TY - GEN
T1 - MULTIDISCIPLINARY OPTIMIZATION OF COMPOSITE WINGS USING REFINED STRUCTURAL AND AEROELASTIC ANALYSIS METHODOLOGIES
AU - Chattopadhyay, Aditi
AU - Jha, Ratneshwar
N1 - Funding Information:
The authors acknowledge the support of this research through a grant from NASA Ames Research Center, Grant number NAG2-908, Technical monitor. Dr. Hirokazu Miura.
Publisher Copyright:
© 1997 American Society of Mechanical Engineers (ASME). All rights reserved.
PY - 1997
Y1 - 1997
N2 - An integrated multidisciplinary procedure has been developed for structural and aeroelastic optimization of composite wings based on refined analysis technique. 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. Flutter/divergence dynamic pressure is obtained by the Laplace domain method through rational function approximation of unsteady aerodynamic loads. The objective of the optimization procedure is to minimize wing structural weight with constraints on flutter/divergence speed and stresses at the root due to the static load. Composite ply orientations and laminate thicknesses are used as design variables. The Kreisselmeier-Steinhauser function approach is used to efficiently integrate the objective function and constraints into a single envelope function. The resulting unconstrained optimization problem is solved using the Davidon-Fletcher-Powell algorithm. Numerical results are presented showing significant improvements, after optimization, compared to a reference design.
AB - An integrated multidisciplinary procedure has been developed for structural and aeroelastic optimization of composite wings based on refined analysis technique. 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. Flutter/divergence dynamic pressure is obtained by the Laplace domain method through rational function approximation of unsteady aerodynamic loads. The objective of the optimization procedure is to minimize wing structural weight with constraints on flutter/divergence speed and stresses at the root due to the static load. Composite ply orientations and laminate thicknesses are used as design variables. The Kreisselmeier-Steinhauser function approach is used to efficiently integrate the objective function and constraints into a single envelope function. The resulting unconstrained optimization problem is solved using the Davidon-Fletcher-Powell algorithm. Numerical results are presented showing significant improvements, after optimization, compared to a reference design.
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U2 - 10.1115/IMECE1997-0168
DO - 10.1115/IMECE1997-0168
M3 - Conference contribution
AN - SCOPUS:85126935300
T3 - ASME International Mechanical Engineering Congress and Exposition, Proceedings (IMECE)
SP - 175
EP - 183
BT - 4th International Symposium on Fluid-Structure Interactions, Aeroelasticity, Flow-Induced Vibration and Noise
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME 1997 International Mechanical Engineering Congress and Exposition, IMECE 1997 - 4th International Symposium on Fluid-Structure Interactions, Aeroelasticity, Flow-Induced Vibration and Noise
Y2 - 16 November 1997 through 21 November 1997
ER -