Preliminary Design of Composite Wings for Buckling, Strength, and Displacement Constraints

Starnes, James H.; Haftka, Raphael T.

doi:10.2514/3.58565

Cited by 276 publications

(48 citation statements)

References 3 publications

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“…Thus extensive research efforts have been devoted to the analysis and optimization of composite wing structures in connection with flutter, natural frequency, and flight loads [1][2][3][4][5]. Starnes and Haftka [1] employed a multi-level approach based on the mathematical programming method for designing composite wing structures. The conservative constraint approximation and approximate second derivatives of the penalty terms were used to obtain minimum mass designs.…”

Section: Introductionmentioning

confidence: 99%

Optimal design of composite wing subjected to gust loads

Kim

Hwang

2005

Computers & Structures

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Section: Introductionmentioning

confidence: 99%

Optimal design of composite wing subjected to gust loads

Kim

Hwang

2005

Computers & Structures

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“…In this study, the wingtip deflection for the CRM wing at a 2.5 g pull-up maneuver is assumed to be 15% of the wing semi-span b. This is based on the relative deformations that can be expected in the wing of a transport-category aircraft as a function of the load factor, as presented in the open scientific literature [19,42]. This value also ensures that the aircraft wingtip does not strike the ground during a taxi bump load or landing operation.…”

Section: Static Stiffness Constraintsmentioning

confidence: 99%

“…These techniques resurrected the use of mathematical programming for structural optimization. Starnes, Jr. and Haftka [19] overcame the difficulties in using approximation techniques for some constraints, such as buckling, by introducing the concept of conservative constraint approximations.…”

Section: Introductionmentioning

confidence: 99%

Application of an Efficient Gradient-Based Optimization Strategy for Aircraft Wing Structures

2018

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Abstract:In this paper, a practical optimization framework and enhanced strategy within an industrial setting are proposed for solving large-scale structural optimization problems in aerospace. The goal is to eliminate the difficulties associated with optimization problems, which are mostly nonlinear with numerous mixed continuous-discrete design variables. Particular emphasis is placed on generating good initial starting points for the search process and in finding a feasible optimum solution or improving the chances of finding a better optimum solution when traditional techniques and methods have failed. The efficiency and reliability of the proposed strategy were demonstrated through the weight optimization of different metallic and composite laminated wingbox structures. The results show the effectiveness of the proposed procedures in finding an optimized solution for high-dimensional search space cases with a given level of accuracy and reasonable computational resources and user efforts. Conclusions are also inferred with regards to the sensitivity of the optimization results obtained with respect to the choice of different starting values for the design variables, as well as different optimization algorithms in the optimization process.

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“…It is in nature the Taylor series expansion in terms of reciprocal variables. Starner and Haftka [3] have also shown that a hybrid constraints mixing the direct variables and reciprocal variables can yield a more conservative approximation, which has the advantage of giving convex sub-problem.…”

Section: Introductionmentioning

confidence: 99%

A new three-point approximation approach for design optimization problems

Guo

Yamazaki

Cheng

2001

Int. J. Numer. Meth. Engng.

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In this paper, a newly developed three‐point approximation scheme is proposed. The expression of this scheme consists of a linear combination of the direct and reciprocal linear Taylor expansions as well as of the lumped diagonal terms of the second‐order direct and inverse terms. The unknown parameters of the expression are computed on the basis of the function and gradient values at three points in the design space. Based on this approach, the accuracy of the existing constraint approximation methods can be improved. The effectiveness of the proposed approach is demonstrated on a number of numerical examples. The numerical results are also compared with those of the previously published work. Copyright © 2001 John Wiley & Sons, Ltd.

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Preliminary Design of Composite Wings for Buckling, Strength, and Displacement Constraints

Cited by 276 publications

References 3 publications

Optimal design of composite wing subjected to gust loads

Optimal design of composite wing subjected to gust loads

Application of an Efficient Gradient-Based Optimization Strategy for Aircraft Wing Structures

A new three-point approximation approach for design optimization problems

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