CN212380124U - High-temperature winding shielding cable for airplane - Google Patents
High-temperature winding shielding cable for airplane Download PDFInfo
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- CN212380124U CN212380124U CN202020988835.3U CN202020988835U CN212380124U CN 212380124 U CN212380124 U CN 212380124U CN 202020988835 U CN202020988835 U CN 202020988835U CN 212380124 U CN212380124 U CN 212380124U
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- high temperature
- energy transmission
- temperature resistant
- resistant energy
- insulating layer
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Abstract
The utility model belongs to the wire and cable field relates to an aircraft is with high temperature winding shielded cable, include: control line core subassembly, a plurality of high temperature resistant energy transmission sinle silks, second magnesium oxide are filled, second winding shielding layer and are gathered perfluor ethylene propylene restrictive coating, and wherein, a plurality of high temperature resistant energy transmission sinle silks evenly spaced set up around control line core subassembly, are equipped with the second magnesium oxide between the adjacent high temperature resistant energy transmission sinle silks and fill, and a plurality of high temperature resistant energy transmission sinle silks outside sets gradually second winding shielding layer and gathers perfluor ethylene propylene restrictive coating. According to the utility model discloses a high temperature winding shielded cable for aircraft, the structure is soft, can stand to reciprocate to drag and draw, has excellent high temperature resistant, anti-interference and tensile strength.
Description
Technical Field
The utility model belongs to the technical field of wire and cable, especially, relate to an aircraft is with high temperature winding shielded cable.
Background
The space in the aircraft cabin is limited, and the cable that is used needs to be flexible, can be wound and coiled, is similar to the tape measure structure, can be pulled out when needing to be used, can retrieve when not needing to be used, therefore requires that the cable must have good compliance and tensile strength. The whole stability of the interior of the aircraft cabin is high, so that a material with high temperature resistance grade is required to be used as an insulation material, and the insulation material is required to be flame-retardant and not to delay combustion.
SUMMERY OF THE UTILITY MODEL
In order to overcome the defects of the prior art, the utility model aims to provide a high-temperature winding shielded cable for an airplane.
According to an aspect of the utility model provides an aircraft is with high temperature winding shielded cable includes: control core subassembly 1, a plurality of high temperature resistant energy transmission sinle silk 2, the second magnesium oxide is filled 3, second winding shielding layer 4 and is gathered perfluor ethylene propylene restrictive coating 5, wherein, a plurality of high temperature resistant energy transmission sinle silks 2 even interval sets up around control core subassembly 1, is equipped with the second magnesium oxide between the adjacent high temperature resistant energy transmission sinle silk 2 and fills 3, and a plurality of high temperature resistant energy transmission sinle silks 2 outsides set gradually second winding shielding layer 4 and gather perfluor ethylene propylene restrictive coating 5.
According to the exemplary embodiment of the present invention, control wire core assembly 1 includes: the control cable comprises a plurality of control cable cores 11, a first magnesium oxide filling layer 12, a first winding shielding layer 13 and a first polytetrafluoroethylene insulating layer 14, wherein the first magnesium oxide filling layer 12 is filled between the control cable cores 11 and the first winding shielding layer 13, and the first polytetrafluoroethylene insulating layer 14 is arranged on the outer side of the first winding shielding layer 13.
According to the utility model discloses an exemplary embodiment, control core 11 includes from inside to outside in proper order: a first tough pitch copper conductor 111, a first mica tape insulating layer 112, a polyperfluoroethylene propylene insulating layer 113 and a copper sheath layer 114.
According to the utility model discloses an exemplary embodiment, high temperature resistant energy transmission sinle silk 2 includes: a plurality of second tough pitch copper conductors 21, a second mica tape insulating layer 22 and a second polytetrafluoroethylene insulating layer 23 which are sequentially coated outside the plurality of second tough pitch copper conductors 21.
According to an exemplary embodiment of the present invention, the first winding shield layer 13 is a copper alloy wire.
According to an exemplary embodiment of the present invention, the second winding shield layer 4 is a copper-magnesium alloy wire.
Compared with the prior art, the utility model discloses a high temperature winding shielded cable for aircraft, the structure is soft, can stand to reciprocate to drag and draw, has excellent high temperature resistant, anti-interference and tensile strength.
Drawings
Fig. 1 is a schematic structural view of a high-temperature wound shielded cable for an aircraft according to the present invention;
fig. 2 is a schematic structural diagram of a control core assembly in a high-temperature winding shielded cable for an aircraft according to the present invention.
In the figure, 1-control wire core assembly, 11-control wire core, 111-first tough-copper conductor, 112-first mica tape insulating layer, 113-fluorinated ethylene propylene insulating layer, 114-copper protective layer, 12-first magnesium oxide filling, 13-first winding shielding layer, 14-first polytetrafluoroethylene insulating layer; 2-high temperature resistant energy transmission wire core, 21-second tough copper conductor, 22-second mica tape insulating layer and 23-second polytetrafluoroethylene insulating layer; 3-magnesium oxide filling, 4-second winding shielding layer and 5-fluorinated ethylene propylene sheath layer.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1, the high-temperature wound shielded cable for aircraft according to the embodiment of the present invention includes: control core subassembly 1, a plurality of high temperature resistant energy transmission sinle silk 2, the second magnesium oxide is filled 3, second winding shielding layer 4 and is gathered perfluor ethylene propylene restrictive coating 5, wherein, a plurality of high temperature resistant energy transmission sinle silks 2 even interval sets up around control core subassembly 1, is equipped with the second magnesium oxide between the adjacent high temperature resistant energy transmission sinle silk 2 and fills 3, and a plurality of high temperature resistant energy transmission sinle silks 2 outsides set gradually second winding shielding layer 4 and gather perfluor ethylene propylene restrictive coating 5.
Specifically, the control wire core assembly 1 includes: the control cable comprises a plurality of control cable cores 11, a first magnesium oxide filling layer 12, a first winding shielding layer 13 and a first polytetrafluoroethylene insulating layer 14, wherein the first magnesium oxide filling layer 12 is filled between the control cable cores 11 and the first winding shielding layer 13, and the first polytetrafluoroethylene insulating layer 14 is arranged on the outer side of the first winding shielding layer 13.
The control wire core 11 comprises from inside to outside in sequence: a first tough pitch copper conductor 111, a first mica tape insulating layer 112, a polyperfluoroethylene propylene insulating layer 113 and a copper sheath layer 114.
High temperature resistant energy transmission sinle silk 2 includes: a plurality of second tough pitch copper conductors 21, a second mica tape insulating layer 22 and a second polytetrafluoroethylene insulating layer 23 which are sequentially coated outside the plurality of second tough pitch copper conductors 21.
The first wound shield layer 13 is a copper alloy wire.
The second winding shielding layer 4 is a copper-magnesium alloy wire.
The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above description is only the embodiments of the present invention, and is not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (6)
1. A high temperature wound shielded cable for an aircraft, the high temperature wound shielded cable for an aircraft comprising: control core assembly (1), a plurality of high temperature resistant energy transmission sinle silk (2), second magnesium oxide fills (3), second winding shielding layer (4) and gather perfluor ethylene propylene restrictive coating (5), wherein, a plurality of high temperature resistant energy transmission sinle silks (2) even interval sets up around control core assembly (1), be equipped with second magnesium oxide between adjacent high temperature resistant energy transmission sinle silk (2) and fill (3), a plurality of high temperature resistant energy transmission sinle silks (2) outside sets gradually second winding shielding layer (4) and gathers perfluor ethylene propylene restrictive coating (5).
2. High-temperature wound shielded cable for aircraft according to claim 1, characterized in that the control core assembly (1) comprises: the cable comprises a plurality of control wire cores (11), first magnesium oxide filling layers (12), a first winding shielding layer (13) and a first polytetrafluoroethylene insulating layer (14), wherein the first magnesium oxide filling layers (12) are filled between the control wire cores (11) and the first winding shielding layer (13), and the first polytetrafluoroethylene insulating layer (14) is arranged on the outer side of the first winding shielding layer (13).
3. A high-temperature wound shielded cable for aircraft according to claim 2, characterized in that the control wire core (11) comprises, in order from the inside to the outside: the first tough copper conductor (111), the first mica tape insulating layer (112), the polyfluorinated ethylene propylene insulating layer (113) and the copper protective layer (114).
4. A high-temperature-wound shielded electrical cable for aircraft according to claim 1, wherein the high-temperature-resistant energy-transmitting core (2) comprises: a plurality of second tough pitch copper conductors (21), a second mica tape insulating layer (22) and a second polytetrafluoroethylene insulating layer (23) which are sequentially coated outside the plurality of second tough pitch copper conductors (21).
5. A high-temperature wound shielded cable for aircraft according to claim 2, wherein the first wound shield layer (13) is a copper alloy wire.
6. A high-temperature wound shielded cable for aircraft according to claim 1, wherein the second wound shield layer (4) is a copper-magnesium alloy wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020988835.3U CN212380124U (en) | 2020-06-03 | 2020-06-03 | High-temperature winding shielding cable for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020988835.3U CN212380124U (en) | 2020-06-03 | 2020-06-03 | High-temperature winding shielding cable for airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212380124U true CN212380124U (en) | 2021-01-19 |
Family
ID=74179749
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020988835.3U Active CN212380124U (en) | 2020-06-03 | 2020-06-03 | High-temperature winding shielding cable for airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212380124U (en) |
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2020
- 2020-06-03 CN CN202020988835.3U patent/CN212380124U/en active Active
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