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Multi-layer splicing forming method for honeycomb

A molding method and technology of honeycomb interlayer, which is applied in the field of honeycomb multi-layer splicing and molding, can solve the problems that cannot meet the requirements of honeycomb sandwich structural parts, and achieve the effect of good appearance quality, meeting the requirements of stiffness and weight, and simple operation

Active Publication Date: 2017-09-19
哈尔滨哈飞航空工业有限责任公司
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  • Claims
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Problems solved by technology

[0004] Aiming at the shortcomings that the existing technology for preventing honeycomb shrinkage and deformation cannot satisfy the forming of large-thickness and large-angle honeycomb sandwich structures, the present invention formulates a method for splicing and forming honeycomb clad layers. Anti-stress

Method used

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  • Multi-layer splicing forming method for honeycomb

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Embodiment Construction

[0016] The technical solution of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. The operation steps of the honeycomb composite splicing preform are as follows:

[0017] 1) Large thickness, large angle honeycomb sandwich structure such as figure 1 As shown, the thickness of the honeycomb sandwich is 60mm, and the angle is 30°;

[0018] 2) Select 3 layers of 20mm thick honeycomb to combine instead of 60mm thick honeycomb, and process the 3 layers of 20mm thick honeycomb with allowance respectively;

[0019] 3) Splicing the width direction splicing on the flat tooling with foaming glue between the processed honeycombs with margins in each layer and partition, and splicing and curing according to the curing parameters of the foaming glue;

[0020] 4) The honeycomb spliced ​​and solidified in the width direction is stacked on the forming tooling in sequence, and the baffle on the tooling is fixed with ...

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Abstract

The invention belongs to the field of aerospace honeycomb processing and particularly relates to a multi-layer splicing forming method for a honeycomb. The defects of the retraction, sliding and collapse and the like of the honeycomb still cannot be overcome by adjusting the curing parameter and an anti-sliding belt friction bolt system for a large-thickness large-chamfering honeycomb interlayer structural component with the high design rigidity and weight requirements. According to the multi-layer splicing forming method for the honeycomb, the thickness of the honeycomb interlayer structural component is laminated, each layer of the honeycomb is spliced in a partitioned manner, and through the splicing and performing of the honeycomb multiple layers, the lateral pressure resistance of the honeycomb is improved; and the purpose of forming and manufacturing the large-thickness large-angle honeycomb interlayer structural component without changing the weight and rigidity conditions is achieved, and the appearance quality of the formed part is good.

Description

technical field [0001] The invention belongs to the field of aviation honeycomb processing, and in particular relates to a splicing and forming method of honeycomb multilayers. Background technique [0002] Honeycomb sandwich composite structural parts are widely used in aerospace manufacturing because of their high design stiffness and low weight. At present, the honeycomb core design thickness of honeycomb sandwich composite structural parts is small (generally <1 inch), and the chamfering angle is small (generally <30°). For honeycomb sandwich structural parts with small thickness and small chamfering angle , the commonly used processing methods include: 1) adjusting the timing of pressurization and heating in the curing parameters; 2) using anti-slip belts to increase friction, 3) using adhesive films to stabilize the honeycomb before curing to improve the compression resistance of the honeycomb itself, Thereby preventing the honeycomb from slipping and deforming....

Claims

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Application Information

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IPC IPC(8): B29C70/68B29C67/20B29C65/48B29B11/14B29L31/30
CPCB29B11/14B29C65/48B29C67/20B29C70/68B29L2031/30B29C49/071B29C2949/0715
Inventor 戴东梅赵学莹苏永玺宋岩成景林硕李野
Owner 哈尔滨哈飞航空工业有限责任公司
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