CN112758360B - Fixed star cabin signal transmission device and butt joint method - Google Patents
Fixed star cabin signal transmission device and butt joint method Download PDFInfo
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- CN112758360B CN112758360B CN202011605540.4A CN202011605540A CN112758360B CN 112758360 B CN112758360 B CN 112758360B CN 202011605540 A CN202011605540 A CN 202011605540A CN 112758360 B CN112758360 B CN 112758360B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
- H01R13/73—Means for mounting coupling parts to apparatus or structures, e.g. to a wall
- H01R13/74—Means for mounting coupling parts in openings of a panel
- H01R13/748—Means for mounting coupling parts in openings of a panel using one or more screws
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R24/00—Two-part coupling devices, or either of their cooperating parts, characterised by their overall structure
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- Aviation & Aerospace Engineering (AREA)
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- Details Of Connecting Devices For Male And Female Coupling (AREA)
Abstract
The invention provides a fixed star cabin signal transmission device and a connection method, wherein the fixed star cabin signal transmission device comprises a main star cabin plate and a propulsion cabin plate, wherein a separation socket is fixedly arranged on the main star cabin plate, and a plug assembly is fixedly arranged on the propulsion cabin plate; the plug assembly comprises a plug fixing plate, a separation plug, a spring and a clamp spring, wherein a limiting hole is formed in the plug fixing plate, the separation plug is embedded in the limiting hole and is in sliding fit with the limiting hole, the separation plug comprises an inserting part and a limiting part, the inserting part and the limiting part are respectively positioned on two sides of the plug fixing plate, and the inserting part is in inserting fit with the separation socket; the side of the separating plug close to the plug-in part is provided with a clamping groove, the clamp spring is embedded in the clamping groove, the spring sleeve is arranged on the separating plug, and two ends of the spring respectively abut against the side wall of the clamp spring and the plug fixing plate which are oppositely arranged. The resilience of the signal transmission device is reduced, so that the damage of the signal transmission device to a main satellite or a propulsion cabin is reduced, and the structure is simple, the working reliability is high, and the applicability is strong.
Description
Technical Field
The invention relates to the technical field of signal transmission between a satellite and a propulsion cabin, in particular to a fixed satellite cabin signal transmission device and a butt joint method.
Background
With the progress of society and the development of science, aerospace technology is more and more mature, and the launching of satellites is more and more frequent.
At present, a satellite in the market adopts a combination mode of a main satellite and a propelling cabin, and the propelling cabin is positioned at the lower part of the main satellite and is used for propelling the main satellite to a working orbit. After the main satellite and the propulsion cabin are separated, the main satellite and the propulsion cabin respectively become independent satellites. The satellite is characterized in that the main satellite needs to provide energy and control for the propulsion cabin and receive telemetering signals during the orbit transfer process.
The existing Chinese patent with publication number CN101995193B is a redundant backup star-arrow separation electric connector separation method, which is characterized by comprising the following steps: (1) The method comprises the following steps that a satellite is installed on a butt joint support for butt joint with a carrier rocket through straps and an explosion bolt assembly, an operation opening is formed in the side edge of the butt joint support, and a separation spring is arranged at the top of the butt joint support; (2) The method comprises the following steps of installing a separation electric connector on a bottom plate of a satellite body, respectively tying two ends of an aramid fiber rope to a base of the separation electric connector and a base of a butt joint support through an operation port, keeping the aramid fiber rope in a loose state, and enabling the length of the aramid fiber rope to be 2-3 mm longer than the distance from the separation electric connector to the base of the butt joint support; (3) After the aramid fiber rope is installed, the operation opening is closed, and the satellite and the bracket are connected with the carrier rocket; (4) Launching the carrier rocket, wherein after an electric connector separation instruction sent by the ground is received, the separation electric connector automatically falls off from the satellite body according to an electric signal, the explosive bolts with belts are unlocked after 1.2 seconds, the separation spring of the butt joint support base pushes the satellite out of the carrier rocket, and the butt joint support is reserved on the carrier rocket; (5) If the electric separation of the separation electric connector is unsuccessful, the separation spring of the butt joint support base ejects the microsatellite to the flight direction, meanwhile, the aramid fiber rope is changed from a loose state to a stretching state, and the separation electric connector is pulled out along the direction opposite to the flight direction, so that the separation electric connector is separated.
The inventor believes that after the electric connector between the carrier rocket and the satellite is separated in the prior art, the situation that the electric connector rebounds to cause damage to the satellite occurs, and a point to be improved exists.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a fixed star cabin signal transmission device and a fixed star cabin signal transmission method.
The fixed star cabin signal transmission device comprises a main star cabin plate and a propulsion cabin plate, wherein a separation socket is fixedly mounted on the main star cabin plate, and a plug assembly is fixedly mounted on the propulsion cabin plate; the plug assembly comprises a plug fixing plate, a separation plug, a spring and a clamp spring, wherein a limiting hole is formed in the plug fixing plate, the separation plug is embedded in the limiting hole and is in sliding fit with the limiting hole, the separation plug comprises an inserting part and a limiting part, the inserting part and the limiting part are respectively located on two sides of the plug fixing plate, and the inserting part is in inserting fit with the separation socket; the side of the separation plug, which is close to the insertion part, is provided with a clamping groove, the clamp spring is embedded in the clamping groove, the spring is sleeved on the separation plug, and two ends of the spring are respectively abutted against the side walls, which are oppositely arranged, of the clamp spring and the plug fixing plate.
Preferably, the main star cabin plate is provided with a first cabin penetrating hole, the separation socket extends out of the main star cabin from the inside of the main star cabin through the first cabin penetrating hole, the separation socket is provided with a first mounting hole, the main star cabin plate is provided with a matching hole, the first mounting hole and the matching hole are oppositely arranged, and the main star cabin plate is further provided with a fixing assembly.
Preferably, the fixing assembly comprises a fixing bolt and a fixing nut, the fixing bolt sequentially penetrates through the corresponding matching hole and the first mounting hole, the fixing nut is in threaded fit with one side, penetrating out of the first mounting hole, of the fixing bolt, and the fixing nut is in abutting fit with the separation socket.
Preferably, a second cabin penetrating hole is formed in the propulsion cabin plate, the inserting part of the plug assembly extends out of the propulsion cabin from the inside of the propulsion cabin through the second cabin penetrating hole, a second mounting hole is formed in the plug fixing plate, a threaded hole is formed in the propulsion cabin plate, the second mounting hole and the threaded hole are correspondingly arranged, and a fixing piece for fixedly connecting the propulsion cabin plate and the plug fixing plate is further arranged on the propulsion cabin plate.
Preferably, the fixing piece comprises a screw, the screw sequentially penetrates through the second mounting hole and the threaded hole, the screw is in threaded fit with the threaded hole, and the threaded end of the screw is screwed into the threaded hole.
Preferably, the opening of the threaded hole is located on the side wall of the propulsion compartment plate located in the propulsion compartment.
Preferably, the cable connected with the separate socket is fixedly arranged on the main board of the star deck, and the cable connected with the plug assembly is fixedly arranged on the board of the propulsion cabin.
The invention provides a docking method of a fixed star cabin signal transmission device, which comprises the following steps:
s1, the separation socket is extended out of a main star cabin from the interior of the main star cabin through a first cabin penetrating hole, the first mounting hole is aligned with a corresponding matching hole, and then the separation socket is fixedly mounted on a main star cabin plate through the matching of a fixing bolt and a fixing nut;
s2, combining and installing the separation plug, the plug fixing plate, the spring and the clamp spring into a plug assembly, then outwards extending the inserting part out of the propelling cabin from the inside of the propelling cabin through a second cabin penetrating hole, and aligning the second mounting hole with the corresponding threaded hole;
s3, enabling the screw to penetrate through the second mounting hole from bottom to top and to be screwed into the threaded hole, and stopping when the screw is screwed into the threaded hole by about one quarter of the length;
s4, lifting the main star body to move downwards until the distance between the separation socket and the plug part is about two centimeters, pushing the plug assembly to enable the plug part to be in butt joint with the separation socket, and then screwing down the screw;
and S5, hoisting the main star body to move downwards until the main star body is butted with the propulsion cabin plate, wherein at the moment, the spring on the plug assembly is in a compressed state, and the separated socket and the plug assembly are butted.
Preferably, when the separation plug, the plug fixing plate, the spring and the snap spring are assembled in S2, the plug fixing plate is firstly sleeved on the separation plug from one side where the insertion portion is located until the plug fixing plate and the limiting portion are contacted with each other, then the spring in a compressed state is sleeved on the separation plug from one side where the insertion portion is located until one axial end of the spring is contacted with the plug fixing plate, then the snap spring is embedded in the clamping groove on the separation plug, and then the plastic binding wire for fixing the spring is cut off and the spring is stretched.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the invention, the signal transmission between the main satellite and the propulsion cabin is realized through the splicing and matching of the separation socket fixedly arranged on the main satellite cabin plate and the plug assembly fixedly arranged on the propulsion cabin plate, when the main satellite and the propulsion cabin are separated, the separation socket and the plug assembly are normally separated, and the separation socket and the plug assembly are both in a fixed state, so that the resilience of the signal transmission device is reduced, and the damage of the signal transmission device to the main satellite or the propulsion cabin is favorably reduced.
2. According to the invention, the separation socket is fixed on the main star deck plate through the matching of the fixing bolt and the fixing nut, and the plug assembly is fixed on the propelling cabin deck plate through the screw, so that the detachable fixed installation of the separation socket and the plug assembly is realized, and the convenience for workers to install the separation socket and the plug assembly is improved.
3. According to the invention, through the matching of the first mounting hole and the matching of the second mounting hole and the threaded hole, a positioning effect is achieved when the socket assembly and the plug assembly are separated, and the convenience of workers for mounting the separated socket assembly and the plug assembly is further improved.
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 view of a connection structure of a separation socket and a separation plug according to the present invention;
FIG. 2 is a schematic view of the overall structure of the split jack embodying the present invention;
fig. 3 is a schematic view of the overall structure of the plug assembly embodying the present invention.
Reference numerals: 1. a main pod plate; 11. a first penetration hole; 12. a mating hole; 2. a propulsion compartment panel; 21. a second penetration hole; 22. a threaded hole; 3. a separate socket; 31. an installation part; 311. a first mounting hole; 4. a plug assembly; 41. a plug fixing plate; 411. a limiting hole; 412. a second mounting hole; 42. separating the plug; 421. a plug-in part; 422. a limiting part; 423. a card slot; 43. a spring; 44. a clamp spring; 5. a fixing assembly; 51. fixing the bolt; 52. fixing a nut; 6. and (4) screws.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will aid those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any manner. 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 invention.
As shown in fig. 1, the fixed type cockpit signal transmission device provided by the present invention includes a main cockpit plate 1 and a propulsion cockpit plate 2, wherein a separate socket 3 is fixedly installed on the main cockpit plate 1, a plug assembly 4 is installed on the propulsion cockpit plate 2, and the plug assembly 4 is in plug-in fit with the separate socket 3.
As shown in fig. 2, a first penetration hole 11 is formed in the main capsule plate 1, the separation socket 3 protrudes out of the main capsule from the main capsule through the first penetration hole 11, the separation socket 3 includes an installation portion 31, the installation portion 31 is square, the installation portion 31 is located in the main capsule, and the installation portion 31 and the side wall of the main capsule plate 1 located in the main capsule are in abutting fit. The mounting portion 31 is provided with four first mounting holes 311, and the four first mounting holes 311 are equally spaced around the central axis of the mounting portion 31 at the peripheral edge position of the mounting portion 31. The main spaceflight board 1 is provided with a matching hole 12, the matching hole 12 and the first mounting hole 311 are oppositely arranged, the main spaceflight board 1 is further provided with a fixing component 5, and the fixing component 5 and the first mounting hole 311 are oppositely arranged.
Since the composition, structure and installation manner of any one set of fixing components 5 are the same, a set of fixing components 5 will be taken as an example for explanation. The fixing component 5 includes a fixing bolt 51 and a fixing nut 52, the fixing bolt 51 sequentially penetrates through the corresponding matching hole 12 and the first mounting hole 311 from bottom to top, the fixing nut 52 is in threaded fit on one side of the fixing bolt 51 penetrating through the first mounting hole 311, and the fixing nut 52 is abutted against the mounting portion 31. The corresponding matching hole 12 and the first mounting hole 311 are matched to play a positioning role, and the fixing bolt 51 and the fixing nut 52 are matched to fix the separation socket 3 and the main cockpit board 1, so that the convenience of installing the separation socket 3 on the main cockpit board 1 by workers is improved.
When the separation socket 3 is installed, the principle that the cable at the rear end of the separation socket 3 is not twisted is taken as a principle, and the cable at the rear end of the separation socket 3 is fixed on the side wall of the main star cabin plate 1 in the main star cabin body through a self-locking binding belt.
As shown in fig. 3, the plug assembly 4 includes a plug fixing plate 41, a separation plug 42, a spring 43 and a clamp spring 44, wherein a limiting hole 411 is formed in the plug fixing plate 41, and the limiting hole 411 is a rectangular through hole. The separation plug 42 is embedded in the limiting hole 411 and is in sliding fit with the limiting hole, the separation plug 42 comprises an inserting portion 421 and a limiting portion 422, the inserting portion 421 and the limiting portion 422 are respectively located on two sides of the plug fixing plate 41, and connecting portions of the inserting portion 421 and the limiting portion 422 are rectangular rod-shaped and are matched with the limiting hole 411. A clamping groove 423 is formed in one side, close to the inserting portion 421, of the separation plug 42, the clamping spring 44 is embedded in the clamping groove 423, the spring 43 is sleeved on the separation plug 42, and two ends of the axis of the spring 43 respectively abut against the clamping spring 44 and the side wall, opposite to the plug fixing plate 41, of the plug fixing plate.
The inserting part 421 is inserted into and matched with the separation socket 3, and the stability of the inserting connection between the inserting part 421 and the separation socket 3 is improved by the matching of the snap spring 44 and the spring 43. And because the circlip 44 has certain deformability and elasticity, the normal separation of the inserting part 421 and the separation socket 3 is ensured.
A second cabin penetrating hole 21 is formed in the propulsion cabin plate 2, and the inserting part 421 of the plug assembly 4 extends out of the propulsion cabin from the inside of the propulsion cabin through the second cabin penetrating hole 21. And the plug retainer plate 41 abuts against the side wall of the propulsion compartment plate 2 inside the propulsion compartment. The plug fixing plate 41 is provided with four second mounting holes 412, and the number of the second mounting holes 412 is equal to or equal to four around the central axis of the plug fixing plate 41 at the peripheral side edge position of the plug fixing plate 41. The propulsion cabin plate 2 is provided with a threaded hole 22, an opening of the threaded hole 22 is located on a side wall of the propulsion cabin plate 2 located in the propulsion cabin, and the threaded hole 22 and the second mounting hole 412 are correspondingly arranged. The propulsion cabin plate 2 is also provided with a screw 6, and the screw 6 is arranged corresponding to the threaded hole 22.
Any screw 6 sequentially penetrates through the corresponding second mounting hole 412 and the corresponding threaded hole 22 from bottom to top, any screw 6 is in threaded fit with the corresponding threaded hole 22, and the threaded end of any screw 6 is screwed into the threaded hole 22. The plug assembly 4 is fixedly mounted on the propulsion cabin panel 2 by means of the screws 6, which improves the convenience of mounting the plug assembly 4 on the propulsion cabin panel 2.
When the plug assembly 4 is installed, a cable connected with the rear end of the plug assembly 4 is not twisted, and the cable connected with the tail part of the plug assembly 4 is fixed on the side wall of the propelling cabin plate 2 in the propelling cabin through the self-locking binding belt.
Referring to fig. 1 to 3, the docking method of a fixed star capsule signal transmission device according to the present invention includes the following steps: s1, a separation socket 3 extends out of a main star cabin from the main star cabin through a first cabin penetrating hole 11, a first mounting hole 311 is aligned with a corresponding matching hole 12, then four fixing bolts 51 sequentially penetrate through the matching hole 12 and the first mounting hole 311 from bottom to top, and the separation socket 3 is fixedly connected with a main star cabin plate 1 through the matching of four fixing nuts 52 and the four fixing bolts 51;
s2, the separation plug 42, the plug fixing plate 41, the spring 43 and the clamp spring 44 are assembled and installed to form a plug assembly 4, the plug fixing plate 41 is sleeved on the separation plug 42 from one side where the inserting portion 421 is located until the plug fixing plate 41 is in contact with the limiting portion 422, then the spring 43 in a compression state is sleeved on the separation plug 42 from one side where the inserting portion 421 is located until one axial end of the spring 43 is in contact with the plug fixing plate 41, then the clamp spring 44 is embedded in the clamping groove 423 on the separation plug 42, then the plastic binding wire for fixing the spring 43 is cut off, the spring 43 is stretched, the inserting portion 421 extends out of the propulsion cabin from the propulsion cabin through the second cabin penetrating hole 21, and any one second installation hole 412 is aligned with the corresponding threaded hole 22;
s3, all four screws 6 penetrate through the corresponding second mounting holes 412 from bottom to top and are screwed into the threaded holes 22, and the screws 6 are stopped after being screwed into the threaded holes 22 by about one quarter of the length;
s4, lifting the main star body to move downwards until the distance between the separation socket 3 and the plug part 421 is about two centimeters, then pushing the plug assembly 4 to enable the plug part 421 to be in butt joint with the separation socket 3, and then screwing four screws 6 respectively;
and S5, hoisting the main star body to move downwards until the main star body is butted with the propulsion cabin plate, wherein at the moment, the spring 43 on the plug assembly 4 is in a compressed state, and the separated socket 3 and the plug assembly 4 are butted.
The working principle is as follows:
in work, a worker fixedly installs the separation socket 3 on the main satellite cabin plate 1, installs the plug assembly 4 on the propulsion cabin plate 2 and transmits signals between the main satellite and the propulsion cabin in a hard connection mode of the separation socket 3 and the separation plug 42; after the main satellite and the propulsion cabin are separated in an orbit, the separation socket 3 and the separation plug 42 are naturally separated, and the separation socket 3 is fixed on the main satellite cabin plate 1 as the separation plug 42 is fixedly arranged on the propulsion cabin plate 2; the cable connector overcomes the defect that one section of the cable at the plug section is positioned outside the cabin and is in an unconstrained state after the previous separation, reduces the resilience of the plug assembly, is favorable for reducing the damage of a signal transmission device to a main satellite or a propulsion cabin, and has the advantages of simple structure, high working reliability and strong applicability.
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 (9)
1. A fixed star cabin signal transmission device is characterized by comprising a main star cabin plate (1) and a propulsion cabin plate (2), wherein a separation socket (3) is fixedly mounted on the main star cabin plate (1), and a plug assembly (4) is fixedly mounted on the propulsion cabin plate (2);
the plug assembly (4) comprises a plug fixing plate (41), a separating plug (42), a spring (43) and a clamp spring (44), a limiting hole (411) is formed in the plug fixing plate (41), the separating plug (42) is embedded in the limiting hole (411) and is in sliding fit with the limiting hole, the separating plug (42) comprises a plug-in part (421) and a limiting part (422), the plug-in part (421) and the limiting part (422) are located on two sides of the plug fixing plate (41) respectively, and the plug-in part (421) is in plug-in fit with the separating socket (3);
a clamping groove (423) is formed in one side, close to the plugging portion (421), of the separation plug (42), the clamping spring (44) is embedded in the clamping groove (423), the spring (43) is sleeved on the separation plug (42), and two ends of the spring (43) are respectively abutted against side walls, opposite to the clamping spring (44) and the plug fixing plate (41).
2. The fixed type spaceflight signal transmission device as claimed in claim 1, wherein the main spaceflight board (1) is provided with a first cabin penetrating hole (11), the separation socket (3) extends out of the main spaceflight from the main spaceflight through the first cabin penetrating hole (11), the separation socket (3) is provided with a first mounting hole (311), the main spaceflight board (1) is provided with a matching hole (12), the first mounting hole (311) and the matching hole (12) are oppositely arranged, and the main spaceflight board (1) is further provided with a fixing component (5).
3. The fixed star capsule signal transmission device according to claim 2, wherein the fixing assembly (5) comprises a fixing bolt (51) and a fixing nut (52), the fixing bolt (51) sequentially penetrates through the corresponding matching hole (12) and the first mounting hole (311), the fixing nut (52) is in threaded fit with one side of the fixing bolt (51) penetrating through the first mounting hole (311), and the fixing nut (52) is in abutting fit with the separation socket (3).
4. The fixed type star capsule signal transmission device according to claim 1, wherein a second capsule penetration hole (21) is formed in the propulsion capsule plate (2), the insertion portion (421) of the plug assembly (4) extends out of the propulsion capsule from the propulsion capsule through the second capsule penetration hole (21), a second mounting hole (412) is formed in the plug fixing plate (41), a threaded hole (22) is formed in the propulsion capsule plate (2), the second mounting hole (412) and the threaded hole (22) are correspondingly arranged, and a fixing member for fixedly connecting the propulsion capsule plate (2) and the plug fixing plate (41) is further arranged on the propulsion capsule plate (2).
5. The fixed star capsule signal transmission device according to claim 4, wherein the fixing member comprises a screw (6), the screw (6) is sequentially inserted into the second mounting hole (412) and the threaded hole (22), the screw (6) is in threaded fit with the threaded hole (22), and the threaded end of the screw (6) is screwed into the threaded hole (22).
6. A fixed star capsule signal transmission device as claimed in claim 4, characterised in that the opening of said threaded hole (22) is located on the side wall of the propulsion capsule plate (2) located inside the propulsion capsule.
7. A fixed star deck signal transmission device as claimed in claim 1, wherein the cables to which the said separate sockets (3) are connected are fixedly arranged on the main star deck (1) and the cables to which the said plug assemblies (4) are connected are fixedly arranged on the propulsion star deck (2).
8. A docking method for a fixed satellite capsule signal transmission device is characterized by comprising the following steps:
s1, a separation socket (3) is protruded out of a main star cabin from the main star cabin through a first cabin penetrating hole (11), a first mounting hole (311) is aligned with a corresponding matching hole (12), and then the separation socket (3) is fixedly mounted on a main star cabin plate (1) through the matching of a fixing bolt (51) and a fixing nut (52);
s2, combining and installing a separation plug (42), a plug fixing plate (41), a spring (43) and a clamp spring (44) into a plug assembly (4), extending the insertion part (421) out of the propulsion cabin from the propulsion cabin through a second cabin penetrating hole (21), and aligning the second installation hole (412) with a corresponding threaded hole (22);
s3, enabling the screw (6) to penetrate through the second mounting hole (412) from bottom to top and to be screwed into the threaded hole (22), and stopping when the screw (6) is screwed into the threaded hole (22) by about one quarter of the length;
s4, lifting the main star body to move downwards until the distance between the separation socket (3) and the plug part (421) is about two centimeters, then pushing the plug assembly (4) and enabling the plug part (421) to be in butt joint with the separation socket (3), and then screwing the screw (6);
and S5, hoisting the main star body to move downwards until the main star body is butted with the pushing cabin plate, wherein at the moment, a spring (43) on the plug assembly (4) is in a compressed state, and the separated socket (3) and the plug assembly (4) are butted.
9. The docking method for the fixed type star capsule signal transmission device according to claim 8, wherein in S2, when the separation plug (42), the plug fixing plate (41), the spring (43) and the snap spring (44) are assembled, the plug fixing plate (41) is firstly sleeved on the separation plug (42) from the side where the insertion part (421) is located until the plug fixing plate (41) and the limiting part (422) are contacted with each other, then the spring (43) in a compressed state is sleeved on the separation plug (42) from the side where the insertion part (421) is located until the axial end of the spring (43) is contacted with the plug fixing plate (41), then the snap spring (44) is embedded in the clamping groove (423) on the separation plug (42), and then the plastic binding wire for fixing the spring (43) is cut off and the spring (43) is stretched.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011605540.4A CN112758360B (en) | 2020-12-29 | 2020-12-29 | Fixed star cabin signal transmission device and butt joint method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011605540.4A CN112758360B (en) | 2020-12-29 | 2020-12-29 | Fixed star cabin signal transmission device and butt joint method |
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| Publication Number | Publication Date |
|---|---|
| CN112758360A CN112758360A (en) | 2021-05-07 |
| CN112758360B true CN112758360B (en) | 2022-12-13 |
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| CN202011605540.4A Active CN112758360B (en) | 2020-12-29 | 2020-12-29 | Fixed star cabin signal transmission device and butt joint method |
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| US10396493B2 (en) * | 2017-09-06 | 2019-08-27 | Hirel Connectors, Inc. | Electrical connector with pull release |
| DE102017218876B4 (en) * | 2017-10-23 | 2021-04-01 | Phoenix Contact Gmbh & Co. Kg | Devices for connecting and disconnecting an electrical connection |
| KR102084710B1 (en) * | 2018-06-01 | 2020-03-04 | 조선대학교산학협력단 | Separation device for deployment structure of cubesat using pogo-pin |
| CN109713513B (en) * | 2018-11-27 | 2023-10-17 | 杭州航天电子技术有限公司 | Corrosion-resistant sealing device and method for underwater cabin penetrating electrical connection |
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2020
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