TY - JOUR
T1 - Multidisciplinary optimization of composite wings using refined structural and aeroelastic analysis methodologies
AU - Jha, Ratneshwar
AU - Chattopadhyay, Aditi
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.
PY - 1999
Y1 - 1999
N2 - An integrated multidisciplinary procedure has been developed for structural and aeroelastic optimization of composite wings based on refined analysis techniques. A refined higher-order theory is used to analyze a composite box beam, which represents the load carrying member of the wing. Unsteady aerodynamic computations are performed using a panel code based on the constant-pressure lifting surface 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 techniques. A refined higher-order theory is used to analyze a composite box beam, which represents the load carrying member of the wing. Unsteady aerodynamic computations are performed using a panel code based on the constant-pressure lifting surface 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 - 10.1080/03052159908941291
DO - 10.1080/03052159908941291
M3 - Article
AN - SCOPUS:0033337739
VL - 32
SP - 59
EP - 78
JO - Engineering Optimization
JF - Engineering Optimization
SN - 0305-215X
IS - 1
ER -