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Manufacturing method of composite material pressure container

A technology for pressure vessels and composite materials, applied in pressure vessels, fixed-capacity gas storage tanks, mechanical equipment, etc., can solve the problems of reducing the overall performance of composite materials and aggravating fiber fracture, so as to maintain stable mechanical properties and reduce fiber fracture rate , the effect of reducing the deformation rate

Inactive Publication Date: 2014-11-26
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Its main disadvantage is that the preset tension in the fiber winding process and the shrinkage of the composite material after curing make the metal lining require a large compressive stress in the self-tightening process to achieve the predetermined plastic deformation, which causes the composite material layer Large expansion deformation also occurs during the self-tightening process, which intensifies fiber fracture and reduces the overall performance of the composite material

Method used

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  • Manufacturing method of composite material pressure container
  • Manufacturing method of composite material pressure container
  • Manufacturing method of composite material pressure container

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0048] Take the 20MPA aluminum-lined carbon fiber full-wound high-pressure gas cylinder as an example. The aluminum lining material is 6061 aluminum alloy, the shape is cylindrical, and the capacity is 120L, 110L and 80 liters. After the lining is heat-treated according to the predetermined plan, the measured Poisson's ratio μ=0.32 and elastic modulus E=70.25GPa.

[0049] Take the wall thickness t=4.5mm uniformly, and the inner diameter R=167mm. It is calculated that the cure shrinkage of the composite material (carbon fiber + epoxy resin) with a glue content of 25% is close to 0.18%, and considering the winding tension of the filaments, the strain ε in formula (3) is taken as 0.2%. Combining formula (1) and formula (2) to solve, it can be obtained that the air should be pre-washed into the aluminum lining to 2.535MPa before winding processing, and the actual value is P 0=2.54MPa. After the inner lining completes the machining process, the frocks 1, 2, 3, 4, 7, etc. in the a...

Embodiment 2

[0051] Take the 35MPA aluminum-lined carbon fiber full-wound high-pressure gas cylinder as an example, with a capacity of 110L and a cylindrical structure of 6061 aluminum alloy. Take wall thickness t=5.0mm, inner diameter R=154mm. Similarly, using the same aluminum alloy heat treatment system, the glue content of the composite material is still 25%, and the curing shrinkage rate is also 0.18%. The actual strain ε in formula (3) is 0.2%. After solving the same formula, it can be obtained that the air should be pre-flushed into the aluminum liner to 3.179MPa before winding processing, and the actual value of P 0 =3.18MPa. After completing the scheduled winding and curing processes, the self-tightening operation is also performed. Compared with the same gas cylinder without stamping operation, the self-tightening pressure of 3MPA is reduced.

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Abstract

The invention relates to a manufacturing method of a composite material pressure container, which comprises the following steps: 1, connecting an inflating and pressure-maintaining tooling with a lining, inflating the lining with air having a certain pressure to enable the lining to be subjected to swelling deformation, and calculating to determine the internal pressure of the inflated metal lining according to a formula; 2, keeping the lining in a pressure-maintaining state, and performing twisting processing of fibrous composite materials; 3, after the twisting operation is finished, transferring into a curing oven, and performing rotary hot curing; and 4, after the curing operation is finished, naturally cooling, and slowly releasing the internal air to relieve the pressure, thereby ensuring that the elastic contraction of the lining counteracts the compression stress in the twisting process and the curing contraction of the composite material and the lining can be peeled and separated from the composite material layer. According to the invention, the internal stress required in the self tightening process can be reduced, and the swelling deformation rate of the composite material layer can be reduced, thereby lowering the fiber breakage rate of the composite material layer and ensuring high overall performance of the composite material.

Description

technical field [0001] The invention relates to a manufacturing method of a composite material pressure vessel, in particular to a manufacturing method of a carbon fiber fully wound metal-lined pressure vessel. Background technique [0002] In the field of composite material pressure vessel manufacturing in China, patents related to this invention include: 03150968.1 "composite material pressure vessel" invented by Zheng Chuanxiang and Cao Kun of Zhejiang University; A dry yarn winding forming method for pressure vessels"; 200510010151.6 "Large-sized, ultra-thin metal-lined composite pressure vessel and its manufacturing method" invented by He Xiaodong and Wang Rongguo of Harbin Institute of Technology; Sinoma Science and Technology ( Suzhou) Co., Ltd. invented 2010102100951.1 "A Method for Manufacturing Pressure Vessels Using Large Tow Carbon Fiber" etc. invented by Wu Feng and Xiao Wengang. These patents all propose the use of composite materials and metal linings to manu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F17C1/06
Inventor 卢敏
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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