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Manufacturing method of honeycomb sandwich structure with dissimilar materials

A technology of honeycomb interlayer and dissimilar materials, which is applied in the direction of manufacturing tools, welding/welding/cutting items, metal processing equipment, etc., can solve the problems of high density of stainless steel and heavy honeycomb structure quality, achieve material cost reduction and expand the scope of application Effect

Inactive Publication Date: 2019-01-15
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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  • Abstract
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AI Technical Summary

Problems solved by technology

However, the density of stainless steel is high, and the mass of the honeycomb structure per unit volume is relatively heavy.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0021] Manufacture of Honeycomb Sandwich Structure of Titanium Alloy Panel / Stainless Steel Honeycomb Core Dissimilar Materials

[0022] Material: The panel is 0.6mm thick TC4 flat plate; the honeycomb core material is 304 stainless steel, the regular hexagonal honeycomb cell distribution, the honeycomb cell wall thickness is 0.1mm, the core height is 5mm, and the cell size is 8.0mm;

[0023] The solder for vacuum brazing is Ag-based solder, and the thickness of the solder is 0.1-0.2mm.

[0024] Specific steps include:

[0025] (1) Clean and clean the brazing side surface of the titanium alloy panel;

[0026] (2) Clean the stainless steel honeycomb core;

[0027] (3) Foil-shaped Ag-based solder is arranged on the brazing side surface of the titanium alloy panel;

[0028] (4) Assemble the titanium alloy panel with the stainless steel core, and the interface gap is less than 0.1mm;

[0029] (5) Put the assembled titanium alloy panel and stainless steel honeycomb core into a v...

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Abstract

The invention relates to a manufacturing method of a honeycomb sandwich structure with dissimilar materials. According to the technical points, the panel material of the honeycomb sandwich structure is titanium alloy, and the honeycomb core body material of the honeycomb sandwich structure is stainless steel. A foil-shaped Ag base brazing filler metal with thickness of 0.1-0.2mm is adopted in thevacuum brazing of a panel and a honeycomb core body, the brazing temperature is 810-835 DEG C, and the insulation time is 5-15 min. Compared with a conventional titanium alloy honeycomb sandwich structure, the fabricated honeycomb sandwich structure of titanium alloy panel / stainless steel honeycomb core body honeycomb sandwich structure with the dissimilar materials reduces much material cost andhas fair tensile mechanical properties, and is suitable for application in low cost environment. Meanwhile, the weight loss of the structure is obvious, the advantages of the titanium alloy and the stainless steel in performance and economy are given full play, and the application range of a metal honeycomb sandwich structure is expanded.

Description

technical field [0001] The invention relates to a method for manufacturing a honeycomb sandwich structure of heterogeneous materials, which belongs to the field of aviation manufacturing. Background technique [0002] The honeycomb sandwich structure consists of an upper panel, a honeycomb core and a lower panel, which are usually connected by brazing or gluing. Compared with core sandwich structures such as foam cores and corrugated board cores, honeycomb core sandwich structures have excellent comprehensive properties such as light weight, high specific strength and specific stiffness, sound attenuation, heat insulation, vibration reduction, and energy absorption. It is widely used in the field of aviation manufacturing engineering, such as aircraft fuselage, rudder wing surface, engine door, engine nacelle sound-absorbing acoustic lining, etc. [0003] Titanium alloy and stainless steel are currently commonly used materials for honeycomb sandwich structures. The honeycom...

Claims

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Application Information

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IPC IPC(8): B23K1/19B23K1/20B23K103/24
CPCB23K1/19B23K1/206
Inventor 邓云华岳喜山陶军
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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