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A Gradient Distributed Reinforced Cylindrical Shell Structure

A distributed and reinforced technology, applied in aerospace equipment, aerospace equipment, spacecraft propulsion system devices, etc., can solve the problems of low reinforcement efficiency and small design space, and achieve simple and excellent manufacturing process Stiffness distribution, the effect of increasing the structure optimization space

Active Publication Date: 2019-01-01
DALIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to propose a new size-layout synergistically distributed reinforced shell in order to improve its shortcomings of low reinforcement efficiency and small design space for the traditional equal-size-equal-layout reinforced shell structure scheme configuration to achieve the purpose of improving the load-carrying performance of the reinforced shell

Method used

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  • A Gradient Distributed Reinforced Cylindrical Shell Structure
  • A Gradient Distributed Reinforced Cylindrical Shell Structure
  • A Gradient Distributed Reinforced Cylindrical Shell Structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] Referring to Fig. 2(a), the vulnerable area 1 such as sudden change in stiffness of the cylindrical shell structure is the action area of ​​the concentrated force condition. With this area as the center of symmetry, gradient distributed reinforcement 3 is arranged on the skin 2 along the circumferential direction. The reinforced section shape is rectangular and the material property is composite. The gradient distribution description method followed by the reinforcement is an exponential function, that is, the size of the i-th reinforcement compared to the i-1-th reinforcement (including variables such as web height and web thickness) and layout information (i.e. The distance between the strip and the reference rib) shows an exponential function change trend, where i=1,2,...,N.

Embodiment 2

[0028] Referring to Fig. 3(a), the vulnerable area 1 such as sudden change in rigidity of the cylindrical shell structure is a weld seam, and with this area as the center of symmetry, gradient distributed reinforcement 3 is arranged on the skin 2 along the circumferential direction. The reinforced section shape is T-shaped, and the material property is metal aluminum alloy. The gradient distribution description method followed by the reinforcement is a sine function, and the size of the i-th reinforcement compared to the i-1th reinforcement (including web height, web thickness, flange width, flange thickness, etc. variable) and the layout information (that is, the distance between the rib and the reference rib) have a sinusoidal function variation trend, where i=1, 2,...,N.

Embodiment 3

[0030] Referring to Fig. 4(a), the vulnerable area 1 such as the abrupt change in rigidity of the cylindrical shell structure is a weakening groove, and with this area as the center of symmetry, gradient distributed reinforcement 3 is arranged on the skin 2 along the axial direction. The shape of the reinforced section is rectangular, and the material property is metal aluminum alloy. The gradient distribution description method followed by the reinforcement is a linear function, that is, the size of the i-th reinforcement compared to the i-1-th reinforcement (including variables such as web height and web thickness) and layout information (i.e. The distance between the strip and the reference rib) shows a linear function change trend, where i=1, 2,...,N.

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Abstract

The invention relates to the field of aerospace primary load bearing thin-walled component design and provides a gradient distribution type rib barrel shell structure. According to the gradient distribution type rib barrel shell structure, gradient distribution type ribs are rationally arranged in a barrel shell stiffness mutation area and other vulnerable areas, so that the overall stiffness of the structure is more evenly distributed, extension of local buckling deformation of the stiffness mutation area and the other vulnerable areas is effectively restrained, the stress concentration destruction phenomenon is reduced, and the bearing capacity of the barrel shell structure is ultimately improved; the number, the size and the layout information of the gradient distribution type ribs are determined according to the diameter, the height and the thickness of the barrel shell structure; the reinforcing efficiency of the stiffness mutation barrel shell structure can be remarkably improved, and the barrel shell structure is simple in process and can be produced on a large scale.

Description

technical field [0001] The invention relates to the design field of main load-bearing thin-walled components in aerospace, in particular to a gradient distributed reinforced cylindrical shell structure. Background technique [0002] Due to its high specific stiffness and specific strength, the reinforced shell structure is widely used in aerospace structures such as fuel tanks and interstage sections of launch vehicles. According to the loading conditions of the rocket body structure during service, the axial compression load is the main loading condition of the reinforced shell structure. Under axial compression conditions, the main failure mode of the reinforced cylindrical shell structure is buckling instability, including overall structural instability, local skin instability, rib local instability and material plastic instability. The optimal design scheme for the reinforced cylindrical shell structure is equal-strength design, that is, the above-mentioned instability ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/22B64G1/40
CPCB64G1/22B64G1/402
Inventor 王博田阔郝鹏张可朱天宇赵海心杜凯繁李玉韦
Owner DALIAN UNIV OF TECH
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