Preparation mould of carbon fiber composite material casing of airplane and aircraft and forming method thereof

A composite material and aircraft technology, applied in the field of winding carbon fiber composite material manufacturing, can solve the problems affecting the performance of the shell, fiber breakage, etc., and achieve the effect of reducing weight

Inactive Publication Date: 2010-10-27
HARBIN INST OF TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0013] The purpose of the present invention is to solve the problem that the existing aircraft and aircraft shells formed by continuous fiber winding will break the fibers and affect the perform

Method used

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  • Preparation mould of carbon fiber composite material casing of airplane and aircraft and forming method thereof
  • Preparation mould of carbon fiber composite material casing of airplane and aircraft and forming method thereof
  • Preparation mould of carbon fiber composite material casing of airplane and aircraft and forming method thereof

Examples

Experimental program
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Effect test

Example Embodiment

[0032] Specific implementation mode 1: the following combination Figure 1 to Figure 6 To describe this embodiment, this embodiment is composed of a core 1, an inner mold 2, an outer mold 3, an upper cover plate 5, a lower cover plate 6 and a shaft 7.

[0033] The mold core 1 has a circular table outer surface and a hollow structure. The inner mold 2 is sleeved on the side surface of the outer surface of the mold core 1 and is tightly fixed. The outer ring surface of the inner mold 2 has a plurality of annular grooves 2-1 , The plurality of annular grooves 2-1 are parallel to each other, and are all parallel to the bottom surface of the mold core 1,

[0034] An outer mold 3 is arranged outside the inner mold 2. The outer mold 3 is coaxial with the inner mold 2. The pressure sleeve 4 has a circular table side wall, the upper end surface is an inwardly protruding ring, and the lower end surface is an outwardly protruding ring. The pressure sleeve 4 is sleeved on the outer surface of...

Example Embodiment

[0041] Embodiment 2: The difference between this embodiment and Embodiment 1 is that the inner mold 2 is assembled from 12 identical longitudinal inner mold pieces. Other components and connection relationships are the same as in the first embodiment.

[0042] In this embodiment, 12 identical longitudinal inner mold pieces are used to assemble the inner mold 2 so that the inner mold 2 is easily disassembled during use.

Example Embodiment

[0043] Specific embodiment three: This embodiment is different from the first embodiment in that the material of the outer mold 3 is aluminum alloy. Other components and connection relationships are the same as in the first embodiment.

[0044] The outer mold 3 made of aluminum alloy can be used repeatedly, and its inner surface is dense and smooth, which can meet the requirements of the surface flatness of the formed shell.

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Abstract

The invention discloses a preparation mould of a carbon fiber composite material casing of an airplane and an aircraft and a forming method thereof, belonging to the field of winding carbon fiber composite material preparation and solving the problem that the traditional airplane and aircraft casing formed by winding a continuous fiber is provided with process holes after formed, so that the fiber is fractured to influence the performance of the casing. In the preparation mould, a mould core is fixed with an inner mould; a plurality of annular clamping grooves are arranged on the outer ring surface of the inner mould; an outer mould is coaxial with the inner mould; a pressurizing sleeve is sleeved outside the outer mould; an upper cover plate is fixed with the mould core and the inner mould; a lower cover plate is fixed with the mould core, the inner mould and the pressurizing sleeve; a shaft passes through center holes of the upper cover plate and the lower cover plate and is fixed with the upper cover plate; the space among the outer mould, the upper cover plate, the lower cover plate and the inner mould is a forming space; and the forming process of the casing comprises the following steps of: winding a longitudinal rib and an annular rib on the mould, flattening, reinforcing and flattening; longitudinally, annularly and spirally winding the casing; and pressurizing and then curing by adopting a curing furnace. The invention is used for casings of formed airplanes and aircrafts.

Description

technical field [0001] The invention relates to a mold for preparing a carbon fiber composite material shell of an aircraft and an aircraft and a forming method thereof, belonging to the field of winding carbon fiber composite material manufacturing. Background technique [0002] With the development of aircraft and aircraft technology, in order to meet the accuracy requirements of range, speed and maneuverability, the structural size and quality requirements of its components are getting higher and higher. At present, lightweight has become an important trend in the development of aircraft and aircraft. Efforts to carry out research and application of advanced composite materials have become one of the important means of lightweight aircraft and aircraft. Compared with other materials, fiber-reinforced polymer composites have become one of the important ways to reduce the weight of aircraft and aircraft shells because of their high specific strength and specific modulus. ...

Claims

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Application Information

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IPC IPC(8): B29C70/54B29C70/34
Inventor 陈玉勇常小平李地红张东兴朱洪艳吴宝昌
Owner HARBIN INST OF TECH
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