CN117960955A - Non-equal-length end shearing method for preventing aircraft cable from being broken - Google Patents
Non-equal-length end shearing method for preventing aircraft cable from being broken Download PDFInfo
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- CN117960955A CN117960955A CN202410079393.3A CN202410079393A CN117960955A CN 117960955 A CN117960955 A CN 117960955A CN 202410079393 A CN202410079393 A CN 202410079393A CN 117960955 A CN117960955 A CN 117960955A
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- aircraft cable
- cable
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- wire
- shearing
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- 238000010008 shearing Methods 0.000 title claims abstract description 40
- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000005452 bending Methods 0.000 claims abstract description 11
- 238000004088 simulation Methods 0.000 claims abstract description 11
- 238000004519 manufacturing process Methods 0.000 claims abstract description 6
- 238000005520 cutting process Methods 0.000 claims description 13
- 239000003550 marker Substances 0.000 claims description 2
- 238000012545 processing Methods 0.000 abstract description 8
- 238000013461 design Methods 0.000 abstract description 2
- 230000008054 signal transmission Effects 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 5
- 238000012423 maintenance Methods 0.000 description 3
- 241001391944 Commicarpus scandens Species 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Abstract
The invention discloses a non-equal-length end shearing method for preventing an aircraft cable from being broken, which comprises the following steps of: 1) Simulating the radius and angle of bending of the aircraft cable according to the three-dimensional digital model of the aircraft cable, and setting a shearing allowance according to the simulation condition of the aircraft cable to finish the primary shearing of the aircraft cable; 2) Manufacturing a matched shearing line mould according to the electric connector data of the aircraft cable; 3) Leading out each wire at the connection end of the aircraft cable and the electric connector, and sleeving a marking tube which is convenient to identify and process on each led-out wire; 4) And (3) installing and fixing each wire in a shearing standardized die according to a marking pipe sleeved on each wire in the aircraft cable, and shearing the cable at the rear part of the die. The invention solves the problems of design and processing of the aircraft cable in the industry for a long time, ensures the signal transmission safety of the power supply system and each system of the aircraft system, and avoids the system non-work or failure caused by line failure.
Description
Technical Field
The invention relates to the technical field of aviation equipment, in particular to a non-equal-length end shearing method for preventing an aircraft cable from being broken.
Background
With the continuous development of aircraft technology, aircraft cables are designed, used and maintained in a mode of rising to an electrical interconnection system, so that the system is required to have stable working performance, is safe and reliable, and meets the working requirements of the aircraft in different environments.
However, the conventional aircraft cable only considers the cable branch length, and the cable bending and twisting factors are not integrated into specific processing operations. For example, the factors of bending and torsion of the cable are not integrated into specific processing operation, only the cable length is considered for shearing the electric wire, so that the processed cable is tidy, but the bent outer electric wire is stressed greatly when the cable is installed on a machine, and is easy to break from a termination processing position. The number of the wires of the plug seat connected by partial cables is more, the number of the wires reaches hundreds, the wires in the middle of the plug seat are sheared as well as the wires at the outer edge, after the wires are connected, the wires at the outer edge are found to be stressed greatly, the wires at the middle are extruded and folded, the wires at the outer side are broken in a pulling way during installation, and the wires are more easily twisted and broken during aircraft flight. The termination of many cables is thus easily broken, making the aircraft unable to work properly and even catastrophic. Therefore, it is very important to solve the termination breakage of the cable wiring. According to the turning direction of the cable and the installation stress, the control is carried out from the wiring processing, the wiring part is prevented from suffering larger stress, the problem that needs to be solved rapidly at present is solved by finding out how to reduce or eliminate the stress at the termination part of the cable wiring from the cutting of the wires.
Disclosure of Invention
The invention aims to provide a system capable of avoiding system non-work or faults caused by line faults, guaranteeing flight safety and completing tasks of safe flight and specified execution; the non-equal-length end shearing method for preventing the cable of the airplane from being broken can reduce maintenance frequency, improve the attendance rate and the service efficiency of the airplane, save time and reduce the use cost.
The invention is realized by the following technical scheme: a non-equal length end shearing method for preventing breakage of an aircraft cable, comprising the steps of:
(1) Simulating the radius and angle of bending of the aircraft cable according to the three-dimensional digital model of the aircraft cable, and setting a shearing allowance according to the simulation condition of the aircraft cable to finish the primary shearing of the aircraft cable;
(2) Manufacturing a matched shearing line mould according to the electric connector data of the aircraft cable;
(3) Leading out each wire at the connection end of the aircraft cable and the electric connector, and sleeving a marking tube which is convenient to identify and process on each led-out wire;
(4) And (3) installing and fixing each wire in a shearing standardized die according to a marking pipe sleeved on each wire in the aircraft cable, and shearing the cable at the rear part of the die.
The working principle of the technical scheme is that if the traditional method is adopted, the wires are cut in order after being pulled, the wires of the cable part after processing or installation are stressed, the wires are broken in actual work, and airplane faults or accidents are caused. The electric connector connected with the aircraft cable is mainly divided into a circular shape and a rectangular shape from the appearance, and the electric connector in each shape has a series type spectrum according to specific standards; according to the existing standard electric connector, a standardized series of tangent molds are designed, unequal length tangent processing is realized, the single electric wire in the processed cable is ensured not to be stressed, and breakage is avoided.
In order to better realize the method of the invention, in the step (1), the specific simulation process of the radius and the angle of the bending of the aircraft cable is that a two-dimensional map of the aircraft cable model is projected on a plane table, and the layout of the cable is determined to be consistent with the laying pre-object.
In order to better implement the method of the present invention, further, in the step (1), the shearing allowance is set to 300mm.
To better implement the method of the present invention, further, in the step (2), the electrical connector data of the aircraft cable includes a size of the electrical connector and an actual layout position of the pinhole.
In order to better implement the method of the present invention, further, the shear line mold manufactured in the step (2) includes a rectangular electric connector shear line mold and a circular electric connector shear line mold.
In order to better implement the method of the invention, the shear line mould is further provided with a plurality of holes according to the electric connector connected with the aircraft cable, and each wire is installed and fixed in the corresponding wire hole according to the marking pipe.
In order to better implement the method of the present invention, further, the thickness of the shear line die is 100 to 200mm.
In order to better implement the method of the present invention, further, the surface of the marking tube in the step (3) is recorded with the function of each wire and the specific condition to be processed.
Compared with the prior art, the invention has the following advantages:
(1) The invention solves the long-term difficult problems of aircraft cable design and processing in industry, and finds the reason and the solution of the aircraft cable easy to break due to the installation and bending, high-density wiring or thick wire wiring starting from the source of cable termination breakage, thereby fundamentally solving the problems;
(2) The invention ensures the safe and reliable signal transmission of the power supply system and each system of the aircraft system, so that the aircraft can avoid the system non-work or failure caused by line failure, ensure the flight safety and complete the tasks of safe flight and specified execution;
(3) The invention can reduce maintenance frequency, improve the attendance rate and the use efficiency of the aircraft, save time and reduce the use cost.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic perspective view of an aircraft cable cut using a rectangular electrical connector cut line die in accordance with the present invention;
FIG. 2 is a schematic plan view of an aircraft cable cut using a rectangular electrical connector cut line die in accordance with the present invention;
FIG. 3 is a schematic perspective view of an aircraft cable cut using a circular electrical connector cut line die in accordance with the present invention;
Wherein: 1-aircraft cable, 2-wire, 3-marker tube, 4-rectangular electrical connector trim line die, 5-circular electrical connector trim line die.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; or may be directly connected, or may be indirectly connected through an intermediate medium, or may be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Example 1:
the embodiment provides a non-equal length end shearing method for preventing an aircraft cable from being broken, which comprises the following steps:
(1) According to the three-dimensional digital model of the aircraft cable, performing radius and angle simulation of bending of the aircraft cable, projecting a two-dimensional graph of the aircraft cable model on a plane table, determining that the layout of the cable is consistent with that of a laid pre-material object, setting a shearing allowance of 300mm according to the simulation condition of the aircraft cable, and completing preliminary shearing of the aircraft cable; the shearing allowance is reserved for the purpose of adjusting the wire of the aircraft cable when passing through the shearing line mould;
(2) Manufacturing a shearing line mould with the thickness of 100-200 mm matched with the electric connector of the aircraft cable according to the size of the electric connector and the actual layout position of the pinholes;
(3) Leading out each wire at the connection end of the aircraft cable and the electric connector, and sleeving a marking pipe which is convenient to identify and process on each led out wire, wherein the surface of the marking pipe is recorded with the function of each wire and the specific condition to be processed;
(4) And (3) installing and fixing each wire in a shearing standardized die according to a marking pipe sleeved on each wire in the aircraft cable, and shearing the cable at the rear part of the die.
The thus obtained non-equal length severed aircraft cable allows for adjustment of the length of the sheared wire based on the termination of the aircraft cable installation bend, high density wire or thick wire connection.
The aircraft can avoid the system non-work or failure caused by the occurrence of line failure, ensure the flight safety and complete the tasks of safe flight and specified execution; the maintenance frequency can be reduced, the attendance rate and the use efficiency of the aircraft are improved, the time is saved, and the use cost is reduced.
Example 2:
based on the above embodiments, the present embodiment provides a cutting line mold for rectangular electrical connectors, which is used for performing a non-equal length end cutting process of an aircraft cable, as shown in fig. 1 and 2:
According to a three-dimensional model of the aircraft cable 1, performing radius and angle simulation of bending of the aircraft cable 1, projecting a two-dimensional graph of the aircraft cable model on a plane table, determining that the layout of the aircraft cable is consistent with that of a laid pre-object, setting a shearing allowance of 300mm according to the simulation condition of the aircraft cable 1, and completing preliminary shearing of the aircraft cable; manufacturing a rectangular electric connector shear line mould 4 with the thickness of 100mm aiming at the size of the rectangular point connector and the actual layout position of pinholes; leading out each electric wire 2 at the connection end of the aircraft cable 1 and the electric connector, and sleeving a marking tube 3 which is convenient to identify and process on each led-out electric wire 2, wherein the surface of the marking tube records the function of each electric wire and the specific condition to be processed; the rectangular electric connector shearing line mould 4 is provided with a plurality of holes according to the electric connector connected with the aircraft cable, each electric wire 2 is installed and fixed in the corresponding wire hole according to the marking pipe 3, and finally the electric wire is sheared on the back of the mould, so that the aircraft cable 1 with non-equal length ends connected with the rectangular electric connector is obtained.
Example 3:
based on the above embodiments, the present embodiment provides a cutting line mold for rectangular electrical connectors, which is used for performing a non-equal length end cutting process of an aircraft cable, as shown in fig. 3:
According to a three-dimensional model of the aircraft cable 1, performing radius and angle simulation of bending of the aircraft cable 1, projecting a two-dimensional graph of the aircraft cable model on a plane table, determining that the layout of the aircraft cable is consistent with that of a laid pre-object, setting a shearing allowance of 300mm according to the simulation condition of the aircraft cable 1, and completing preliminary shearing of the aircraft cable; manufacturing a rectangular electric connector shearing line mould 5 with the thickness of 150mm aiming at the size of the rectangular point connector and the actual layout position of pinholes; leading out each electric wire 2 at the connection end of the aircraft cable 1 and the electric connector, and sleeving a marking tube 3 which is convenient to identify and process on each led-out electric wire 2, wherein the surface of the marking tube records the function of each electric wire and the specific condition to be processed; the rectangular electric connector shearing line mould 4 is provided with a plurality of holes according to the electric connector connected with the aircraft cable, each electric wire 2 is installed and fixed in the corresponding wire hole according to the marking pipe 3, and finally the electric wire is sheared on the back of the mould, so that the aircraft cable 1 with non-equal length ends connected with the rectangular electric connector is obtained.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the spirit and principles of the invention, the scope of which is defined by the claims and their equivalents.
Claims (8)
1. A non-equal length end shearing method for preventing breakage of an aircraft cable, comprising the steps of:
(1) Simulating the radius and angle of bending of the aircraft cable according to the three-dimensional digital model of the aircraft cable, and setting a shearing allowance according to the simulation condition of the aircraft cable to finish the primary shearing of the aircraft cable;
(2) Manufacturing a matched shearing line mould according to the electric connector data of the aircraft cable;
(3) Leading out each wire at the connection end of the aircraft cable and the electric connector, and sleeving a marking tube which is convenient to identify and process on each led-out wire;
(4) And (3) installing and fixing each wire in a shearing standardized die according to a marking pipe sleeved on each wire in the aircraft cable, and shearing the cable at the rear part of the die.
2. The non-equal length end shearing method for preventing aircraft cable breakage according to claim 1, wherein in the step (1), the specific simulation process of the radius and angle of the bending of the aircraft cable is that a two-dimensional map of an aircraft cable model is projected on a plane table, and the layout of the cable is determined to be consistent with the laying pre-physical object.
3. A non-equal length end cutting method for preventing breakage of aircraft cables according to claim 1 or 2, wherein in said step (1), the cutting allowance is set to 300mm.
4. A non-isometric end cutting method for preventing breakage of an aircraft cable according to claim 1 or claim 2, wherein in step (2) the electrical connector data of the aircraft cable includes the size of the electrical connector and the actual placement of pinholes.
5. The method of claim 4, wherein the wire-cutting dies manufactured in step (2) comprise rectangular wire-cutting dies and circular wire-cutting dies.
6. A non-equal length end cutting method for preventing breakage of an aircraft cable according to claim 5, wherein said shear line die is provided with a plurality of holes arranged according to electrical connectors connected to the aircraft cable, each wire being mounted and secured in a corresponding wire hole according to a marker tube.
7. The method of claim 6, wherein the thickness of the shear line die is 100-200 mm.
8. A non-equal length end cutting method for preventing breakage of aircraft cables according to claim 1 or 2, wherein the surface of the marking tube in said step (3) is recorded with the function of each wire and the specific condition to be processed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410079393.3A CN117960955A (en) | 2024-01-19 | 2024-01-19 | Non-equal-length end shearing method for preventing aircraft cable from being broken |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410079393.3A CN117960955A (en) | 2024-01-19 | 2024-01-19 | Non-equal-length end shearing method for preventing aircraft cable from being broken |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117960955A true CN117960955A (en) | 2024-05-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410079393.3A Pending CN117960955A (en) | 2024-01-19 | 2024-01-19 | Non-equal-length end shearing method for preventing aircraft cable from being broken |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117960955A (en) |
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2024
- 2024-01-19 CN CN202410079393.3A patent/CN117960955A/en active Pending
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