Multilevel optimization in aircraft structural design evaluation

Hansen, Lars U.; Horst, Peter

doi:10.1016/j.compstruc.2007.05.021

Cited by 62 publications

(30 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…This shows that the application of multicriteria optimizations, considering all relevant criteria in a single optimization step, is rare for aircraft structures, especially when it comes to real-world problems with an appropriate level of detail. A two-step, multilevel optimization approach has been shown by [8] for unconventional aircraft structures by using an evolutionary algorithm and a deterministic optimization method to find suitable designs under different design constraints.…”

Section: Nomenclaturementioning

confidence: 99%

Evolutionary Multicriteria Design Optimization of Integrally Stiffened Airframe Structures

Hansen¹,

Häusler²,

Horst³

2008

Journal of Aircraft

Self Cite

View full text Add to dashboard Cite

In industrial practice, innovative structural aircraft design is, on the one hand, driven by several design criteria like static stress, damage tolerance, and stability, and, on the other hand, by new manufacturing methods and materials, which promise beneficial effects on manufacturing costs and weight. Published optimization approaches are mostly based on pure static stress criteria, albeit the important influence of stability and damage tolerance is neglected. This assumption is perilous but significantly simplifies the investigation. The investigation of unconventional designs under consideration of the preceding criteria is challenging because no analytical or handbook solutions are available. This paper introduces an optimization approach based on an evolution strategy, which incorporates multiple criteria by using nonlinear finite-element analyses for stability and a set of linear analyses for damage-tolerance evaluation. To demonstrate the approach, one design investigation is presented for the window area of a generic aircraft fuselage. The definition of dimensions and the choice of an ideal topology define the optimization problem. The chosen fuselage structure uses an integral design with an innovative combination of window and circumferential frame and is investigated with regard to three load cases that represent relevant in-flight conditions derived from global finite-element analyses. NomenclatureA, B, k, C f , n f , K c = Forman coefficients a = crack length a m , b m , m = shape coefficients of the mass mapping function a u , b u = shape coefficients of the deflection mapping function a SIF , b SIF = shape coefficients of the fatigue-response mapping function C feas , D feas = coefficients of the failure mapping function, feasible state C limit , D limit = coefficients of the failure mapping function, limit state d i = design response i E = Young's modulus G I = energy release rate, mode I G II = energy release rate, mode II g = gravitational acceleration K = stress intensity factor K th = stress intensity factor, threshold value N = load cycle n = load factor p = pressure R = stress ratio t = thickness u = longitudinal displacements at the crack surface v = normal displacements at the crack surface w i = weight factor i X i = longitudinal force at the crack tip Y i = normal force at the crack tip d = exponent of the deflection mapping function SIF = exponent of the fatigue-response mapping function = life span = offspring per generation = population size = Poisson's ratio = density

show abstract

Section: Nomenclaturementioning

confidence: 99%

Evolutionary Multicriteria Design Optimization of Integrally Stiffened Airframe Structures

Hansen¹,

Häusler²,

Horst³

2008

Journal of Aircraft

Self Cite

View full text Add to dashboard Cite

show abstract

“…On the other hand, an analytical method based on finite element analysis enables quick structural design modification without much time and cost through comparing between the results of structural test and numerical analysis [7,8]. Many studies on the finite element analysis modeling technology for the honeycomb structure have been conducted in the aerospace industry, and are being used for analytical evaluation [9][10][11]. In the railway vehicle sector, however, few studies have been conducted on the modeling technique.…”

Section: Introductionmentioning

confidence: 99%

The suggestion of the standardized finite element model through the experimental verifications of various railway vehicle structures made of sandwich composites

Shin

Hahn

2011

J Mech Sci Technol

View full text Add to dashboard Cite

“…These components were then optimized using the prescribed interactions, followed by a new global calculation to update the interactions. Hansen and Horst (2008) presented another approach to solve the structural optimization task by dividing the complete task into two separate optimization problems: a sizing task and a topology task although this approach can be better referred as a hybrid strategy where both tasks are performed simultaneously.…”

Section: Introductionmentioning

confidence: 99%

Robust design and optimization of composite stiffened panels in post-buckling

Bacarreza

Aliabadi

Apicella

2014

Struct Multidisc Optim

View full text Add to dashboard Cite

Multilevel optimization including progressive failure analysis and robust design optimization for composite stiffened panels, in which the ultimate load that a post-buckled panel can bear is maximized for a chosen weight, is presented for the first time. This method is a novel robust multiobjective approach for structural sizing of composite stiffened panels at different design stages. The approach is integrated at two design stages labelled as preliminary design and detailed design. The robust multilevel design methodology integrates the structural sizing to minimize the variance of the structural response. This method improves the product quality by minimizing variability of the output performance function. This innovative approach simulates the sequence of actions taken during design and structural sizing in industry where the manufacture of the final product uses an industrial organization that goes from the material characterization up to trade constraints, through preliminary analysis and detailed design. The developed methodology is validated with an example in which the initial architecture is conceived at the preliminary design stage by generating a Pareto front for competing objectives that is used to choose a design with a required weight. Then a robust solution is sought in the neighbourhood of this solution to finally find the layup for the panel capable of bearing the highest load for the given geometry and boundary conditions.

show abstract

Multilevel optimization in aircraft structural design evaluation

Cited by 62 publications

References 5 publications

Evolutionary Multicriteria Design Optimization of Integrally Stiffened Airframe Structures

Evolutionary Multicriteria Design Optimization of Integrally Stiffened Airframe Structures

The suggestion of the standardized finite element model through the experimental verifications of various railway vehicle structures made of sandwich composites

Robust design and optimization of composite stiffened panels in post-buckling

Contact Info

Product

Resources

About