Structural Design and Aeroelastic Analysis of an Oscillating Airfoil for Flapping Wing Propulsion

2008 ◽  
Author(s):  
Ralf Unger ◽  
Matthias Haupt ◽  
Peter Horst ◽  
Jan Windte
Keyword(s):  
Structural Design ◽  
Flapping Wing ◽  
Aeroelastic Analysis ◽  
Oscillating Airfoil

scholarly journals Multidisciplinary design optimization of the flapping wing system for forward flight

2017 ◽  
Vol 9 (2) ◽  
pp. 93-110
Author(s):  
Jung-Sun Choi ◽  
Gyung-Jin Park
Keyword(s):  
Design Optimization ◽  
Design Process ◽  
Multidisciplinary Design Optimization ◽  
Flapping Wing ◽  
Multidisciplinary Design ◽  
Vehicle Model ◽  
Thrust Coefficient ◽  
Analysis And Design ◽  
Aeroelastic Analysis ◽  
Air Vehicle

The success of a flapping wing air vehicle flight is strongly related to the flapping motion and wing structure. Various disciplines should be considered for analysis and design of the flapping wing system. A design process for a flapping wing system is defined by using multidisciplinary design optimization. Unsteady aeroelastic analysis is employed as the system analysis. From the results of the aeroelastic analysis, the deformation of the wing is transmitted to the fluid discipline and the dynamic pressure is conveyed to the structural discipline. In the fluid discipline, a kinematic optimization problem is solved to maximize the time-averaged thrust coefficient and the propulsive efficiency simultaneously. In the structural discipline, nonlinear dynamic topology optimization is performed to find the distribution of reinforcement by using the equivalent static loads method for nonlinear static response structural optimization. The defined design process is applied to a flapping wing air vehicle model and the flapping wing air vehicle model is fabricated based on the optimization results.

scholarly journals Aeroelastic Analysis of a Flapping Blow Fly Wing

2020 ◽  
Vol vm01 (is01) ◽  
pp. 14-21
Author(s):  
Can Beker ◽  
Ali Emre Turgut ◽  
Kutluk Bilge Arikan ◽  
Dilek Funda Kurtulus
Keyword(s):  
Fluid Dynamics ◽  
3D Model ◽  
Input Function ◽  
Flapping Wing ◽  
Blow Fly ◽  
Structural Dynamic ◽  
Aeroelastic Analysis ◽  
Sinusoidal Input ◽  
Computational Fluid Dynamics Cfd ◽  
Analysis Models

In this study, a 3D model of the bio-inspired blowfly wing Callphere Erytrocephala is created and aeroelastic analysis is performed to calculate its aerodynamical characteristics by use of numerical methods. To perform the flapping motion, a sinusoidal input function is created. The scope of this study is to perform aeroelastic analysis by synchronizing computational fluid dynamics (CFD) and structural dynamic analysis models and to investigate the unsteady lift formation on the aeroelastic flapping wing for different angles of attack.

The Influence Analysis of Stiffness on Stringer Layout and Dimension of Full Composite Wing

2014 ◽  
Vol 911 ◽  
pp. 3-7
Author(s):  
Sheng Jun Qiao ◽  
Hang Shan Gao ◽  
Fu Sheng Wang ◽  
Zhu Feng Yue
Keyword(s):  
Structural Design ◽  
Bending Stiffness ◽  
Torsional Stiffness ◽  
Wall Structure ◽  
Thin Wall ◽  
Influence Analysis ◽  
Wing Section ◽  
Aeroelastic Analysis ◽  
Center Position ◽  
Composite Wing

The present study aimed at obtaining torsional stiffness, bending stiffness and stiffness center position of full composite wing using thin wall structure mechanics theory. The influence of stringer layout on wing integer structure stiffness was furthermore investigated. It was found that wing section stiffness was influenced by stringer layout and dimension. The best spacing of stringer was within the range from 130 mm to 150 mm, at the same time, stringer stiffness had more change by the differences of its numbers. The study of this paper provided important support for structural design and aeroelastic analysis on composite wing.

Flow Field Measurements on an Oscillating Airfoil for Flapping Wing Propulsion

2008 ◽  
Author(s):  
Stephan Bansmer ◽  
Ulrich Scholz ◽  
Jan Windte ◽  
Christian Kähler ◽  
Rolf Radespiel
Keyword(s):  
Flow Field ◽  
Field Measurements ◽  
Flapping Wing ◽  
Oscillating Airfoil

An aeroelastic analysis of a flexible flapping wing using modified strip theory

2008 ◽  
Author(s):  
Dae-Kwan Kim ◽  
Jun-Seong Lee ◽  
Jin-Young Lee ◽  
Jae-Hung Han
Keyword(s):  
Flapping Wing ◽  
Aeroelastic Analysis ◽  
Strip Theory

Nonlinear Aeroelastic Analysis for Highly Flexible Flapping Wing in Hover

2022 ◽  
Author(s):  
Xuan Yang ◽  
Aswathi Sudhir ◽  
Atanu Halder ◽  
Moble Benedict
Keyword(s):  
Structural Model ◽  
Flapping Wing ◽  
Image Correlation ◽  
Elastic Response ◽  
Flapping Wings ◽  
Aerodynamic Model ◽  
Aeroelastic Analysis ◽  
Air Vehicle ◽  
Aeroelastic Simulations ◽  
Nonlinear Fluid

Aeromechanics of highly flexible flapping wings is a complex nonlinear fluid–structure interaction problem and, therefore, cannot be analyzed using conventional linear aeroelasticity methods. This paper presents a standalone coupled aeroelastic framework for highly flexible flapping wings in hover for micro air vehicle (MAV) applications. The MAV-scale flapping wing structure is modeled using fully nonlinear beam and shell finite elements. A potential-flow-based unsteady aerodynamic model is then coupled with the structural model to generate the coupled aeroelastic framework. Both the structural and aerodynamic models are validated independently before coupling. Instantaneous lift force and wing deflection predictions from the coupled aeroelastic simulations are compared with the force and deflection measurements (using digital image correlation) obtained from in-house flapping wing experiments at both moderate (13 Hz) and high (20 Hz) flapping frequencies. Coupled trim analysis is then performed by simultaneously solving wing response equations and vehicle trim equations until trim controls, wing elastic response, inflow and circulation converge all together. The dependence of control inputs on weight and center of gravity (cg) location of the vehicle is studied for the hovering flight case.

scholarly journals New biomimetic approach to the aircraft wing structural design based on aeroelastic analysis

2017 ◽  
Vol 65 (5) ◽  
pp. 741-750
Author(s):  
D. Gawel ◽  
M. Nowak ◽  
H. Hausa ◽  
R. Roszak
Keyword(s):  
Structural Design ◽  
Interaction Analysis ◽  
Load Case ◽  
Aircraft Wing ◽  
And Topology ◽  
Aeroelastic Analysis ◽  
Biomimetic Approach ◽  
Wing Structure ◽  
Multiple Load Case ◽  
Multiple Load

Abstract This paper presents a new biomimetic approach to the structural design. For the purpose of aircraft wing design the numerical environment combining simultaneous structural size, shape, and topology optimization based on aeroelastic analysis was developed. For the design of aircraft elements the optimization process must be treated as a multi-load case task, because during the fluid structure interaction analysis each step represents a different structural load case. Also, considering different angles of attack, during the CFD computation each result is considered. The method-specific features (such as domain independence, functional configurations during the process of optimization, and multiple load case solution implemented in the optimization scenario) enable the optimal structural form. To illustrate the algorithm functionality, the problem of determining the optimal internal wing structure was presented. The optimal internal wing structure resulting from aeroelastic computation with different angles of attack has been presented.

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