A hybrid multilevel approach for aeroelastic optimization of composite wing-box

The quest for finding optimum solutions to engineering problems has been existing for a long time. In the last decade several optimization techniques have been applied to the structural design of composite wing structures. Generally many of these proposed procedures have dealt with different disciplines such as aerodynamics, structures, or dynamics separately. However an aeronautical design process is multidisciplinary since it involves strong couplings and interactions among, for instance, aerodynamics, dynamics, flight mechanics and structures. The main problem in a multidisciplinary aircraft design is usually the development of an efficient method to integrate structures or structural properties, which can be considered both as “global” and “local” design variables. This paper describes an integrated aerodynamic / dynamic / structural optimization procedure for a composite wing-box design. The procedure combines an aeroelastic optimization of a composite wing based on a general purpose optimizer such as the Sequential Quadratic Programming (SQP) and a composite optimization using Genetic Algorithm (GA). Both the optimizations are implemented through a hybrid multilevel decomposition technique.

[1]  Paolo Gasbarri,et al.  A Comparative Overview of Strain Actuated Surfaces' Design , 1997 .

[2]  R. Haftka,et al.  Elements of Structural Optimization , 1984 .

[3]  P. Gasbarri,et al.  Structural Dynamics of a Cantilever Wing-Like Anisotropic Swept Plate , 2000 .

[4]  J. Sobieszczanski-Sobieski,et al.  Structural optimization by multilevel decomposition , 1983 .

[5]  L Walsh Joanne,et al.  Integrated Aerodynamic/Dynamic/Structural Optimization of Helicopter Rotor Blades Using Multilevel Decomposition , 2003 .

[6]  Zbigniew Michalewicz,et al.  Genetic Algorithms + Data Structures = Evolution Programs , 1996, Springer Berlin Heidelberg.

[7]  Augustine R. Dovi,et al.  Multilevel Decomposition Approach to the Preliminary Sizing of a Transport Aircraft Wing , 1988 .

[8]  John C. Halpin,et al.  Primer on Composite Materials Analysis , 1984 .

[9]  P. Santini,et al.  Lifting Surface in Subsonic Unsteady Regime , 1999 .

[10]  John H. Holland,et al.  Adaptation in Natural and Artificial Systems: An Introductory Analysis with Applications to Biology, Control, and Artificial Intelligence , 1992 .

[11]  Gilbert Syswerda,et al.  Uniform Crossover in Genetic Algorithms , 1989, ICGA.

[12]  Juan Pablo Leiva,et al.  A New Approach in Stacking Sequence Optimization of Composite Laminates Using GENESIS Structural Analysis and Optimization Software , 2002 .

[13]  Peter Spellucci,et al.  An SQP method for general nonlinear programs using only equality constrained subproblems , 1998, Math. Program..

[14]  Kok Lay Teo,et al.  Optimization methods and applications , 2001 .

[15]  Michael Kost,et al.  CONVERGENCE OF SQP-TYPE METHODS OF FEASIBLE DIRECTIONS , 2001 .

[16]  H. Gea,et al.  Optimal orientation of orthotropic materials using an energy based method , 1998 .

[17]  J. Sobieszczanski-Sobieski.  Two alternative ways for solving the coordination problem in multilevel optimization , 1993 .

[18]  Nielen Stander,et al.  The genetic algorithm applied to stiffness maximization of laminated plates: review and comparison , 1998 .

[19]  David E. Goldberg,et al.  Genetic Algorithms in Search Optimization and Machine Learning , 1988 .

[20]  David A. Peters,et al.  Optimization of rotor blades for combined structural, dynamic, and aerodynamic properties , 1992 .

[21]  D. E. Goldberg,et al.  Genetic Algorithms in Search , 1989 .

[22]  Michael M. Kostreva,et al.  A superlinearly convergent method of feasible directions , 2000, Appl. Math. Comput..