Novel Method Based on Inflatable Bump for Vertical Tail Buffeting Suppression

Zhang, Qing; Ye, Zhengyin

doi:10.2514/1.c032552

Cited by 6 publications

(1 citation statement)

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“…The application field is more and more extensive, which has more and more important research value and engineering application prospects [1][2][3][4][5][6][7]. The most typical was the NASA-I-2000 flexible aerated wing aircraft developed by NASA and conducted low-level flight test development, which technically verified the feasibility of the aerated wing to achieve flight [8][9].…”

Section: Introductionmentioning

confidence: 99%

Research on Influence of Temperature Variation on Deformation of Inflatable Wing Skin Film

Liu¹,

Jiang²,

Peng³

et al. 2018

Proceedings of the 2018 International Conference on Mathematics, Modelling, Simulation and Algorithms (MMSA 2018)

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Abstract-With many advantages of foldable, small size, good portability, easy loading and transportation, rapid deployment, and easy launch, the flexible inflatable wing has attracted the attention of scholars and engineers abroad. However, the ambient temperature variation directly affects the internal pressure of the inflatable wing, which produces significant complex deformation of the wing skin film. In this paper, the influence of different temperature conditions on the pressure change of the flexible inflating wing is studied, and the ABAQUS finite element modeling method is used to simulate the wing skin film under different temperature conditions (25°C, 35°C, 45°C, 55°C). The result shows that strain deformation characteristics and data structure indicate that the strain change of the skin film is closely related to the ambient temperature, and the temperature changes will cause the internal and external pressure difference to increase, and the strain near the wing root and the wing tip will become larger, and the law of strain variation along the spanning characteristic line and the chordwise characteristic line is discussed, which provides an effective reference for the analysis and design of the inflatable mechanical deformation of the flexible inflatable membrane structure (wing).

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Section: Introductionmentioning

confidence: 99%