A Numerical Method for Cost-Weight Optimisation of Stringer-Skin Panels

Curran, Richard; Rothwell, A.; Castagne, Sylvie

doi:10.2514/6.2004-2018

Cited by 12 publications

(12 citation statements)

References 15 publications

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“…Their review article gives a broad overview of what has been done within cost estimation [15]. They also described how DOC was simplified for optimization purposes [16]. The quantification of the weight penalty, however, is not simple, as the effect of weight reductions depends on the perspective in which the methodology is used.…”

Section: Introductionmentioning

confidence: 99%

Integrated cost/weight optimization of aircraft structures

Kaufmann

Zenkert

Wennhage

2009

Struct Multidisc Optim

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PostprintThis is the accepted version of a paper published in Structural and multidisciplinary optimization (Print). This paper has been peer-reviewed but does not include the final publisher proof-corrections or journal pagination.Citation for the original published paper (version of record):Kaufmann, M., Zenkert, D., Wennhage, P. (2010) Integrated cost/weight optimization of aircraft structures. July 2007A methodology for a combined cost/weight optimization of aircraft components is proposed. The objective function is formed by a simplified form of direct operating cost, i.e. by a weighted sum of the manufacturing cost and the component weight. Hence, the structural engineer can perform the evaluation of a design solution based on economical values rather than pure cost or weight targets. The parameter that governs the balance between manufacturing cost and weight is called weight penalty and incorporates the effect of fuel burn, environmental impact or contractual penalties due to overweight. Unlike previous work, the analytical cost and structural models are replaced by commercially available software packages. They allow for a more realistic model of the manufacturing cost, and for arbitrary constraints in the structural analysis. By means of parametric studies it is shown that the design solution strongly depends on the magnitude of the weight penalty.

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Section: Introductionmentioning

confidence: 99%

Integrated cost/weight optimization of aircraft structures

Kaufmann

Zenkert

Wennhage

2009

Struct Multidisc Optim

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“…A previous analysis of T-stringer panels has shown that the choice of objective function is crucial (Curran et al 2006). Very different results for the design parameters were obtained according to the objective function, and the minimum weight condition was found not to be the optimal solution from a minimum life cycle cost point of view.…”

Section: Definition Of the Objective Functionmentioning

confidence: 96%

“…It is composed of two terms: the acquisition cost (AC) and the fuel burn (FB), the acquisition cost being the manufacturing cost (MFC) multiplied by a weight factor n. For the majority of the flight sectors, the acquisition cost contributes two to four times more than the cost of fuel burn to the DOC. In keeping with the panel sizes addressed in the paper, it was shown that a 50% weighting for acquisition cost and 15% weighting for fuel burn is reasonable for the DOC split for an aircraft in the regional aircraft sector (Curran et al 2006). Consequently, the factor n was determined by fitting the cost results for a panel traditionally optimised for weight and the above mentioned percentage.…”

Section: Life Cycle Cost Modellingmentioning

confidence: 99%

“…The structural analysis for inverted T-stringer panels has been described by Curran et al (2006). The present paper focuses on Z-stringer panels with chemi-milled pockets.…”

Section: Structural Analysismentioning

confidence: 99%

“…The manufacturing cost model is developed using the genetic-causal method as described by Curran et al (2006), where each cost element is computed in relation to its main cost drivers, these being linked to particular genetic identifiers relating to materials, processes and forms. The cost elements can be anything that incurs a cost such as a part or an assembly operation.…”

Section: Development Of the Manufacturing Cost Modelmentioning

confidence: 99%

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A generic tool for cost estimating in aircraft design

et al. 2008

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A methodology to estimate the cost implications of design decisions by integrating cost as a design parameter at an early design stage is presented. The model is developed on a hierarchical basis, the manufacturing cost of aircraft fuselage panels being analysed in this paper. The manufacturing cost modelling is original and relies on a genetic-causal method where the drivers of each element of cost are identified relative to the process capability. The cost model is then extended to life cycle costing by computing the Direct Operating Cost as a function of acquisition cost and fuel burn, and coupled with a semiempirical numerical analysis using Engineering Sciences Data Unit reference data to model the structural integrity of the fuselage shell with regard to material failure and various modes of buckling. The main finding of the paper is that the traditional minimum weight condition is a dated and sub-optimal approach to airframe structural design.

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Research on the Optimization Model of Aircraft Structure Design for Cost

Shan-shan

Wei

Global Design to Gain a Competitive Edge

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A Numerical Method for Cost-Weight Optimisation of Stringer-Skin Panels

Cited by 12 publications

References 15 publications

Integrated cost/weight optimization of aircraft structures

Integrated cost/weight optimization of aircraft structures

A generic tool for cost estimating in aircraft design

Research on the Optimization Model of Aircraft Structure Design for Cost

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