Mass estimation of transport aircraft wingbox structures with a CAD/CAE-based multidisciplinary process

Hürlimann, Florian; Kelm, Roland; Dugas, Michael; Oltmann, Kim; Kress, Gerald

doi:10.1016/j.ast.2010.08.005

Cited by 53 publications

(40 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…CAA has the highest customizability and CAA, C++ and API provides better interface, but the comparably complicated program language are the main reasons why CAA is often dismissed in favor of Visual Basic (VBScripts) [14,15]. Although the function of VBScript is less powerful than that of CAA, it has a low development difficulty and is easily understood, and more importantly it could fully meet the functional requirements of aircraft structural rapid modeling.…”

Section: Development Platform and Toolmentioning

confidence: 99%

“…X-axis points toward the tail from aircraft head, Y-axis points toward the left or right of "External References" or "External Parameters" in order to build the detailed model. [14,15]. Although the function of VBScript is less powerful than that of CAA, it has a low development difficulty and is easily understood, and more importantly it could fully meet the functional requirements of aircraft structural rapid modeling.…”

Section: Aircraft Wing Structure Definitionmentioning

confidence: 99%

See 1 more Smart Citation

Rapid Design Method and System Development for Aircraft Wing Structure

Tang¹,

Jing²,

Mingqiang³

2016

International Journal of Aeronautical and Space Sciences

View full text Add to dashboard Cite

This work is mainly done by too many manual operations in the aircraft structure design process resulting in heavy workload, low efficiency and quality, non-standardized processes and procedures. A top-down associated design method employing the template parametric technology is proposed here in order to improve the quality of design and efficiency of aircraft wing structure at the preliminary design stage. The appropriate parametric tool is chosen and the rapid design system of knowledgedriven aircraft wing structure is developed. First, a skeleton model of aircraft wing structure is rapidly built up through the template encapsulated design knowledge. Associated design is then introduced to realize the association between the typical structural part and skeleton model. Finally, the related elements are referenced from skeleton model, and a typical structural part reflecting an automatic response for design changes of the upstream skeleton model is quickly constructed within the template. The rapid design system proposed and developed in this paper is able to formalize the design standardization of aircraft wing structure and thus the rapid generation of different aircraft wing structure programs and achieve the structural design knowledge reuse as well.

show abstract

Section: Development Platform and Toolmentioning

confidence: 99%

Section: Aircraft Wing Structure Definitionmentioning

confidence: 99%

Rapid Design Method and System Development for Aircraft Wing Structure

Tang¹,

Jing²,

Mingqiang³

2016

International Journal of Aeronautical and Space Sciences

View full text Add to dashboard Cite

show abstract

“…The structural analysis is performed for the load cases listed in Table 5. Fatigue is simulated by limiting the stress in the wing box lower panel to 42% of the maximum allowable stress of the material in a 1.3g gust load case (Hürlimann et al 2011). The aircraft rolling moment due to aileron deflection (L δ ) in the critical roll case is limited to be higher or equal to L δ of the initial aircraft.…”

Section: Test Case Applicationmentioning

confidence: 99%

Concurrent wing and high-lift system aerostructural optimization

Kieboom

Elham

2017

Struct Multidisc Optim

View full text Add to dashboard Cite

A method is presented for concurrent aerostructural optimization of wing planform, airfoil and high lift devices. The optimization is defined to minimize the aircraft fuel consumption for cruise, while satisfying the field performance requirements. A coupled adjoint aerostructural tool, that couples a quasi-three-dimensional aerodynamic analysis method with a finite beam element structural analysis is used for this optimization. The Pressure Difference Rule is implemented in the quasi-three-dimensional analysis and is coupled to the aerostructural analysis tool in order to compute the maximum lift coefficient of an elastic wing. The proposed method is able to compute the maximum wing lift coefficient with reasonable accuracy compared to high-fidelity CFD tools that require much higher computational cost. The coupled aerostructural system is solved using the Newton method. The sensitivities of the outputs of the developed tool with respect to the input variables are computed through combined use of the chain rule of differentiation, automatic differentiation and coupled-adjoint method. The results of a sequential optimization, where the wing shape and high lift device shape are optimized

show abstract

“…(16) and the loads assigned to these nodes are calculated by substituting λ, λ x , and λ z into Eq. (15). Allocate each load into the finite element notes by this method.…”

Section: (12)mentioning

confidence: 99%

“…This method was studied by many scholars, such as Droegkamp [12], Bindolino [13], Laban [14], Hurlimann [15], and Sensmeier [16]. Such methods are generally based on finite element analysis to size the various components of the primary structure and compute their weight with material density and volume information [10].…”

Section: Introductionmentioning

confidence: 99%

Wing weight estimation considering constraints of structural strength and stiffness in aircraft conceptual design

Chen¹,

Mingqiang²,

Zhong³

et al. 2014

International Journal of Aeronautical and Space Sciences

View full text Add to dashboard Cite

According to the requirement of wing weight estimation and frequent adjustments during aircraft conceptual design, a wing weight estimation method considering the constraints of structural strength and stiffness is proposed to help designers make wing weight estimations rapidly and accurately. This method implements weight predictions on the basis of structure weight optimization with stiffness constraints and strength constraints, which include achievement of wing shape parametric modeling, rapid structure layout, finite element (FE) model automated generation, load calculation, structure analysis, weight optimization, and weight computed based on modeling. A software tool is developed with this wing weight estimation method. This software can realize the whole process of wing weight estimation with the method and the workload of wing weight estimation is reduced because much of the work can be completed by the software. Finally, an example is given to illustrate that this weight estimation method is effective.

show abstract

Mass estimation of transport aircraft wingbox structures with a CAD/CAE-based multidisciplinary process

Abstract: Mass Estimation of Transport Aircraft Wingbox Structures with a CAD/CAE-Based Multidisciplinary Process

Cited by 53 publications

References 9 publications

Rapid Design Method and System Development for Aircraft Wing Structure

Rapid Design Method and System Development for Aircraft Wing Structure

Concurrent wing and high-lift system aerostructural optimization

Wing weight estimation considering constraints of structural strength and stiffness in aircraft conceptual design

Contact Info

Product

Resources

About