Development and application of the integrated structural design tool LAGRANGE

Schweiger, Johannes; Krammer, J.; Hoernlein, H.

doi:10.2514/6.1996-4169

Cited by 14 publications

(3 citation statements)

References 6 publications

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“…The structural analysis and optimisation package Lagrange is an EADS-M in-house development designed prima rily for optimisation tasks [11]. The package allows optimisation of Finite Element structural models including treatment of buckling static (stress and displacement), dynamics (both in time and frequency domain), static and dynamic aeroelastic and calculation of analytical sensitivities in consideration of manufacturing restrictions.…”

Section: The Structural Analysis Code Mbb-lagrangementioning

confidence: 99%

Time-dependent aeroelastic simulation of rapid manoeuvring aircraft

Fornasier¹,

Rieger²,

Tremel³

et al. 2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

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This paper presents the aeroelastic-related computational activity performed by the EADS-M team in the ESPRIT Project EP25050 JULIUS. The main objective of the JULIUS project was the development of 6S, a Problem Solving Environment, designed to provide an integration platform for software modules required to simulate complex, large scale, industrial problems. As part of the industrial demonstrator suite defined to assess 6S capabilities when performing large scale, multi-physics comp utational simulation, EADS-M has simulated the fluid-structure interaction during rapid aircraft flight manoeuvres at transonic conditions by use of an advanced, time-accurate CFD-CSM coupling methodology. The aerodynamic modelling, elastomechanical modelling and the temporal and spatial coupling algorithms implemented in this approach are presented. The solution of the unsteady Euler equations for transient flow involving moving boundaries for realistic 3-D configurations is computationally expensive. Use of highly parallel computers is one of the ways for reducing the run times. The design of the coupling procedure and its components has been driven by computational efficiency requirements on parallel, distributed memory architecture machines, resulting in a highly efficient implementation which can utilise today's high performance computing resources. The paper addresses the computational issues. Finally, the results obtained from the simulation of a 5-g pull-up manoeuvre for a generic X-31-Experimental Aircraft Configuration are presented. Nomenclature C D aerodynamic drag coefficient C L aerodynamic lift coefficient p/p ∞ dimensionless pressure coefficient q generalised coordinate

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Section: The Structural Analysis Code Mbb-lagrangementioning

confidence: 99%

Time-dependent aeroelastic simulation of rapid manoeuvring aircraft

Fornasier¹,

Rieger²,

Tremel³

et al. 2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

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show abstract

“…The number of design variables that can be optimised is in excess of 100,000 [1]. For the optimization design of structures with large-scale variables, optimization tools such as Dassault's ELFINI [2] and Airbus's LAGRANGE [3] have been developed which play an important role during the design and manufacture processes of aircraft structures. However, the usage of these tools is restricted by special rules and procedures.…”

Section: Introductionmentioning

confidence: 99%

An analytical sensitivity theory-based optimization method for composite structures with large-scale variables

Luo¹,

Guo²,

Nie³

2022

J. Phys.: Conf. Ser.

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This research focusses on large-scale variable optimization techniques for commercial composite wing structures. To achieve a more complete set of results, the layer thickness for composite layers with the same material and ply direction, are set as a design variable in this study. An analytical approach was utilized to deal with the sensitivity analysis so as to study the relationship between displacement, stress and strain constraints. In order to improve the applicability and user-friendliness, the procedure of sensitivity analysis has been programmed within Fortran and integrated into a Computer-Aided Engineering (CAE) software named HAJIF. To compare the consistency and efficiency, the analytical sensitivity calculation method, along with the finite difference method and a semi-analytical method, were employed to optimise a composite aircraft wing structure. The analytical method was found to have the best consistency and efficiency amongst the three optimization methods. With the aid of HAJIF, the wing was optimized with a weight loss ratio of 8.9%. The total optimization time was is 56 times quicker than the finite difference method and semi-analytical method.

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“…For example, Adeli's group has attempted solution of such problems using concurrent and distributed genetic algorithms 1,4 in workstation cluster 15 and in massively parallel supercomputers. 3,36 The design tools Lagrange 14,37 and ASTROS 12 have been used for design of aircraft structures. The MSC/NASTRAN 18 code can be used for design optimization of structural components.…”

Section: Introductionmentioning

confidence: 99%

Substructuring for Structural Optimization in a Parallel Processing Environment

Patnaik

Coroneos

Hopkins

2000

Computer aided Civil Eng

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Design optimization of large structures can be attempted through a substructure strategy. In this strategy, the structure is divided into smaller substructures that are clustered to obtain a sequence of subproblems. Solution to the large problem is obtained iteratively through repeated solutions to the modest subproblems. Substructure strategies, in sequential and parallel computational environments on a Cray-YMP computer, have been implemented in a design test bed CometBoards. The issues encountered during substructure solution and their resolution are discussed under (1) coupling and constraint formulation, (2) differences in optimal solutions, and (3) amount of computation. Coupling between subproblems and separating constraints into local and global sets promote convergence of the iterative process. The substructure strategy can converge to different local optimal designs with equal minimum weight. Substructure optimization can be computation-intensive. However, in a parallel computational mode, it can effectively use assigned processors.

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Development and application of the integrated structural design tool LAGRANGE

Cited by 14 publications

References 6 publications

Time-dependent aeroelastic simulation of rapid manoeuvring aircraft

Time-dependent aeroelastic simulation of rapid manoeuvring aircraft

An analytical sensitivity theory-based optimization method for composite structures with large-scale variables

Substructuring for Structural Optimization in a Parallel Processing Environment

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