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Method for whole forming of aluminum honeycomb sandwich structure of carbon panel

A sandwich structure and integral forming technology, which is applied in the integral forming of carbon panel aluminum honeycomb sandwich structure, satellite support and instrument cabin structure, and payload support field, can solve the problem of honeycomb sandwich bonding angle deviation, low rigidity of metal end frame, honeycomb Increased risk of debonding at seams and other problems, to achieve the effect of increasing the maximum load-carrying capacity

Active Publication Date: 2015-11-25
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When the size of the product increases, the area of ​​the honeycomb sandwich increases, and the number of joints between the honeycomb sandwiches increases, which may easily cause the deviation of the bonding angle of the honeycomb sandwich, and the thickened area between the honeycomb splicing and the inner and outer panels or hair loss. The probability of overlap in the foam filling area increases, which increases the risk of debonding at the honeycomb seam, which brings greater difficulty to the cutting and sinking of the honeycomb sandwich
In addition, when the size of the product increases, the rigidity of the metal end frame is low, and it is easy to deform, which affects the assembly positioning accuracy of the product and the size after curing

Method used

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  • Method for whole forming of aluminum honeycomb sandwich structure of carbon panel
  • Method for whole forming of aluminum honeycomb sandwich structure of carbon panel
  • Method for whole forming of aluminum honeycomb sandwich structure of carbon panel

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Embodiment

[0063] Product Name: Payload Bracket

[0064] Dimensions: Axial height 1480mm, front metal end frame diameter 4126mm, rear metal end frame diameter 5117mm, front metal end frame and rear metal end frame cross section "F", inner panel thickness 1.5mm, outer panel thickness 1.5mm mm, the side length of the aluminum honeycomb sandwich is 4mm, the thickness of the aluminum foil is 0.05mm, and the height of the sandwich is 14mm. It can be seen from the above dimensions that the diameter of the payload bracket is greater than or equal to 5m. Such as figure 1 Shown is the front view of the carbon panel aluminum honeycomb sandwich structure of the embodiment of the present invention, figure 2 It is a partial sectional view of an aluminum honeycomb sandwich structure with a carbon panel according to an embodiment of the present invention.

[0065] Such as image 3 As shown, the implementation steps of the integral molding method are as follows:

[0066] (1) According to the produ...

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Abstract

The invention relates to a method for whole forming of an aluminum honeycomb sandwich structure of a carbon panel. The method comprises the following steps of designing and manufacturing a male die of a main body, manufacturing a split steel die of an outer panel, preparing a prepreg, manufacturing an inner panel and the outer panel, assembling, curing, removing the dies, and the like. The method has the advantages that by adopting the reasonable design of the dies, and the process control of carbon epoxy panel, aluminum honeycomb core and metal end frame assembly process, the aluminum honeycomb sandwich structure product of the carbon panel of a large rotary body with attractive appearance and high internal quality can be manufactured, and the design index requirements of the product are met; at the premises of not increasing the manufacturing cost, the structure size of the product is increased, and the bearing capacity of an effective load bracket is increased.

Description

technical field [0001] The invention relates to an integral forming method of a carbon panel aluminum honeycomb sandwich structure, especially a method for integral forming of a carbon panel aluminum honeycomb sandwich structure with a diameter greater than or equal to 5m, which belongs to the field of composite material main load-bearing structure forming, and is mostly used in payload supports, satellites Support and instrument compartment structure. Background technique [0002] Carbon epoxy composite materials have the characteristics of high specific strength, high specific modulus, and good fatigue resistance. The honeycomb sandwich structure has outstanding specific stiffness and specific strength, high flatness, and is not easy to deform. Efficiency, increased payload. The carbon epoxy panel / aluminum honeycomb sandwich structure is an advanced structural form, which has the characteristics of strong designability, high structural efficiency, and mature manufacturing...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B15/04B32B3/12B32B15/20B32B9/00B32B3/06B32B37/02B32B38/00B32B37/12B32B38/16
CPCB32B3/06B32B3/12B32B9/007B32B15/04B32B15/20B32B37/02B32B37/12B32B38/0004B32B38/0012B32B38/0036B32B38/164B32B2038/0076
Inventor 张霄楠李健芳张娅婷付平俊黄智彬
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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