Method for preparing composite material through hot-pressing strengthening

A composite material and reinforcement technology, applied in the field of composite material manufacturing, can solve the problems of difficult to meet model product design indicators and mission requirements, sacrificing aircraft payload, and difficult to meet complex limit flight conditions and other problems

Active Publication Date: 2020-10-23
上海航天智能装备有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] As the flight conditions of various new-generation aircraft and missiles become more and more severe, the requirements for mechanical properties such as tensile strength and fatigue strength of the main structural materials continue to increase, and traditional aluminum alloy materials have been difficult to meet the flight requirements

Method used

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  • Method for preparing composite material through hot-pressing strengthening
  • Method for preparing composite material through hot-pressing strengthening
  • Method for preparing composite material through hot-pressing strengthening

Examples

Experimental program
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Effect test

Embodiment

[0051] A device for preparing composite materials by hot pressing, such as Figure 1-3 , the device includes a liner 3, an outer hoop 6 and a high-frequency induction coil 8; the composite material matrix 4 is set outside the liner 3, the composite material reinforcement 5 is laid outside the matrix 4, and the outer hoop 6 is arranged on the reinforcement 5, the high-frequency induction coil 8 is located outside the outer hoop 6. Under the inner and outer support of the lining plate 3 and the outer hoop 6 and the heating environment of the high-frequency induction coil 8, the matrix 4 presses the reinforcement 5 into the semi-solid matrix 4 by applying external pressure to the outer hoop 6. After completion, the purpose of improving the strength and tensile properties of the matrix 4 is achieved.

[0052] The number of lining plates 3 is three, the gap between each lining plate 3 is not more than 0.1mm, and the thickness of the lining plates 3 is not less than the difference be...

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Abstract

The invention relates to a method for preparing a composite material through hot-pressing strengthening. The method comprises the following steps that (1) a base body (4) is machined to the designed size; (2) a lining plate (3) is sleeved with the base body (4), the base body (4) is internally supported and clamped, and then a reinforcing body (5) is laid on the surface of the outer side of the base body (4); (3) the base body (4) on which the reinforcing body (5) is laid is integrally hooped by using an outer side hoop (6), and the fastening torque of the outer side hoop (6) is adjusted through a bolt; (4) a high-frequency induction coil (8) is arranged on the outer side of the outer side hoop (6) to be heated; and (5) cooling is conducted to reach room temperature, and finish machining is performed on the outer molded surface by taking the inner molded surface as a positioning reference to obtain the composite material. Compared with the prior art, the requirement of an aircraft shell for an original material performance of a product is lowered by the method, and a structural part can be strengthened as required in the product level stage by adopting traditional cast magnesium alloy or wrought magnesium alloy.

Description

technical field [0001] The invention relates to the field of composite material manufacturing, in particular to a method for preparing composite materials through hot pressing strengthening. Background technique [0002] In the field of aerospace, the pursuit of lightweight design for aircraft, launch vehicles, and missile products has never stopped. As one of the currently mature and light-density metal materials, magnesium and aluminum alloys are widely used in various types of missile cabins and aircraft cabins. Segment, satellite platform important structural parts products. [0003] As the flight conditions of various new-generation aircraft and missiles become more and more severe, the requirements for mechanical properties such as tensile strength and fatigue strength of the main structural materials continue to increase, and traditional aluminum alloy materials have been difficult to meet the flight requirements of complex limits in some fields. working conditions. ...

Claims

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Application Information

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IPC IPC(8): B29C70/74B29K705/02
CPCB29C70/74B29C70/681B29K2705/02Y02T50/40
Inventor 秦文津周井文任培强肖静文郑方志殷伟刘星金超
Owner 上海航天智能装备有限公司
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