Application of hybrid optimization technique for improved aeroelastic performance of composite wings

Aditi Chattopadhyay; Ratneshwar Jha; Charles Seeley

doi:10.2514/6.1996-4015

Application of hybrid optimization technique for improved aeroelastic performance of composite wings

Aditi Chattopadhyay, Ratneshwar Jha, Charles Seeley

Mechanical and Aerospace Engineering

Research output: Contribution to conference › Paper › peer-review

1 Scopus citations

Abstract

A comprehensive procedure has been developed for aeroelastic optimization of composite wings. Wing structural weight is taken as the objective function with constraints on flutter/divergence speed and stresses at the wing root due to static load. Wing root chord, composite ply orientations and wall thickness are used as design variables. A hybrid optimization technique is implemented to simultaneously include continuous and discrete design variables. A refined higher-order theory is used to analyze composite box beam, which represents the load carrying member of the wing. Unsteady aerodynamic computations are performed using a panel code based on the Doublet Lattice Method and flutter/divergence speed is obtained by the V-g method. Numerical results are presented showing significant improvements, after optimization, compared to reference design.

Original language	English (US)
DOIs	https://doi.org/10.2514/6.1996-4015
State	Published - 1996
Event	6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1996 - Bellevue, United States Duration: Sep 4 1996 → Sep 6 1996

Other

Other	6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1996
Country/Territory	United States
City	Bellevue
Period	9/4/96 → 9/6/96

ASJC Scopus subject areas

Aerospace Engineering
Mechanical Engineering

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10.2514/6.1996-4015

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abstract = "A comprehensive procedure has been developed for aeroelastic optimization of composite wings. Wing structural weight is taken as the objective function with constraints on flutter/divergence speed and stresses at the wing root due to static load. Wing root chord, composite ply orientations and wall thickness are used as design variables. A hybrid optimization technique is implemented to simultaneously include continuous and discrete design variables. A refined higher-order theory is used to analyze composite box beam, which represents the load carrying member of the wing. Unsteady aerodynamic computations are performed using a panel code based on the Doublet Lattice Method and flutter/divergence speed is obtained by the V-g method. Numerical results are presented showing significant improvements, after optimization, compared to reference design.",

author = "Aditi Chattopadhyay and Ratneshwar Jha and Charles Seeley",

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AU - Chattopadhyay, Aditi

AU - Jha, Ratneshwar

AU - Seeley, Charles

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N2 - A comprehensive procedure has been developed for aeroelastic optimization of composite wings. Wing structural weight is taken as the objective function with constraints on flutter/divergence speed and stresses at the wing root due to static load. Wing root chord, composite ply orientations and wall thickness are used as design variables. A hybrid optimization technique is implemented to simultaneously include continuous and discrete design variables. A refined higher-order theory is used to analyze composite box beam, which represents the load carrying member of the wing. Unsteady aerodynamic computations are performed using a panel code based on the Doublet Lattice Method and flutter/divergence speed is obtained by the V-g method. Numerical results are presented showing significant improvements, after optimization, compared to reference design.

AB - A comprehensive procedure has been developed for aeroelastic optimization of composite wings. Wing structural weight is taken as the objective function with constraints on flutter/divergence speed and stresses at the wing root due to static load. Wing root chord, composite ply orientations and wall thickness are used as design variables. A hybrid optimization technique is implemented to simultaneously include continuous and discrete design variables. A refined higher-order theory is used to analyze composite box beam, which represents the load carrying member of the wing. Unsteady aerodynamic computations are performed using a panel code based on the Doublet Lattice Method and flutter/divergence speed is obtained by the V-g method. Numerical results are presented showing significant improvements, after optimization, compared to reference design.

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Y2 - 4 September 1996 through 6 September 1996

ER -

Application of hybrid optimization technique for improved aeroelastic performance of composite wings

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