CN113629607B - Cable bundle structure suitable for spacecraft and wiring method thereof - Google Patents
Cable bundle structure suitable for spacecraft and wiring method thereof Download PDFInfo
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- CN113629607B CN113629607B CN202110780455.XA CN202110780455A CN113629607B CN 113629607 B CN113629607 B CN 113629607B CN 202110780455 A CN202110780455 A CN 202110780455A CN 113629607 B CN113629607 B CN 113629607B
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- cable
- cable support
- barrel
- top plate
- laminate
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- 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
- H02G3/0406—Details thereof
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- 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
- H02G1/00—Methods or apparatus specially adapted for installing, maintaining, repairing or dismantling electric cables or lines
- H02G1/06—Methods or apparatus specially adapted for installing, maintaining, repairing or dismantling electric cables or lines for laying cables, e.g. laying apparatus on vehicle
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- 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
- H02G3/0456—Ladders or other supports
Abstract
The invention provides a cable harness structure suitable for a spacecraft and a wiring method thereof, wherein the cable harness structure comprises a column-cone assembly, wherein the column-cone assembly comprises a first cone barrel, a second cone barrel and a column barrel; the first conical barrel and the second conical barrel are respectively connected and arranged at two ends of the column barrel; the column-cone assembly is provided with a top plate and a layer plate, the top plate is arranged on the first cone barrel, and the layer plate is connected and arranged at the connecting position of the first cone barrel and the column barrel; a top plate cable support is arranged on the top plate, a layer plate cable support is arranged on the layer plate, and a light cable support is arranged on the first conical barrel; an operation hole is formed in the first conical barrel; the first conical barrel is provided with a traction rope, and the traction rope penetrates through the operation hole. The invention solves the difficult problem of cable routing of the closed structure body and avoids the risk of collision between the cable and a single machine in the cabin.
Description
Technical Field
The invention relates to the technical field of cable wiring in a spacecraft cabin body with a semi-closed structure, in particular to a cable bundle structure suitable for a spacecraft and a wiring method thereof.
Background
A spacecraft of a certain model adopts a column-cone combined structure, and a single machine in a combined body can be operated only when a top plate is in an open state. According to the layout design of the spacecraft, the single machines are arranged on the top plate and the inner plate of the cabin body of the combination, and signals are transmitted between the single machines of the top plate and the single machines of the plate through cables. The wiring of cable need compromise can carry out the plug operation to the cable in ground test stage, can fix the cable when sealing the cabin.
Patent document No. CN106793647A discloses a method for laying out large-current transmission cables on satellites, which includes the following steps: according to the function and the signal property of the connecting line, two platform buses, two T/R buses and four buses related to the on-satellite cable of the high-current primary power line are found out, and the parts which can be twisted or cannot be twisted on the high-current transmission paths of the four buses are determined; collecting four cables with the same type of signals of the buses together for wiring; controlling the direction of a cable on the satellite related to a high-current primary power line by adopting a forced inspection point; and in the whole satellite magnetic testing process, the residual magnetic variation caused by the cable trend is tested and calculated, and the magnetic distance variation of the whole satellite caused by the large-current transmission of the cable is ensured to be within 3A.m 2. However, the patent document cannot realize the wiring and fixing of the cable in two states of opening and closing the cabin, and the risk that the cable cannot be fixed and collide with a single machine exists, so that the cable or the single machine is damaged.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a cable bundle structure suitable for a spacecraft and a wiring method thereof.
The cable harness structure suitable for the spacecraft comprises a column-cone assembly, wherein the column-cone assembly comprises a first cone barrel, a second cone barrel and a column barrel; the first conical barrel and the second conical barrel are respectively connected and arranged at two ends of the column barrel;
the column-cone assembly is provided with a top plate and a layer plate, the top plate is connected and arranged at one end of the first cone barrel, which is far away from the column barrel, and the layer plate is connected and arranged at the connecting position of the first cone barrel and the column barrel;
a top plate cable support used for binding and fixing a cable is arranged on the top plate, a layer plate cable support used for binding and fixing a cable is arranged on the layer plate, and a light cable support used for binding and fixing a cable is arranged on the first conical barrel;
the first conical barrel is provided with an operating hole, the operating hole is positioned on one side of the laminate cable support, and the operating hole is higher than the top end of the laminate cable support; the light cable bracket is arranged on the inner wall of the first conical barrel and is positioned at the lower end of the operation hole;
the first cone barrel is provided with a traction rope for drawing the cable, and the traction rope penetrates through the operation hole.
Preferably, the roof cable support includes a first roof cable support and a second roof cable support, and the first roof cable support and the second roof cable support are oppositely disposed on the roof.
Preferably, the laminate cable support comprises a first laminate cable support and a second laminate cable support, and the first laminate cable support and the second laminate cable support are oppositely arranged on the laminate at intervals.
Preferably, a first binding groove for binding and fixing the cable is arranged on the top plate cable support.
Preferably, a plurality of first binding grooves are arranged on the top plate cable support at intervals along the extending direction of the top plate cable support.
Preferably, the distance between adjacent first binding grooves is 10 cm.
Preferably, a second binding groove for binding and fixing the cable is arranged on the laminate cable support.
Preferably, a plurality of second binding grooves are formed in the laminate cable support at intervals along the extending direction of the laminate cable support.
Preferably, the distance between adjacent second binding grooves is 10 cm.
The invention also provides a wiring method based on the cable bundle structure suitable for the spacecraft, which comprises the following steps:
the method comprises the following steps: a free section cable between the laminate cable support and the top plate cable support is a traction rope, and the traction rope is led out from an operation hole on the first conical barrel;
step two: the hoisting top plate stops moving downwards for about ten centimeters, the cable is bound at a first binding groove part of the inclined edge along the inclined edge of the cable support of the semi-Y-shaped top plate so as to reduce the length of the cable at the suspension section;
step three: hoisting the top plate downwards again, and simultaneously drawing the free section to the outer side of the column-cone assembly through a drawing rope, so that the cable moves to the inner side of the first cone barrel;
step four: the top plate reaches the position of closing the cover, and the free section cable is pulled to the operation hole region by the haulage rope simultaneously, uses the ribbon to ligature the cable on the inboard light-duty cable support of first awl bucket, tears down the haulage rope on the cable, uses the thermal control multilayer to seal the operation hole.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention realizes the connection of the layer plate and the top plate cable through the cable bracket, and solves the difficult problem that the cable is difficult to fix due to the limited operation in the cabin of the column-cone combined isomer structure;
2. the invention adopts a mode that the cable is straight up and straight down, thereby reducing the problem that the length of the inner side of the cable winding cone barrel is too long, and reducing the weight of the cable;
3. the invention ensures that the cable can adapt to different states during cabin opening and cabin closing by matching the laminate bracket, the top plate bracket and the light bracket of the cone drum cable, solves the risk that the cable cannot be fixed and collide with a single machine during cabin closing, and has reasonable and reliable design;
4. the invention finishes wiring in the semi-closed special-shaped structure body, and the wiring mode can give consideration to two states of cabin opening and cabin closing, so that the cable is in a fixed state during final emission, and the risk of the cable colliding with a single machine is avoided.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic wiring diagram of a cable harness structure suitable for a spacecraft of the present invention in an open-cabin state;
FIG. 2 is a schematic view of the wiring of a cable harness structure suitable for a spacecraft of the present invention in a capsule-sealed state;
FIG. 3 is a schematic structural view of a cable harness structure for a spacecraft of the present invention highlighting a first lashing groove;
fig. 4 is a schematic structural view of a cable harness structure suitable for a spacecraft of the present invention highlighting the second lashing groove.
The figures show that:
column cone assembly 1 layer plate cable support 5
First binding groove 9 of roof cable support 4
Second binding groove 10 of first top plate cable support 401
Second ceiling cable holder 402 cable 11
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1 and fig. 2, the cable harness structure suitable for a spacecraft provided by the invention includes a cylindrical-conical assembly 1, where the cylindrical-conical assembly 1 includes a first conical barrel 101, a second conical barrel 102 and a cylindrical barrel 103, and the first conical barrel 101 and the second conical barrel 102 are respectively connected and disposed at two ends of the cylindrical barrel 103. Be provided with roof 2 and plywood 3 on the column cone assembly 1, roof 2 is connected and is set up the one end of keeping away from column barrel 103 at first awl bucket 101, plywood 3 is connected and is set up the hookup location department at first awl bucket 101 and column barrel 103, be provided with the roof cable support 4 that is used for ligature fixed cable on the roof 2, be provided with the plywood cable support 5 that is used for ligature fixed cable on the plywood 3, be provided with light-duty cable support 6 that is used for ligature fixed cable on first awl bucket 101, set up handle hole 7 on first awl bucket 101, handle hole 7 is located plywood cable support 5 one side, handle hole 7 is higher than 5 tops of plywood cable support, light-duty cable support 6 sets up the position department that is located handle hole 7 lower extreme on first awl bucket 101 inner wall, be provided with haulage rope 8 that is used for tractive cable on first awl bucket 101, haulage rope 8 passes handle hole 7 and sets up.
All set up the unit on roof 2 and the plywood 3, reserve one section free cable between roof cable support 4 and the plywood cable support 5 for 2 units of roof and under-deck units operate under 2 opening state of roof. Under the state that the top plate 2 is covered, the layer plate 3 divides the cable into two bundles, the two cable bundles respectively go upwards through a layer plate cable support 5, are fixed through a light cable support 6 on the inner side of the first conical barrel 101 and enter a wiring area of the top plate 2 through a top plate cable support 4; under the state that the top plate 2 is not covered, the cable bundle directly crosses through the laminate cable support 5 and enters the top plate cable support 4, and the cable between the laminate cable support 5 and the top plate cable support 4 is in a free suspension state, so that the operation in the cabin is facilitated.
As shown in fig. 3 and 4, the top plate cable support 4 is provided with first binding grooves 9 for binding and fixing cables, the top plate cable support 4 is provided with a plurality of first binding grooves 9 at intervals along the extending direction of the top plate cable support, the distance between every two adjacent first binding grooves 9 is 10cm, and binding adhesive tapes are used for fixing the positions of the cables in the first binding grooves 9. Be provided with the second ligature recess 10 that is used for the ligature fixed cable on the plywood cable support 5, be provided with a plurality of second ligature recesses 10 along its self extending direction interval on the plywood cable support 5, the distance between adjacent second ligature recess 10 is 10cm, uses the position of ligature sticky tape fixed cable at second ligature recess 10.
The invention realizes the connection of the cables of the layer plate 3 and the top plate 2 through the cable bracket, and solves the difficult problem that the cables are difficult to fix due to the limited operation in the cabin of the column-cone combined isomer structure.
The invention also provides a wiring method based on the cable bundle structure suitable for the spacecraft, which comprises the following steps:
the method comprises the following steps: a free section cable between the laminate cable support 5 and the top plate cable support 4 is a traction rope 8, and the traction rope 8 is led out from an operation hole 7 on the first conical barrel 101;
step two: the hoisting top plate 2 stops moving downwards for about ten centimeters, the cable is bound at the first binding groove 9 part of the inclined edge along the inclined edge direction of the cable support 4 of the semi-Y-shaped top plate so as to reduce the length of the cable at the suspension section;
step three: hoisting the top plate 2 downwards again, and simultaneously drawing the free section to the outer side of the column-cone assembly 1 through the drawing rope 8, and moving the cable to the inner side of the first cone barrel 101;
step four: the top plate 2 reaches the position of closing the cover, and simultaneously the free section cable is pulled to the area of the operation hole 7 by the hauling cable 8, the cable is bound on the light cable support 6 on the inner side of the first conical barrel 101 by using a binding belt, the hauling cable 8 on the cable is detached, and the operation hole 7 is sealed by using the thermal control multilayer.
As shown in fig. 1, the cone-column assembly is in an open-cabin state, a top plate 2 is fixed at a position fifty centimeters away from a mounting surface of the top plate 2, cables on a layer plate 3 are gathered into two bundles at a layer plate cable support 5 after being combed, the gathered cables are arranged along the trend of the layer plate cable support 5, and binding and fixing are carried out at a second binding groove 10. The cable bundle continuously extends upwards after being separated from the laminate cable support 5, is pre-fixed after reaching the top plate cable support 4, continuously reaches the mounting surface of the top plate 2 along the top plate cable support 4, and is distributed to different single machines. Under the state of opening the cabin, the top plate 2 is opened, the operation in the cabin is convenient to carry out, and the length of the cable at the free section is about sixty centimeters at the moment.
As shown in fig. 2, the cone-column assembly is closed, the lifting top plate 2 stops moving downwards about ten centimeters, the cable moves along the bevel edge of a half-Y bracket of the top plate 2, the cable is bound at the position of a first binding groove 9 for binding the bevel edge, the free section cable is ensured to extend towards the wall direction of the first cone barrel 101, meanwhile, the length of the suspension section cable is reduced, the lifting top plate 2 moves downwards again, meanwhile, the free section cable is pulled towards the outer side of the cone-column assembly through a traction rope 8 to move towards the inner side of the first cone barrel 101, the top plate 2 reaches the cover closing position, meanwhile, the free section cable is pulled to an operation hole 7 area through the traction rope 8, the cable is bound on a light cable bracket 6 at the inner side of the first cone barrel 101 through a binding belt, the traction rope 8 on the cable is removed, and the operation hole 7 is closed through a thermal control multilayer.
The invention finishes wiring in the semi-closed special-shaped structure body, and the wiring mode can give consideration to two states of cabin opening and cabin closing, so that the cable is in a fixed state during final emission, and the risk of the cable colliding with a single machine is avoided.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the 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 application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A cable bundle structure suitable for a spacecraft is characterized by comprising a column-cone combination body (1), wherein the column-cone combination body (1) comprises a first cone barrel (101), a second cone barrel (102) and a column barrel (103); the first conical barrel (101) and the second conical barrel (102) are respectively connected and arranged at two ends of the column barrel (103);
a top plate (2) and a layer plate (3) are arranged on the column-cone assembly (1), the top plate (2) is connected and arranged at one end, away from the column barrel (103), of the first cone barrel (101), and the layer plate (3) is connected and arranged at the connecting position of the first cone barrel (101) and the column barrel (103);
a top plate cable support (4) for binding and fixing cables is arranged on the top plate (2), a layer plate cable support (5) for binding and fixing cables is arranged on the layer plate (3), and a light cable support (6) for binding and fixing cables is arranged on the first conical barrel (101);
an operation hole (7) is formed in the first conical barrel (101), the operation hole (7) is located on one side of the laminate cable support (5), and the operation hole (7) is higher than the top end of the laminate cable support (5); the light cable bracket (6) is arranged on the inner wall of the first conical barrel (101) at the position of the lower end of the operation hole (7);
the first taper barrel (101) is provided with a traction rope (8) for drawing a cable, and the traction rope (8) penetrates through the operation hole (7).
2. The cable harness structure for a spacecraft of claim 1, wherein the ceiling cable support (4) comprises a first ceiling cable support (401) and a second ceiling cable support (402), the first ceiling cable support (401) and the second ceiling cable support (402) being oppositely disposed on the ceiling (2).
3. A cable bundle structure suitable for a spacecraft according to claim 1, wherein the laminate cable support (5) comprises a first laminate cable support (501) and a second laminate cable support (502), the first laminate cable support (501) and the second laminate cable support (502) being arranged in spaced opposition on the laminate (3).
4. A cable harness structure for a spacecraft as claimed in claim 1, wherein the roof cable support (4) is provided with a first lashing groove (9) for lashing and securing cables.
5. A cable harness structure for a spacecraft as claimed in claim 4, wherein the roof cable support (4) has a plurality of first lashing grooves (9) spaced along its own extension.
6. Cable bundle structure for a spacecraft according to claim 5, characterised in that the distance between adjacent first lashing grooves (9) is 10 cm.
7. A cable harness structure for a spacecraft as claimed in claim 1, wherein the laminate cable support (5) is provided with a second lashing groove (10) for lashing and securing cables.
8. A cable harness structure for a spacecraft as claimed in claim 7, wherein the laminate cable support (5) is provided with a plurality of second lashing grooves (10) at intervals along its own extension direction.
9. A cable harness structure for a spacecraft according to claim 8, wherein the distance between adjacent second lashing grooves (10) is 10 cm.
10. A wiring method based on a cable harness structure for a spacecraft according to any one of claims 1 to 9, characterized in that it comprises the following steps:
the method comprises the following steps: a free section cable between the laminate cable support (5) and the top plate cable support (4) is a hauling cable (8), and the hauling cable (8) is led out from an operation hole (7) on the first conical barrel (101);
step two: the hoisting top plate (2) stops moving downwards for about ten centimeters, the cable is bound at the first binding groove (9) part of the inclined edge along the inclined edge direction of the cable support (4) of the semi-Y-shaped top plate so as to reduce the length of the cable at the suspension section;
step three: the hoisting top plate (2) moves downwards again, meanwhile, the free section is pulled to the outer side of the column-cone combined body (1) through the pulling rope (8), and the cable moves to the inner side of the first cone barrel (101);
step four: the top plate (2) reaches the cover closing position, meanwhile, the free-section cable is pulled to the area of the operation hole (7) by the pulling rope (8), the cable is bound on the light cable support (6) on the inner side of the first conical barrel (101) by using a binding belt, the pulling rope (8) on the cable is detached, and the operation hole (7) is sealed by using the thermal control multilayer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110780455.XA CN113629607B (en) | 2021-07-09 | 2021-07-09 | Cable bundle structure suitable for spacecraft and wiring method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110780455.XA CN113629607B (en) | 2021-07-09 | 2021-07-09 | Cable bundle structure suitable for spacecraft and wiring method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113629607A CN113629607A (en) | 2021-11-09 |
| CN113629607B true CN113629607B (en) | 2022-08-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110780455.XA Active CN113629607B (en) | 2021-07-09 | 2021-07-09 | Cable bundle structure suitable for spacecraft and wiring method thereof |
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| CN (1) | CN113629607B (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3196024B2 (en) * | 1998-11-10 | 2001-08-06 | ヒエン電工株式会社 | Spiral support for cable suspension |
| KR101579567B1 (en) * | 2010-02-11 | 2015-12-22 | 호워드 엠. 친 | Rocket launch system |
| CN106793647A (en) * | 2016-11-09 | 2017-05-31 | 上海卫星工程研究所 | High current transmission cable layout method on a kind of satellite |
| CN110162923B (en) * | 2019-06-03 | 2020-04-03 | 北京卫星环境工程研究所 | Flexible cable process digital prototype construction system and method for spacecraft assembly |
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2021
- 2021-07-09 CN CN202110780455.XA patent/CN113629607B/en active Active
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