Studies on the influence of spar position on aeroelastic optimization of a large aircraft wing

Wan, Zhiqiang; Liu, Dongyue; Tang, Changhong; Yang, Chao

doi:10.1007/s11431-011-4584-9

Cited by 7 publications

(2 citation statements)

References 6 publications

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“…In this optimization, the plane shape of the wing and the number of spars and ribs remain unchanged, and only the internal layout of the wing are changed. P1 in each group of SpaRibs is a constant 18,19 , the boundary of each other variables is shown in Table 3.…”

Section: Structure and Aerodynamic Modelmentioning

confidence: 99%

Aeroelastic optimization design of SpaRibs wing structure

Zhou

Yang

et al. 2023

Third International Conference on Mechanical Design and Simulation (MDS 2023)

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Traditionally, the internal of aircraft wings is generally straight spars and ribs. The use of curvilinear spars and ribs (SpaRibs) on the wing can greatly broadens the design space and further improve the aeroelastic performance. An aeroelastic comprehensive optimization design method is proposed for flying-wing aircraft with SpaRibs based on genetic algorithm. The supersonic double lattice method is used to calculate the unsteady aerodynamics, and the modal method is used to carry out the static aeroelastic analysis The flutter velocity is optimized by considering the static aerodynamic deformation constraint. A comprehensive optimization design calculation example of a flying wing aircraft shows that the flutter velocity can be increased by 20.34% on the basis of a weight increase of 1.321% for a wing with a SpaRibs structure. It provides a new idea for the system design of the flying wing aircraft structure and project a fast and effective aeroelastic comprehensive optimization design method.

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Section: Structure and Aerodynamic Modelmentioning

confidence: 99%

Aeroelastic optimization design of SpaRibs wing structure

Zhou

Yang

et al. 2023

Third International Conference on Mechanical Design and Simulation (MDS 2023)

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“…With the frozen aerodynamic shape, the structure designs of different phases are carried out. Usually, the structure design of large aircraft wing consists of stiffness design, 7,8 structural layout design, 9 structural size design, 10 and structure design with uncertainties. 11,12 The structural property parameterization is much more convenient in the finite element method.…”

Section: Introductionmentioning

confidence: 99%

Integrated aerodynamics/structure/stability optimization of large aircraft in conceptual design

Wan

Wang

Yang

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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The multidisciplinary design optimization is suitable for modern large aircraft, and it has the potential in conceptual phase of aircraft design especially. An integrated optimization method considering the disciplines of aerodynamics, structure and stability for large aircraft design in conceptual phase is presented. The objective is the minimum stiffness of a beam-frame wing structure subject to aeroelasticity, aerodynamics, and stability constraints. The aeroelastic responses are computed by commercial software MSC. Nastran, and the cruise stability is evaluated by the linear small-disturbance equations. A viscous-inviscid iteration method, which is composed of a computational fluid dynamics tool solving the Euler equations and a viscous correction method, is used for computing the flow over the model. The method ensures effective and rapid computation. In this paper, a complete aircraft model is optimized, and all the responses are computed in the trim condition with a fixed maximum takeoff weight. Genetic algorithm is utilized for global optimizations, and the optimal jig shape, the elastic axis positions and the stiffness distribution can be attained adequately. The results show that the method has a value of application in engineering optimizations. For the satisfaction of the total drag and stability constraints, the structure weight usually needs a price to pay. The integrated optimization captures the tradeoff between aerodynamics, structure and stability, and the repeated design can be avoided.

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