multibody Methods

2017 ◽  
Vol 54 (2) ◽  
pp. 548-560 ◽  
Author(s):  
Michele Castellani ◽  
Jonathan E. Cooper ◽  
Yves Lemmens
Keyword(s):  
Finite Element ◽  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Static Aeroelasticity ◽  
Nonlinear Static

scholarly journals Aerodynamic effects of a folding wingtip to increase take-off, landing and cruise performance.

2022 ◽  
pp. 35-44
Author(s):  
S Rajat Singh ◽  
Amala Raja Rajeswar Gajula ◽  
Praneetha Maccha
Keyword(s):  
High Pressure ◽  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Fuel Efficiency ◽  
Bottom Surface ◽  
Induced Drag ◽  
The World ◽  
Gust Loads ◽  
Folding Wing ◽  
Wing Tip

The main purpose of a folding wing tip is to allow aerodynamically efficient high aspect ratio wing. To allow a wing tip to move in flight is to alleviate the loads and achieve lower wing weight or enable wing span to maximize. Thus reduces the induced drag and improve fuel efficiency. The folding wing tip may include spring devices in order to provide an additional gust loads alleviation ability in flight. A wing without a winglet produces wingtip vortices which increases drag as the air from the bottom surface of the wing (high pressure) tries to move to the upper surface (low pressure). To avoid this and have less vortices a winglet is used, around which the flow is same on both surfaces. A folding wingtip can be set at an angle of 0° to have maximum cruise performance and aspect ratio. If the wingtip is set in the range of 15°-50° it can increase lift during take-off. This folding wingtip can access any airport in the world because if it is folded at an angle of 90°, it can meet the gate requirements and restrictions of any airport. To study the performance of this mechanism, the wing tip was designed by using CATIA V5 software. The analysis of the wingtip at different angle of attacks was done using ANSYS and XFLR 5 softwares.

Numerical analysis of geometrical nonlinear aeroelasticity with CFD/CSD method

2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Xueyuan Nie
Keyword(s):  
Finite Element ◽  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Data Transfer ◽  
Geometrical Nonlinearity ◽  
Three Dimensional ◽  
Geometrical Nonlinear ◽  
Static Aeroelasticity ◽  
Nonlinear Static ◽  
Linear And Nonlinear

Abstract A nonlinear static aeroelastic methodology based on the coupled CFD/CSD approach has been developed to study the geometrical nonlinear aeroelastic behaviors of high-aspect-ratio or multi-material flexible aerial vehicles under aerodynamic loads. The Reynolds-averaged Navier–Stokes solver combined with the three-dimensional finite-element nonlinear solver is used to perform the fluid-structure coupling simulation. The interpolation technique for data transfer between the aerodynamic and structural modules employs radial basis function algorithm as well as dynamic mesh deformation. A high-aspect-ratio structure with multi-material is modeled by the finite element method to investigate the effects of geometrical nonlinearity on the aeroelastic behavior. Numerical simulations of the linear and nonlinear static aeroelasticity were conducted at transonic regime with different angles of attack. By comparing the aeroelastic behaviors of linear and nonlinear structure, it shows that geometrical nonlinearity plays an important role for flexible high-aspect-ratio wings undergoing the large static aeroelastic deformation and should be taken into account in aeroelastic analysis for such structures.

Sign in / Sign up

Export Citation Format

Share Document