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Sandwich structure radar radome and preparation method thereof

A technology of radome and sandwich structure, which is applied to antennas, antenna parts, chemical instruments and methods, etc., can solve the problem of debonding between honeycomb and skin, and achieve the effect of improving environmental adaptability

Pending Publication Date: 2021-06-18
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the problem of debonding between the honeycomb and the skin of the existing honeycomb sandwich structure radome in a low external pressure environment, the present invention provides a sandwich structure radome and its preparation method

Method used

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  • Sandwich structure radar radome and preparation method thereof

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preparation example Construction

[0037] In a second aspect, the present invention provides a method for preparing the sandwich structure radome described in the first aspect of the present invention, said method comprising the steps of:

[0038] (1) Paste the radome skin I prepreg on the radome mold to obtain the radome skin green body;

[0039] (2) bonding the honeycomb core layer through an adhesive film on the radome skin blank, and curing and molding in an autoclave (autoclave forming) to obtain a prefabricated body comprising the radome skin I and the honeycomb core layer;

[0040] (3) mix the resin material and the hollow glass microspheres uniformly with a solvent and / or diluent and fill them in the grid of the honeycomb core layer included in the prefabricated body;

[0041] (4) Adhesive film and radome skin II prepreg are pasted on the surface of the honeycomb core layer filled with the resin material and the hollow glass microspheres, and the sandwich structure radome is obtained by curing and moldi...

Embodiment 1

[0051] A kind of sandwich structure radar radome is made up of radome outer skin, filling core layer and radome inner skin; Described filling core layer comprises honeycomb core layer and the honeycomb filler that fills in the grid of described honeycomb core layer, The honeycomb filler is formed by mixing and curing resin materials and hollow glass microspheres. The inner skin of the radome and the outer skin of the radome are both quartz fiber / cyanate composite materials with a thickness of 0.6mm, the honeycomb core layer is Nomax honeycomb core layer with a thickness of 8.5mm, and the honeycomb filler is cyanate resin For the blended hollow glass microspheres, the mass ratio of cyanate resin and hollow glass microspheres is 1:1.5; the lowest wave transmittance of the radome in the L and S frequency bands of this structure is 85%.

[0052] The preparation method is as follows: firstly, cyanate quartz cloth prepreg (radome outer skin prepreg) is pasted on the female mold of t...

Embodiment 2

[0055] A kind of sandwich structure radar radome is made up of radome outer skin, filling core layer and radome inner skin; Described filling core layer comprises honeycomb core layer and the honeycomb filler that fills in the grid of described honeycomb core layer, The honeycomb filler is formed by mixing and curing resin materials and hollow glass microspheres. The inner skin of the radome and the outer skin of the radome are both glass fiber / epoxy resin composite materials with a thickness of 1.0mm, the honeycomb core layer is Nomax honeycomb core layer with a thickness of 15.2mm, and the honeycomb filler is epoxy Hollow glass microspheres blended with resin, the mass ratio of epoxy resin and hollow glass microspheres blended is 1:1.5; the minimum wave transmittance of the radome of this structure is 75% in the C frequency band.

[0056] The preparation method is as follows: firstly, paste epoxy resin glass cloth prepreg (radome outer skin prepreg) on ​​the female mold of t...

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Abstract

The invention relates to a sandwich structure radar radome and a preparation method thereof. The sandwich structure radar radome comprises a skin I, a filling core layer and a skin II; the filling core layer comprises a honeycomb core layer and honeycomb filler filled in grids of the honeycomb core layer, and the honeycomb filler is formed by mixing and curing a resin material and hollow glass beads. The method comprises the following steps: preparing a skin blank; bonding the a honeycomb core layer to the skin blank, and obtaining a prefabricated body comprising the skin I and the honeycomb core layer through autoclave curing forming; uniformly mixing the resin material and hollow glass beads with a solvent and / or a diluent, and filling the mixture into grids of the honeycomb core layer included in the prefabricated body; and finally, pasting a glue film and a skin II prepreg on the surface of the honeycomb core layer, and obtaining the sandwich structure radar radome through autoclave curing forming. The environment adaptability of the radome can be improved, the problem that the skin and the honeycomb core layer are prone to debonding and bulging in the hanging process of the radome is solved, the electrical performance index requirement of the radome is met, and meanwhile the product reliability is guaranteed.

Description

technical field [0001] The invention belongs to the technical field of radome, and in particular relates to a radome with a sandwich structure and a preparation method thereof. Background technique [0002] At present, the wideband aviation radar radome usually adopts the sandwich structure of skin / core layer / skin to meet the requirements of wideband wave transmission and weight reduction of the radome. Among them, glass fiber reinforced resin-based composite materials are mostly used for skin materials, and Nomax honeycomb core layers or PMI foam core layers are mostly used for core layer materials. For radome products with complex profiles, the PMI foam core layer is difficult to form and the cost is high. Due to the influence of the air in the honeycomb gap of the Nomax honeycomb core structure, the pressure difference between the inside and outside of the product is likely to cause skin debonding or even bulging when flying at high altitudes, affecting product safety. ...

Claims

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Application Information

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IPC IPC(8): H01Q1/42B32B3/12B32B3/08B32B7/12B32B37/10
CPCH01Q1/422B32B3/12B32B3/08B32B7/12B32B37/10B32B2037/1223
Inventor 徐亮唐培毅李南郭艳丽梁垠
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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