CN113097946A - Aircraft wiring harness laying structure - Google Patents
Aircraft wiring harness laying structure Download PDFInfo
- Publication number
- CN113097946A CN113097946A CN202110371820.1A CN202110371820A CN113097946A CN 113097946 A CN113097946 A CN 113097946A CN 202110371820 A CN202110371820 A CN 202110371820A CN 113097946 A CN113097946 A CN 113097946A
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- CN
- China
- Prior art keywords
- adapter
- harness
- aircraft
- connector plug
- structure according
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000001681 protective effect Effects 0.000 claims description 24
- 239000010410 layer Substances 0.000 claims description 15
- 239000011241 protective layer Substances 0.000 claims description 13
- 238000002788 crimping Methods 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 8
- 238000003466 welding Methods 0.000 claims description 8
- 230000007704 transition Effects 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims 2
- 230000001070 adhesive effect Effects 0.000 claims 2
- 239000005871 repellent Substances 0.000 claims 2
- 238000005476 soldering Methods 0.000 claims 1
- 238000005452 bending Methods 0.000 abstract description 2
- 239000003292 glue Substances 0.000 description 4
- 229920000297 Rayon Polymers 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/02—Details
- H02G3/04—Protective tubing or conduits, e.g. cable ladders or cable troughs
- H02G3/0462—Tubings, i.e. having a closed section
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R27/00—Coupling parts adapted for co-operation with two or more dissimilar counterparts
Landscapes
- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Cable Accessories (AREA)
Abstract
The invention relates to the technical field of electronics, and discloses an aircraft wiring harness laying structure which comprises a main plug, a first adapter, a second adapter, a third adapter and a fourth adapter, wherein one end of the first adapter is connected with the main plug, and the other end of the first adapter is provided with a plurality of branch structures; the second adapter is of a broken line type structure; the third adapter is of a broken line type structure. The laying structure realizes the arrangement of the wiring harness branch channels through the first adapter, so that the structure is simplified, and the wiring harness branch channels can be flexibly matched with the second adapter, the third adapter and the fourth adapter for use so as to realize the connection of the wiring harness branch and equipment; the second adapter and the third adapter are located on two sides of the fourth adapter, and the structural design of a broken line type is adopted, so that the bending degree of two sides of the wiring harness can be reduced, the occupied space of the wiring harness is reduced, the fourth adapter is U-shaped, the U-shaped wiring harness is suitable for being used in a complex environment, and the requirement for wiring harness laying is met in a narrow space.
Description
Technical Field
The invention relates to the technical field of electronics, in particular to an aircraft wire harness laying structure.
Background
In the prior art, in the process of laying a wire harness, a protective sleeve is generally required to be added outside the wire harness to improve the adaptivity of the wire harness, the protective sleeve generally does not have good flexibility, the overall diameter of the wire harness after the protective sleeve is added is also increased, the turning radius required in the process of laying the wire harness is also increased, the space of the special areas is narrow, the difficulty of laying the wire harness is very high in the space, and the laying requirement of the wire harness cannot be met frequently.
Disclosure of Invention
Aiming at the technical problems in the prior art, the invention provides an aircraft wire harness laying structure which can meet the laying requirements of wire harnesses in a narrow space.
The technical scheme adopted by the invention for solving the technical problems is as follows: an aircraft harness routing structure comprising a main plug; the first adapter is connected with the main plug at one end, and a plurality of branch structures are arranged at the other end of the first adapter; one end of the second adapter is connected with the other end of the first adapter through a first wire harness, the other end of the second adapter can be connected with first electric equipment, and the second adapter is of a broken line type structure; one end of the third adapter is connected with the other end of the first adapter through a second wire harness, the other end of the third adapter can be connected with second electrical equipment, and the third adapter is of a broken line type structure; and the fourth adapter is positioned between the second adapter and the third adapter, one end of the fourth adapter is connected with the other end of the first adapter through a third wiring harness, the other end of the fourth adapter can be connected with a third electric device, and the fourth adapter is U-shaped.
In the aircraft harness laying structure, the first harness, the second harness and the third harness each include a wire and a protective sleeve, and the wire is arranged inside the protective sleeve.
According to the aircraft wire harness laying structure, the protective sleeve sequentially comprises the insulating layer, the shielding layer and the protective layer from inside to outside.
In the aircraft wire harness laying structure, the protective sleeve further comprises a protective sleeve arranged between the insulating layer and the shielding layer.
In the aircraft wire harness laying structure, the protective layer is a waterproof protective layer or an oil-proof protective layer.
In the aircraft harness laying structure, one end of each of the protective sleeves of the first harness, the second harness and the third harness is tightly connected with the first adapter through a viscose glue, and the other end of each of the protective sleeves of the first harness, the second harness and the third harness is tightly connected with one end of the second adapter, the third adapter and the fourth adapter through viscose glue.
The second adapter is connected with the first electric equipment through a first connector plug, a wire in the first wire harness is connected with the first connector plug in a welding/crimping mode, the third adapter is connected with the second electric equipment through a second connector plug, the wire in the second wire harness is connected with the second connector plug in a welding/crimping mode, the fourth adapter is connected with the third electric equipment through a third connector plug, and the wire in the third wire harness is connected with the third connector plug in a welding/crimping mode.
In the aircraft harness laying structure, the other end of the second adapter is in threaded connection with the first connector plug, the other end of the third adapter is in threaded connection with the second connector plug, and the other end of the fourth adapter is in threaded connection with the third connector plug.
In the above aircraft harness installation structure, one end of the first adapter is screwed to the main plug.
In the aircraft harness laying structure, the second adapter and the third adapter both comprise the first connecting section and the second connecting section, the first connecting section and the second connecting section are in circular arc transition connection, and an included angle between the axis of the first connecting section and the axis of the second connecting section is 45 degrees.
The aircraft wire harness laying structure at least has the following beneficial effects: the laying structure realizes the arrangement of the wiring harness branch channels through the first adapter without adopting a deconcentrator and other accessories, so that the structure is simplified, the weight is lightened, the occupied space is smaller, and the wiring harness branch can be flexibly matched with the second adapter, the third adapter and the fourth adapter to be used for realizing the connection of the wiring harness branch and equipment; the second adapter and the third adapter are located on two sides of the fourth adapter, and adopt the structural design of a broken line type, so that the first electric equipment and the second electric equipment can be connected, the bending degree of two sides of the wire harness can be reduced, the occupied space of the wire harness is reduced, the fourth adapter is in a U shape, the small wire harness can be rapidly divided into a large wire harness in a narrow space, and the requirement of laying the wire harness can be met in a complex environment.
Drawings
The invention will be further described with reference to the following figures and examples, in which:
fig. 1 is a schematic overall structure diagram of an aircraft harness radiation structure according to an embodiment of the present invention.
In the drawings: a 100 host plug, a 200 first adapter, a 210 furcation structure, a 300 second adapter, a 310 first harness, a 320 first connector plug, a 330 first electrical device, a 400 third adapter, a 410 second harness, a 420 second connector plug, a 430 second electrical device, a 500 fourth adapter, a 510 third harness, a 520 third connector plug, a 530 third electrical device.
Detailed Description
Describing an embodiment of the present invention in detail, referring to fig. 1, the embodiment of the present invention provides an aircraft harness routing structure, including a main plug 100, a first adapter 200, a second adapter 300, a third adapter 400, and a fourth adapter 500, wherein one end of the first adapter 200 is connected to the main plug 100, and the other end has a plurality of branch structures 210; one end of the second adapter 300 is connected to the other end of the first adapter 200 through a first wire harness 310, the other end of the second adapter 300 can be connected to a first electric device 330, and the second adapter 300 is of a broken line type structure; one end of the third adapter 400 is connected to the other end of the first adapter 200 through a second wire harness 410, the other end of the third adapter 400 can be connected to a second electrical device 430, and the third adapter 400 is of a broken line type structure; the fourth adapter 500 is located between the second adapter 300 and the third adapter 400, one end of the fourth adapter 500 is connected to the other end of the first adapter 200 through a third wire harness 510, the other end of the fourth adapter 500 is connectable to a third electrical device 530, and the fourth adapter 500 is U-shaped.
The laying structure realizes the arrangement of the wiring harness branch channels through the first adapter 200 without adopting a deconcentrator and other accessories, so that the structure is simplified, the weight is lightened, the occupied space is smaller, and the wiring harness branch channels can be flexibly matched with the second adapter 300, the third adapter 400 and the fourth adapter 500 to be used so as to realize the connection of the wiring harness branch channels and equipment; second adapter 300 and third adapter 400 are located the both sides of fourth adapter 500 to adopt the structural design of broken line type, so that connect first consumer 330 and second consumer 430, can reduce the crooked degree of pencil both sides, reduced the occupation space of pencil, fourth adapter 500 is the U type, is favorable to being divided into little pencil with big pencil fast in narrow and small space, in complicated environment, can satisfy the requirement that the pencil laid.
The adapter of multiple shape is used in collocation, can further reduce the turn radius of pencil, is favorable to carrying out the pencil and lays in narrow and small space. Of course, the first adapter 200, the second adapter 300, and the third adapter 400 in the present invention can be flexibly used in combination, and for the electric device with a good installation position of the socket, the connection structure of the first adapter 200 and the third adapter 400 can be adopted, and for the electric device with a poor installation position of the socket, for example, the socket is located below the electric device, the connection mode of the fourth adapter 500 can be adopted, which can reduce the length of the branch of the wire harness, reduce the turning radius of the wire harness, and save the installation space. The first wire harness 310, the second wire harness 410 and the third wire harness 510 are connected to the bifurcating structure 210 of the first adapter 200, and the number of the bifurcating structures 210 in the first adapter 200 can be increased or decreased according to actual situations, and in the embodiment of the present invention, three bifurcating structures 210 are provided.
Specifically, the first wire harness 310, the second wire harness 410 and the third wire harness 510 all comprise wires and protective sleeves, the wires are arranged inside the protective sleeves, the wires are distributed inside after being separated by the first adapter 200, winding among the wires can be avoided, the protective sleeves can effectively protect the wires, and continuous work of a laying structure in a complex environment is facilitated. Further, the protective sleeve sequentially comprises an insulating layer, a shielding layer and a protective layer from inside to outside, the first wire harness 310, the second wire harness 410 and the third wire harness 510 are high in overall hardness and strong in impact resistance, and under the connection of the first adapter 200, the second adapter 300 and the third adapter 400, the large turning radius does not need to be provided, so that the requirement of laying the wire harnesses can be met. In some embodiments, the protective sleeve further comprises a protective sleeve disposed between the insulating layer and the shielding layer, and all or some of the insulating layer, the protective sleeve, the shielding layer and the protective layer may be combined according to actual needs, so as to meet different protection requirements by increasing or decreasing the number of layers of the protective sleeve. Further, the protective layer is a waterproof protective layer or an oil-proof protective layer. Further, one end of each of the protecting sleeves of the first wire harness 310, the second wire harness 410 and the third wire harness 510 is tightly connected with the first adapter 200 through glue, and the other end is tightly connected with one end of each of the second adapter 300, the third adapter 400 and the fourth adapter 500 through glue, so as to ensure that the waterproof requirement is met.
Specifically, the second adapter 300 is connected to the first electrical device 330 through the first connector plug 320, the wires in the first harness 310 are connected to the first connector plug 320 through welding/crimping, and similarly, the third adapter 400 is connected to the second electrical device 430 through the second connector plug 420, the wires in the second harness 410 are connected to the second connector plug 420 through welding/crimping, the fourth adapter 500 is connected to the third electrical device 530 through the third connector plug 520, and the wires in the third harness 510 are connected to the third connector plug 520 through welding/crimping, so that the connection between the aircraft harness and the electrical device is achieved. Specifically, the other end of the second adapter 300 is threadedly coupled to the first connector plug 320, the other end of the third adapter 400 is threadedly coupled to the second connector plug 420, and the other end of the fourth adapter 500 is threadedly coupled to the third connector plug 520, so as to facilitate quick installation and replacement.
Specifically, one end of the first adapter 200 is threadedly coupled to the main plug 100 to facilitate connection of the main plug 100 and to facilitate installation, removal and replacement. In some embodiments, each of the second adaptor 300 and the third adaptor 400 includes a first connection section and a second connection section, the first connection section and the second connection section are in arc transition connection, and an included angle between an axis of the first connection section and an axis of the second connection section is 45 degrees, so that a turning radius of the wire harness can be reduced, and the wire harness can be laid in a narrow space.
In the description of the present invention, the meaning of a plurality of means is one or more, the meaning of a plurality of means is two or more, and larger, smaller, larger, etc. are understood as excluding the number, and larger, smaller, inner, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
In the description of the present invention, unless otherwise explicitly limited, terms such as arrangement, installation, connection and the like should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention in combination with the specific contents of the technical solutions.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the gist of the present invention.
Claims (10)
1. An aircraft harness laying structure characterized by comprising
A main plug (100);
a first adapter (200), one end of the first adapter (200) is connected with the main plug (100), and the other end of the first adapter has a plurality of branch structures (210);
a second adapter (300), wherein one end of the second adapter (300) is connected with the other end of the first adapter (200) through a first wire harness (310), the other end of the second adapter (300) can be connected with a first electric device (330), and the second adapter (300) is of a broken line type structure;
a third adapter (400), wherein one end of the third adapter (400) is connected with the other end of the first adapter (200) through a second wire harness (410), the other end of the third adapter (400) can be connected with a second electrical device (430), and the third adapter (400) is of a fold line type structure;
a fourth adapter (500) located between the second adapter (300) and the third adapter (400), wherein one end of the fourth adapter (500) is connected with the other end of the first adapter (200) through a third wire harness (510), the other end of the fourth adapter (500) can be connected with a third electric device (530), and the fourth adapter (500) is U-shaped.
2. An aircraft harness routing structure according to claim 1, wherein the first harness (310), the second harness (410) and the third harness (510) each comprise a conductive wire and a protective jacket, the conductive wire being provided inside the protective jacket.
3. An aircraft harness routing structure according to claim 2, wherein the protective sleeve comprises, in order from the inside to the outside, an insulating layer, a shielding layer and a protective layer.
4. An aircraft wiring harness routing structure according to claim 3, wherein the protective sleeve further comprises a protective sleeve disposed between the insulating layer and the shielding layer.
5. An aircraft wire harness installation structure according to claim 3 or 4, wherein the protective layer is a water-repellent protective layer or an oil-repellent protective layer.
6. An aircraft harness routing structure according to claim 2, wherein the protective sheaths of the first (310), second (410) and third (510) harnesses are each secured at one end to the first adapter (200) by adhesive and at the other end to one end of the second (300), third (400) and fourth (500) adapters respectively by adhesive.
7. An aircraft harness routing structure according to claim 2, wherein the second adapter (300) connects the first electrical device (330) by means of a first connector plug (320), the wires in the first wire harness (310) are connected with the first connector plug (320) by means of welding/crimping, the third adapter (400) is connected to the second electrical device (430) by means of a second connector plug (420), the wires in the second wire harness (410) are connected with the second connector plug (420) by means of welding/crimping, said fourth adapter (500) being connected to said third electrical device (530) by means of a third connector plug (520), the wires within the third harness (510) are connected to the third connector plug (520) by means of soldering/crimping.
8. An aircraft harness routing structure according to claim 7, wherein the other end of the second adapter (300) is threadedly connected to the first connector plug (320), the other end of the third adapter (400) is threadedly connected to the second connector plug (420), and the other end of the fourth adapter (500) is threadedly connected to the third connector plug (520).
9. An aircraft harness routing structure according to claim 1, wherein one of the ends of the first adapter (200) is threaded onto the main plug (100).
10. An aircraft harness routing structure according to claim 1, wherein the second adapter (300) and the third adapter (400) each comprise a first connection section and a second connection section, the first connection section and the second connection section being arc transition connected, and the angle between the axis of the first connection section and the axis of the second connection section being 45 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110371820.1A CN113097946A (en) | 2021-04-07 | 2021-04-07 | Aircraft wiring harness laying structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110371820.1A CN113097946A (en) | 2021-04-07 | 2021-04-07 | Aircraft wiring harness laying structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113097946A true CN113097946A (en) | 2021-07-09 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110371820.1A Pending CN113097946A (en) | 2021-04-07 | 2021-04-07 | Aircraft wiring harness laying structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113097946A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205376959U (en) * | 2015-12-31 | 2016-07-06 | 苏州卓德电子有限公司 | Automobile wire harness |
| CN110556677A (en) * | 2019-09-06 | 2019-12-10 | 沈阳兴华航空电器有限责任公司 | wire harness structure with fireproof and anti-electromagnetic interference functions |
| CN110767379A (en) * | 2019-08-26 | 2020-02-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Wire harness branching sleeve |
| CN211930186U (en) * | 2020-05-22 | 2020-11-13 | 沈阳兴华航空电器有限责任公司 | Aircraft landing gear wire harness with rigid and flexible combined structure |
-
2021
- 2021-04-07 CN CN202110371820.1A patent/CN113097946A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205376959U (en) * | 2015-12-31 | 2016-07-06 | 苏州卓德电子有限公司 | Automobile wire harness |
| CN110767379A (en) * | 2019-08-26 | 2020-02-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Wire harness branching sleeve |
| CN110556677A (en) * | 2019-09-06 | 2019-12-10 | 沈阳兴华航空电器有限责任公司 | wire harness structure with fireproof and anti-electromagnetic interference functions |
| CN211930186U (en) * | 2020-05-22 | 2020-11-13 | 沈阳兴华航空电器有限责任公司 | Aircraft landing gear wire harness with rigid and flexible combined structure |
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| PB01 | Publication | ||
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Application publication date: 20210709 |