CN215496122U

CN215496122U - High-temperature-resistant and corrosion-resistant wire for aircraft

Info

Publication number: CN215496122U
Application number: CN202120101665.7U
Authority: CN
Inventors: 刘毅华; 赵燕; 黄振
Original assignee: Guangzhou Star Conduction Technology Co Ltd
Current assignee: Guangzhou Star Conduction Technology Co Ltd
Priority date: 2021-01-14
Filing date: 2021-01-14
Publication date: 2022-01-11
Anticipated expiration: 2031-01-14

Abstract

The utility model discloses a high-temperature-resistant and corrosion-resistant wire for an aircraft, which sequentially comprises the following components from inside to outside: a center conductor, an inner insulating layer, and an outer insulating layer; the inner insulating layer wraps the periphery of the central conductor, and the outer insulating layer wraps the periphery of the inner insulating layer; the central conductor is made of silver-plated or tin-plated soft copper wires through bunching. Wherein, the inner insulation layer adopts HDPE polymer insulation material, and the outer insulation layer adopts PVDF polymer insulation material, and this two kinds of materials are than original traditional teflon/nylon insulation material, greatly reduced the weight of wire self. The designed inner layer and outer layer of insulation can achieve insulation performance complementation, external force damage to the outer traditional single-layer insulation due to self stress of a conductor is offset, the requirements of electrical and physical mechanical properties of an aerospace system are met, and the insulated wire meets the performance requirements of high mechanical strength, good flexibility, high and low temperature resistance, radiation resistance, light weight and the like, and is the general trend of wire development for the future aircraft industry.

Description

High-temperature-resistant and corrosion-resistant wire for aircraft

Technical Field

The utility model relates to the technical field of wires and cables, in particular to the field of application of aerospace instrument and meter electronic technology, and particularly relates to a high-temperature-resistant and corrosion-resistant wire for an aircraft.

Background

In recent years, the aerospace industry in China is rapidly developed, and nowadays, Chang' e five successfully completes the lunar exploration planning task, brings lunar soil samples, and establishes milestone significance for the development of the aerospace industry in China. With the rapid development of aerospace industry in China, higher requirements are put forward on connecting wires in electronic instruments and instrument equipment matched with the aerospace field, and the requirements on higher temperature resistance, radiation resistance, light weight and other performance of modern aerospace must be met; the traditional Teflon/nylon insulated wire product is a very excellent wire and cable insulating material and plays an important role in aerospace cables. Along with the development of scientific and technological requirements, the defects of the materials are more obvious, the weakest point is poor radiation resistance except insufficient mechanical strength, all plastics can crack under the irradiation of high-energy gamma rays, potential safety hazards are easy to appear, and the materials are particularly developed in the directions of high conductivity, high precision, miniaturization, light weight, wear resistance, high strength, high reliability and the like aiming at various wires for electrical matching connection.

The original high-temperature-resistant wire matched with the traditional high-temperature-resistant wire mostly adopts Teflon and nylon molecular materials as outer-covering insulating materials, the density of the product is high, the outer diameter is relatively large, the weight is relatively heavy, a single-layer insulating structure designed by the high-temperature-resistant wire is easy to crack or damage an outer-covering insulating layer due to the stress action possibly generated by the structure of an inner conductor, short circuit and leakage of matched lines are caused, the safety and reliability are poor, and potential safety hazards exist according to the high safety standard requirement of aerospace. Innovations must be improved.

Therefore, a novel high-temperature-resistant corrosion-resistant wire for aircraft with high safety is needed.

SUMMERY OF THE UTILITY MODEL

In view of the safety bottleneck existing in the prior art, the high-temperature-resistant and corrosion-resistant wire for the aircraft provided by the utility model has the advantages of high safety, light weight, high temperature resistance, corrosion resistance, wear resistance and high mechanical strength.

The embodiment of the utility model provides a high-temperature-resistant anticorrosive wire for an aircraft, which sequentially comprises the following components from inside to outside: a center conductor, an inner insulating layer, and an outer insulating layer;

the inner insulating layer wraps the periphery of the central conductor, and the outer insulating layer wraps the periphery of the inner insulating layer; the central conductor is made of silver-plated or tin-plated soft copper wires through bunching.

In the embodiment, the wire is provided with the inner/outer insulating layers, and the thin-wall inner insulating layer and the thin-wall outer insulating layer are simultaneously extruded by adopting a double-layer co-extrusion technology; the tension coefficient of the traditional single-layer insulated wire, which is generated by the stress of the conductor, is relieved, and the single-layer insulating layer is easy to crack and damage; the potential safety hazard to the aerospace craft can be avoided. In addition, the central conductor is a stranded conductor, and fully plays roles of high conductivity and corrosion resistance.

Further, the inner insulating layer is made of HDPE polymer insulating material and has the density of 0.92g/cm³The thickness is 0.15 mm.

In the embodiment, the inner insulating layer can be ensured to have better flexibility, the weight is light, and the strength is greatly enhanced.

Furthermore, the outer insulating layer adopts a cross-linked polyvinylidene fluoride insulating material, and the density of the cross-linked polyvinylidene fluoride insulating material is 1.17g/cm³。

In this embodiment, the outer insulating layer is made of a polymer material, and has ultraviolet and high-energy radiation resistance, chemical corrosion resistance, high-temperature discoloration resistance, oxidation resistance, excellent wear resistance, flexibility, and high tensile strength and impact strength.

Furthermore, the outer insulating layer is made of a cross-linked polyvinylidene fluoride insulating material, and the strength is 40N/mm²。

In the embodiment, the outer insulating layer has good mechanical strength, the oxygen index of the outer insulating layer can reach 40, the outer insulating layer belongs to a temperature-resistant and flame-retardant material, and the safety coefficient is high.

Further, the density of the inner insulation layer and the outer insulation layer is 1.1g/cm³. Compared with the traditional Teflon/nylon, the density is 2.2g/cm³The material is reduced by one time; thereby greatly reducing the quality of the finished wire.

Further, the sectional area of the lead is 1-4 mm²And the self weight of the lead is greatly reduced while high conductivity is met.

The technical scheme provided by the embodiment of the utility model has the beneficial effects that at least:

the high-temperature-resistant and corrosion-resistant wire for the aircraft comprises a central inner conductor, an inner insulating layer and an outer insulating layer, wherein the central conductor is formed by bundling silver-plated or tin-plated soft copper wires, the inner insulating layer is made of HDPE high-polymer insulating materials, the outer insulating layer is made of high-polymer insulating materials, and compared with the original traditional Teflon/nylon insulating materials, the weight of the wire is greatly reduced. The designed inner layer and outer layer of insulation can achieve insulation performance complementation, external force damage to the outer traditional single-layer insulation due to self stress of a conductor is offset, the requirements of electrical and physical mechanical properties of an aerospace system are met, and the insulated wire meets the performance requirements of high mechanical strength, good flexibility, high and low temperature resistance, radiation resistance, light weight and the like, and is the general trend of wire development for the future aircraft industry.

Additional features and advantages of the utility model will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the utility model. The objectives and other advantages of the utility model will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.

The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.

Drawings

The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the principles of the utility model and not to limit the utility model. In the drawings:

fig. 1 is a perspective view of a high-temperature resistant and corrosion-resistant wire for an aircraft according to an embodiment of the present invention;

FIG. 2 is a cross-sectional view of a high temperature resistant corrosion resistant wire for an aircraft according to an embodiment of the present invention;

in the drawing, 1-center conductor, 2-inner insulation layer, 3-outer insulation layer.

Detailed Description

Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the utility model easy to understand, the utility model is further described with the specific embodiments.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front", "rear", "both ends", "one end", "the other end", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, such as "connected," which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

The embodiment of the utility model provides a high-temperature-resistant anticorrosive wire for an aircraft, which comprises the following components in sequence from inside to outside with reference to FIGS. 1-2: a central conductor 1, an inner insulating layer 2 and an outer insulating layer 3; the inner insulating layer 2 wraps the periphery of the central conductor 1, and the outer insulating layer 3 wraps the periphery of the inner insulating layer 2; the central conductor 1 is made of silver-plated or tin-plated soft copper wires through bunching.

The wire is composed of a central conductor 1, a conductor inner insulating layer 2 and an outer insulating layer 3, and a double-layer insulating conductive wire core is formed. The wire is provided with an inner insulating layer and an outer insulating layer, and thin-walled inner insulating layers and outer insulating layers are simultaneously extruded by adopting a double-layer co-extrusion technology; the tension coefficient of the traditional single-layer insulated wire, which is generated by the stress of the conductor, is relieved, and the single-layer insulating layer is easy to crack and damage; the potential safety hazard to the aerospace craft can be avoided. In addition, the central conductor is a stranded conductor, and fully plays roles of high conductivity and corrosion resistance.

Specifically, the central inner conductor 1 is a soft conductor formed by bundling tin-plated copper or silver filaments. The bundle twisted conductor has high conductivity and corrosion resistance. The inner insulating layer 2 is made of HDPE polymer insulating material with the density of 0.92g/cm³The design thickness is only 0.15 mm. The inner insulating layer can be ensured to have better flexibility, the weight is light, and the strength is greatly enhanced. The outer insulating layer 3 is made of cross-linked polyvinylidene fluoride insulating material with the density of 1.17g/cm³The high polymer material has the advantages of ultraviolet ray resistance, high energy radiation resistance, chemical corrosion resistance, high temperature color change resistance, oxidation resistance, excellent wear resistance, flexibility, high expansion strength and impact strength. In addition, the outer insulating layer is insulated by crosslinked polyvinylidene fluoride, and the strength of the material is 40N/mm²Has the advantages ofGood mechanical strength. The oxygen index can reach 40, and the material belongs to a temperature-resistant and flame-retardant material and has high safety coefficient.

The density of the inner/outer insulating layer is 1.1g/cm³Compared with the traditional Teflon/nylon, the density is 2.2g/cm³The material is reduced by one time; thereby greatly reducing the quality of the finished product wire; the sectional area of the lead is 1-4 mm²The weight of the lead wire itself can be further reduced while high conductivity is satisfied.

The high-temperature-resistant and anti-corrosion wire for the aircraft provided by the embodiment of the utility model has the characteristics of high chemical stability, good anti-corrosion property, thermal aging resistance and adaptability to harsh ultraviolet-resistant environment, so that the high-temperature-resistant and anti-corrosion wire can be widely applied. The safety of electrical connection of the aircraft instruments and meters can be guaranteed, the service life of the lead is longer, and the safety is higher.

It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the utility model. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.

Claims

1. The utility model provides an aircraft is with anticorrosive wire of high temperature resistant which characterized in that, by interior to exterior in proper order including: a center conductor, an inner insulating layer, and an outer insulating layer;

the inner insulating layer wraps the periphery of the central conductor, and the outer insulating layer wraps the periphery of the inner insulating layer; the central conductor is formed by bundling and twisting silver-plated or tin-plated soft copper wires;

the inner insulating layer is made of HDPE polymer insulating material and has a density of 0.92g/cm³The thickness is 0.15 mm;

the outer insulating layer is made of cross-linked polyvinylidene fluoride insulating material and has a density of 1.17g/cm³。

2. The aircraft high temperature resistant corrosion resistant wire of claim 1 wherein the strength of the outer insulation layer is 40N/mm²。

3. The aircraft high-temperature-resistant corrosion-resistant wire according to claim 1, wherein the density of the inner insulating layer and the outer insulating layer is 1.1g/cm³。

4. The high-temperature-resistant and corrosion-resistant wire for the aircraft as claimed in any one of claims 1 to 3, wherein the cross-sectional area of the wire is 1 to 4mm²。