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 r

Method used

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  • Sandwich structure radar radome and preparation method thereof

Examples

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Example Embodiment

[0037] The present invention provides a method of preparing a sandwich structure radar antenna cover according to the first aspect of the present invention, including the following steps:

[0038] (1) Paste the antenna cover in the antenna cover mold to obtain an antenna mask blanger;

[0039] (2) A preform comprising antenna cover I and a honeycomb core layer is obtained by a thermocouple tank by a thermocompression tank.

[0040] (3) The resin material and the hollow glass microbeam are mixed with a solvent and / or diluent to mix uniformly after uniformity of the preform included in the grid of the honeycomb core included in the prefabrication;

[0041] (4) The surface paste film and antenna cover II prepreg of the honeycomb core layer filled with the resin material and the hollow glass beads, and the thermocouple can be solidified by the heat pressing tank. .

[0042] In the present invention, for example, when the antenna mask I prepreg is blurred on the female wire of the an...

Example Embodiment

[0050] Example 1

[0051] A laminated structure radar antenna cover is composed of an antenna cover, a filler core layer, and an antenna cover; the filler core layer includes a honeycomb core layer and a honeycomb fill in a grid of the honeycomb core. The honeycomb filler is formed by mixing a resin material and a hollow glass bead. Outside the antenna cover inner skin and antenna cover is a quartz fiber / cyanate composite, the thickness is 0.6mm, the honeycomb core is the Nomax honeycomb core layer, the thickness is 8.5 mm, the honeycomb filler is a cyanate resin The mass ratio of the blended hollow glass microbead, cyanate resin and hollow glass beads is 1: 1.5; the structural antenna cover is at the L, the S-band minimum transmission rate is 85%.

[0052] The preparation method is: First, in the antenna hood mold, the cyanate quartz fabric prepreg (outer skin is pre-extmetled), and the honeycomb core layer is bonded to the film, and the heat press can be obtained. Including th...

Example Embodiment

[0054] Example 2

[0055] A laminated structure radar antenna cover is composed of an antenna cover, a filler core layer, and an antenna cover; the filler core layer includes a honeycomb core layer and a honeycomb fill in a grid of the honeycomb core. The honeycomb filler is formed by mixing a resin material and a hollow glass bead. The outer sheet of the antenna cover and the antenna cover are both a glass fiber / epoxy resin composite material having a thickness of 1.0 mm, and the honeycomb core is a Nomax honeycomb core layer, a thickness of 15.2 mm, and honeycomb fillers are epoxy. Oxygen Hollow glass microbeads blended with resin, the mass ratio of epoxy resin and hollow glass beads is 1: 1.5; the structural antenna cover is at least 75% in the C-band.

[0056] The preparation method is: First, in the antenna hood mold, the epoxy resin glass fabric prepreg (outer skin is pre-extract), and the honeycomb core layer is bonded to the film, and the thermal tank is solidified. Incl...

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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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