scholarly journals High-fidelity multidisciplinary design optimization of flexible aircraft wings

2021 ◽  
Author(s):  
Brian T. Leonard
Keyword(s):  
Design Optimization ◽  
Multidisciplinary Design Optimization ◽  
Multidisciplinary Design ◽  
High Fidelity ◽  
Element Analysis ◽  
Aircraft Wings ◽  
Aeroelastic Analysis ◽  
Computational Fluid Dynamics Cfd ◽  
Wing Structure ◽  
Design Freedom

Multidisciplinary design optimization (MDO) was performed on an aircraft wing using high-fidelity design tools. The wing aerodynamics were analyzed using computational fluid dynamics (CFD) with FLUENT and the wing structure was analyzed via finite element analysis (FEA) in ANSYS. MATLAB was used as a wrapper to perform computational static aeroelastic analysis on any wing configuration using the aforementioned high-fidelity tools. A main program was developed to convert pressures to forces, map the CFD grid to the FEA mesh, and to transfer the FEA displacements back to the CFD grid. The static aeroelastic software was coupled with the multidisciplinary design feasible (MDF) MDO architecture using sequential quadratic programming (SQP) to perform the optimization. The optimization was given the maximum amount of design freedom to create any wing shape. Ultimately, it was found that MDO is possible using these high-fidelity tools and that, to get a true wing design, aeroelastic effects must be included in the MDO procedure.

scholarly journals High-fidelity multidisciplinary design optimization of flexible aircraft wings

2021 ◽  
Author(s):  
Brian T. Leonard
Keyword(s):  
Design Optimization ◽  
Multidisciplinary Design Optimization ◽  
Multidisciplinary Design ◽  
High Fidelity ◽  
Element Analysis ◽  
Aircraft Wings ◽  
Aeroelastic Analysis ◽  
Computational Fluid Dynamics Cfd ◽  
Wing Structure ◽  
Design Freedom

Multidisciplinary design optimization (MDO) was performed on an aircraft wing using high-fidelity design tools. The wing aerodynamics were analyzed using computational fluid dynamics (CFD) with FLUENT and the wing structure was analyzed via finite element analysis (FEA) in ANSYS. MATLAB was used as a wrapper to perform computational static aeroelastic analysis on any wing configuration using the aforementioned high-fidelity tools. A main program was developed to convert pressures to forces, map the CFD grid to the FEA mesh, and to transfer the FEA displacements back to the CFD grid. The static aeroelastic software was coupled with the multidisciplinary design feasible (MDF) MDO architecture using sequential quadratic programming (SQP) to perform the optimization. The optimization was given the maximum amount of design freedom to create any wing shape. Ultimately, it was found that MDO is possible using these high-fidelity tools and that, to get a true wing design, aeroelastic effects must be included in the MDO procedure.

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.

Finite Element Analysis and Multidisciplinary Design Optimization of Diesel Engine Connecting Rod Based on ISIGHT

2012 ◽  
Vol 479-481 ◽  
pp. 1863-1867
Author(s):  
Shou Guang Yao ◽  
Sheng Chen Zhao ◽  
Fei Liu
Keyword(s):  
Diesel Engine ◽  
Design Optimization ◽  
Multidisciplinary Design Optimization ◽  
Design Method ◽  
Equivalent Stress ◽  
Optimization Method ◽  
Multidisciplinary Design ◽  
Connecting Rod ◽  
Element Analysis ◽  
Maximum Equivalent Stress

Based on the multidisciplinary design optimization method and the MDO software ISIGHT, the 16PA6STC diesel engine connecting rod was taken to the model, used the Pro/engineer software to build the 3D model of connecting rod. The software ANSYS and Nastran was taken to complete the static analysis and modal analysis to get the maximum equivalent stress and the first and second modal frequencies. the software including Pro/Engineer、ANSYS、Nastran, was combined on the ISIGHT to complete the structural optimization work on the condition of restrain the stress and modal of the connecting rod, to explore the application of the MDO design method in the diesel engine connecting rod structure optimization field, offer a reference for the further improvement design study.

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