Kinetic locus design for longitudinal stretch forming of aircraft skin components

Multi-point stretch forming (MPSF) is a new technique to form aircraft outer skin panel. Since multi-point die is composed by the discrete punches, the result of the MPSF aircraft outer skin panel need to study in depth. The thickness of elastic cushion and free length are two important factors to affect the accuracy, and they must be chosen reasonably. A series of numerical simulations on typical MPSF processes were carried out to an aircraft outer skin panel part. The results show that the thicker the elastic cushion is, the more valid the dimple will be suppressed .The longer free length is, the smaller the equivalent strain and thinning and more uniform the distribution of thickness will be. When the free length is shorter, the degree of effect is relatively obvious on the equivalent strain and thinning and the distribution of thickness; when the free length is longer than a certain value, the degree of effect is small.

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Optimization on springback reduction in cold stretch forming of titanium-alloy aircraft skin

Transactions of Nonferrous Metals Society of China ◽

10.1016/s1003-6326(10)60654-1 ◽

2010 ◽

Vol 20 (12) ◽

pp. 2350-2357 ◽

Cited By ~ 12

Author(s):

De-hua HE ◽

Dong-sheng LI ◽

Xiao-qiang LI ◽

Chao-hai JIN

Keyword(s):

Titanium Alloy ◽

Stretch Forming ◽

Aircraft Skin ◽

Springback Reduction

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Analysis of designs of modern stretch-forming dies for lineforming aircraft skin

10.18411/lj-04-2019-238 ◽

2019 ◽

Author(s):

E.G. Karpukhin ◽

G.L. Rivin ◽

A.A. Fedorov ◽

Yu.V. Zhukova

Keyword(s):

Stretch Forming ◽

Aircraft Skin

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Aircraft Skin Stretch-Forming Die Light-Weight Design Using Topology Optimization

Materials Science Forum ◽

10.4028/www.scientific.net/msf.697-698.600 ◽

2011 ◽

Vol 697-698 ◽

pp. 600-603 ◽

Cited By ~ 1

Author(s):

Ji Hong Zhu ◽

H. Wang ◽

W.H. Zhang ◽

X.J. Gu

Keyword(s):

Numerical Simulation ◽

Topology Optimization ◽

Topology Design ◽

Surface Load ◽

Light Weight ◽

Stretch Forming ◽

Weight Design ◽

Aircraft Skin ◽

Skin Stretch ◽

Skin Stretch Forming

The purpose of this paper is to use the topology optimization method to solve the light-weight design problem of large aircraft skin stretch-forming die. The platform of ABAQUS is firstly used for numerical simulation of skin stretch-forming. And the surface load conditions are therefore obtained. The topology optimization is carried out accordingly to maximize the structural stiffness with the material properties and the boundary conditions properly defined. Referring to the obtained topology design, the optimal structure is reconstructed and then evaluated by the non-linear numerical simulation of stretch-forming. Compared with the traditional design, the numerical results have shown that the topology design can improve the stiffness and strength of the stretch-forming die significantly.

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