CN113783021A - Redundancy control device for separating electric connector for deep space exploration and spacecraft - Google Patents
Redundancy control device for separating electric connector for deep space exploration and spacecraft Download PDFInfo
- Publication number
- CN113783021A CN113783021A CN202111034391.5A CN202111034391A CN113783021A CN 113783021 A CN113783021 A CN 113783021A CN 202111034391 A CN202111034391 A CN 202111034391A CN 113783021 A CN113783021 A CN 113783021A
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- China
- Prior art keywords
- electric connector
- cover plate
- separation
- bracket
- deep space
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- 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
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- 238000000926 separation method Methods 0.000 claims abstract description 68
- 238000010030 laminating Methods 0.000 abstract description 2
- 230000001681 protective effect Effects 0.000 description 7
- 239000000463 material Substances 0.000 description 6
- 238000001514 detection method Methods 0.000 description 5
- 230000008901 benefit Effects 0.000 description 3
- 238000013523 data management Methods 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000011897 real-time detection Methods 0.000 description 1
- 238000005493 welding type Methods 0.000 description 1
Images
Classifications
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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
-
- 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
- H01R13/46—Bases; Cases
- H01R13/52—Dustproof, splashproof, drip-proof, waterproof, or flameproof cases
- H01R13/5213—Covers
-
- 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
- H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
- H01R13/621—Bolt, set screw or screw clamp
- H01R13/6215—Bolt, set screw or screw clamp using one or more bolts
Landscapes
- Connector Housings Or Holding Contact Members (AREA)
Abstract
The invention provides a device for controlling the redundancy of a separated electric connector for deep space exploration and a spacecraft, comprising: the device comprises a bracket, a separation electric connector, a torsion spring and a cover plate; one side of the bracket is connected with the separation electric connector, and the cover plate is arranged at one side of the bracket, which is connected with the separation electric connector; one side of the cover plate is rotatably connected with the bracket, and the torsion spring is arranged at the position where the cover plate is connected with the bracket; when the bracket is connected with the separating electric connector, the cover plate and the bracket form an included angle and are in an open state; when the support with when separating the electric connector, the apron passes through the torsional spring laminating the support side is and be the closed condition. The device can be freely closed, and controls the redundancy in a mode of effectively isolating the separation socket from other irrelevant parts on the satellite, thereby fully considering the use characteristics of the separation electric connector for deep space exploration and the practical situation of being installed outside a spacecraft.
Description
Technical Field
The invention relates to a deep space excess control device, in particular to a separated electric connector excess control device for deep space exploration and a spacecraft.
Background
The deep space exploration environment is relatively severe, the control on redundancy is more strict, the spacecraft product has the characteristics of small fault tolerance rate and low repairability rate, and high reliability and high safety are required to be achieved on the premise of ensuring the functions of the spacecraft product. At present, the socket part of the separation electric connector for the spacecraft is mostly arranged and used in the spacecraft, and is not directly exposed in the space environment, so that the redundant objects are prevented from entering the connector. The whole separated electric connector for deep space detection is positioned outside the spacecraft, and in order to ensure that the separated electric connector is not directly exposed in a space environment and prevent redundant materials from entering a connector, the installation structure of the separated electric connector needs to be redesigned.
Patent document CN110816902B provides a system, a real-time detection method and a medium for detecting the redundant material in a satellite structure platform hole, wherein the system includes an image acquisition module, an online module, a communication module, a redundant material detection module and a data management module; the communication module is respectively communicated with the image acquisition module and the online module in real time and can send a set instruction to the data management module; the image data acquired by the image acquisition module can be sequentially output by the redundancy detection module and the data management module to obtain a redundancy detection result.
Patent document CN203114850U relates to an explosion bolt protection device and a cabin structure. An explosion bolt guard comprising: the protective device comprises a protective cover, a protective plate, a base, a steel wire threaded sleeve and the like, wherein the base is in threaded connection with the protective plate, and the protective plate is in welded connection with the protective cover. The protection capability of the cabin body excess is improved by adopting a protection cover, a steel wire thread sleeve and the like.
Patent document CN212114111U discloses an electric connector with protective structure, including the electric connector body, the outside fixed mounting of electric connector body has the cover shell, two recesses have been seted up in the cover shell outside, and the block is connected with first lagging and second lagging in two recesses respectively, threaded hole has all been seted up to four positive edges of first lagging and four positive edges of second lagging, and there is the connecting rod through threaded hole threaded connection, the positive one side fixedly connected with pole setting of first lagging, one side of pole setting articulates there is the cap, the cavity has been seted up to the inside of cap, the fixed buckle that is equipped with in bottom of cap one end prevents through the electric connector outside fixed mounting cover shell that the electric connector from receiving the damage.
Patent document CN110932037B relates to a high vacuum separation electric connector for deep space exploration, which belongs to the technical field of aerospace electric connectors, and adopts a structural mode that a coil is wound on a socket, and a collision column triggers and pushes a plug pull rod under an electric separation condition to realize separation; parts such as a shell, a cable cover, a contact element and the like made of light materials are adopted to complete assembly; a contact element with lower contact resistance and a separation spring with higher separation power are adopted to improve the ratio coefficient of the separation power to the separation resistance; the compression joint type contact is adopted, so that the influence of low temperature on the welding type contact is avoided; the special high-vacuum lubricating grease is adopted to reduce the friction resistance.
In the prior art, the detection mode or the fixed protection cover adding mode is adopted to isolate the redundancy, the structure is complex, the cost is high, or the redundancy cannot be automatically isolated after separation.
Disclosure of Invention
In view of the defects in the prior art, the invention aims to provide a redundancy control device of a separated electric connector for deep space exploration and a spacecraft.
According to the invention, the device for controlling the redundancy of the separated electric connector for deep space exploration comprises: the device comprises a bracket, a separation electric connector, a torsion spring and a cover plate;
one side of the bracket is connected with the separation electric connector, and the cover plate is arranged at one side of the bracket, which is connected with the separation electric connector;
one side of the cover plate is rotatably connected with the bracket, and the torsion spring is arranged at the position where the cover plate is connected with the bracket;
when the bracket is connected with the separating electric connector, the cover plate and the bracket form an included angle and are in an open state;
when the support with when separating the electric connector, the apron passes through the torsional spring laminating the support side is and be the closed condition.
Preferably, a groove is formed in one side, connected with the separation electric connector, of the support, and a separation socket is installed in the groove.
Preferably, a separation plug is installed on one side of the separation electric connector, and a cable bundle is installed on the other side of the separation electric connector;
when the separation electric connector is connected with the bracket, the separation plug is connected with the separation socket.
Preferably, when the cover plate is in an open state, the cover plate leans against the separation electric connector through the torsion spring and does not contact the cable bundle;
when the cover plate is in a closed state, the cover plate and the groove form a closed cavity.
Preferably, the cover plate is connected with one side of the bracket through a mounting hinge and is connected with the bracket through the hinge.
Preferably, the hinge is provided in plurality, and a shaft is provided between a plurality of the hinges.
Preferably, the torsion spring is sleeved on the shaft.
Preferably, the spacecraft adopts the separated electric connector redundancy control device for deep space exploration.
Preferably, the torsion spring adopts a parallel double-torsion spring, and the single-side effective number of turns of the parallel double-torsion spring is 8.
Preferably, the torsion of the torsion spring is 0-150 degrees.
Preferably, a pin and a socket are also mounted in the groove.
Compared with the prior art, the invention has the following beneficial effects:
1. the device can be freely closed, and the redundancy is controlled in a mode of effectively isolating the separation socket from other irrelevant parts on the satellite, so that the use characteristics of the separation electric connector for deep space exploration and the actual situation of being installed outside a spacecraft are fully considered;
2. the device has a simple structure, is easy to realize, and improves the overall safety and reliability of the spacecraft;
3. the device is suitable for the spacecraft which needs to use the separated electric connector, and particularly has greater benefit for the spacecraft which is integrally positioned outside the cabin.
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 partial cross-sectional view of a redundant control apparatus for a discrete electrical connector;
FIG. 2 is a partial sectional view of the redundant control device of the separated electrical connector;
FIG. 3 is a schematic perspective view of the electrical connector before separation;
FIG. 4 is a schematic perspective view of the separated electrical connector;
shown in the figure:
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.
Example 1
As shown in fig. 3 and 4, a redundant control device for a separated electrical connector for deep space exploration, which can be used in a spacecraft such as a satellite, includes: the electric connector separation device comprises a support 1, a separation electric connector 4, a torsion spring 5 and a cover plate 6, wherein one side of the support 1 is connected with the separation electric connector 4, the cover plate 6 is installed on one side of the support 1, which is connected with the separation electric connector 4, one side of the cover plate 6 is rotatably connected with the support 1, and the torsion spring 5 is installed at the position of the cover plate 6, which is connected with the support 1; a groove is formed in one side, connected with the separating electric connector 4, of the support 1, a separating socket is installed in the groove, a separating plug is installed on one side of the separating electric connector 4, a cable harness is installed on the other side of the separating electric connector 4, and when the separating electric connector 4 is connected with the support 1, the separating plug is connected with the separating socket.
When the bracket 1 is connected with the separation electric connector 4, the cover plate 6 and the bracket 1 form an included angle and are in an open state; when the bracket 1 is separated from the separation electric connector 4, the cover plate 6 is attached to the side surface of the bracket 1 through the torsion spring 5 and is in a closed state. When the cover plate 6 is in the open state, the cover plate 6 leans against the separation electric connector 4 through the torsion spring 5 and does not contact the cable harness, and when the cover plate 6 is in the closed state, the cover plate 6 and the groove form a closed chamber.
As shown in fig. 1 and 2, a hinge 2 is installed on one side of a cover plate 6 connecting support 1 and is connected with the support 1 through the hinge 2, a plurality of hinges 2 are arranged, a shaft 3 is arranged between the hinges 2, and a torsion spring 5 is sleeved on the shaft 3.
Example 2
Example 2 is a preferred example of example 1.
As shown in fig. 1 and 2, an automatic closing cover plate 6 is designed for a separation electric connector 4 which is directly exposed outside after separation of a satellite and an arrow, after the satellite and the arrow are separated, the cover plate 6 is automatically closed through a shaft 3 and a hinge 2 through the force of a torsion spring 5 to form a relatively closed space so as to protect a separation socket of the separation electric connector 4 after separation from direct exposure and ensure that pins or jacks of the separation electric connector 4 are effectively isolated from other irrelevant parts on the satellite so as to control the surplus objects, and the device is suitable for a spacecraft which needs to use the separation electric connector 4, and particularly has greater benefit for the spacecraft which is arranged outside the spacecraft integrally with the separation electric connector 4. The torsion spring 5 adopts a parallel double-torsion spring, and the number of effective turns on a single side is 8. With the design of two hinges 2, a torsion spring 5 is mounted in between the two hinges 2.
As shown in fig. 3 and 4, in the case where the entire electrical connector 4 is located outside the spacecraft, the mounting panel is designed to avoid the disadvantage that the electrical connector is directly exposed and the entry of excess material is not possible. If the original cover plate 6 is expanded to form a relatively closed cover plate box-shaped space, considering that the cable bundle on the electric connector 4 is separated before separation, if the cover plate 6 is too long, the cable bundle can be pressed, and the cable bundle is damaged, so that the cover plate 6 is preferably not contacted with the cable bundle, and the cover plate 6 and the bracket 1 form a closed space after being closed. Considering that one end of the separation electric connector 4 is provided with a cable harness plug, the cover plate 6 needs to be turned by 90 degrees to facilitate the plugging and unplugging operation of the separation electric connector 4, the torsion degree allowed by the designed torsion spring 5 is 0-150 degrees, and before the star arrow is not separated, the separation electric connector 4 and the cable harness can realize the plugging and unplugging of the separation electric connector 4 separation plug and the separation socket through the turning cover plate 6. After the star and arrow are separated, the separation plug is separated from the separation socket, the cover plate 6 is automatically closed by the force of the torsion spring 5, so that the separated separation socket is protected from being directly exposed in a space environment, and redundant materials are prevented from entering the separation electric connector 4.
The device is characterized in that a closable cover plate 6 is designed for a separating electric connector 4 which can be directly exposed after the device and the arrow are separated, so that high safety and reliability of the device are guaranteed; due to the adoption of the technical scheme, the whole separation electric connector 4 can be ensured to be positioned outside the spacecraft, and the separation electric connector has the characteristics of simplifying product design and saving spacecraft resources.
In conclusion, the device for controlling the surplus objects of the separating electric connector 4 for deep space exploration fully considers the use characteristics of the separating electric connector 4 for deep space exploration, and the cover plate 6 capable of being automatically closed is independently designed for the situation outside the spacecraft, so that the concept is innovative, the method is simple, and the overall safety and reliability of the spacecraft are improved.
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 (8)
1. A split electrical connector redundancy control apparatus for deep space exploration, comprising: the device comprises a bracket (1), a separation electric connector (4), a torsion spring (5) and a cover plate (6);
one side of the bracket (1) is connected with the separating electric connector (4), and the cover plate (6) is installed on one side of the bracket (1) connected with the separating electric connector (4);
one side of the cover plate (6) is rotatably connected with the bracket (1), and the torsion spring (5) is arranged at the position where the cover plate (6) is connected with the bracket (1);
when the bracket (1) is connected with the separating electric connector (4), the cover plate (6) and the bracket (1) form an included angle and are in an open state;
when the support (1) is separated from the separation electric connector (4), the cover plate (6) is attached to the side surface of the support (1) through the torsion spring (5) and is in a closed state.
2. The electrical connector redundancy control apparatus for deep space exploration according to claim 1, wherein: the support (1) is connected with one side of the separation electric connector (4) and is provided with a groove, and a separation socket is installed in the groove.
3. The electrical connector redundancy control apparatus for deep space exploration according to claim 2, wherein: a separation plug is arranged on one side of the separation electric connector (4), and a cable harness is arranged on the other side of the separation electric connector (4);
when the separation electric connector (4) is connected with the bracket (1), the separation plug is connected with the separation socket.
4. The electrical connector redundancy control apparatus for deep space exploration according to claim 3, wherein: when the cover plate (6) is in an open state, the cover plate (6) leans against the separation electric connector (4) through the torsion spring (5) and does not contact the cable harness;
when the cover plate (6) is in a closed state, the cover plate (6) and the groove form a closed chamber.
5. The electrical connector redundancy control apparatus for deep space exploration according to claim 1, wherein: the cover plate (6) is connected with a hinge (2) arranged on one side of the support (1) and is connected with the support (1) through the hinge (2).
6. The electrical connector redundancy control apparatus for deep space exploration according to claim 5, wherein: the hinge (2) is provided with a plurality of hinges, and a shaft (3) is arranged between the plurality of hinges (2).
7. The electrical connector redundancy control apparatus for deep space exploration according to claim 6, wherein: the torsion spring (5) is sleeved on the shaft (3).
8. A spacecraft, characterized by: the spacecraft employs the separated electrical connector redundancy control device for deep space exploration according to any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111034391.5A CN113783021A (en) | 2021-09-03 | 2021-09-03 | Redundancy control device for separating electric connector for deep space exploration and spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111034391.5A CN113783021A (en) | 2021-09-03 | 2021-09-03 | Redundancy control device for separating electric connector for deep space exploration and spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113783021A true CN113783021A (en) | 2021-12-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111034391.5A Pending CN113783021A (en) | 2021-09-03 | 2021-09-03 | Redundancy control device for separating electric connector for deep space exploration and spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113783021A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4214031A1 (en) * | 1992-04-29 | 1993-11-04 | Berker Geb | Hinged joint for flap covering electrical socket outlet - uses leaf spring on spacer for tensioning and for ensuring positive closure and holding flap upright in open position |
| EP1732175A2 (en) * | 2005-06-08 | 2006-12-13 | Lapp Engineering & Co | Angular connector housing with cover |
| CN107230882A (en) * | 2017-06-08 | 2017-10-03 | 郑州航天电子技术有限公司 | A kind of connector ends protector |
| CN108598770A (en) * | 2018-04-28 | 2018-09-28 | 北京机械设备研究所 | A kind of electric connector and blindmate method of reliable blindmate |
| CN209880939U (en) * | 2019-04-19 | 2019-12-31 | 江苏富浩电子科技有限公司 | Rain-proof device that drenches for connector |
| CN209928067U (en) * | 2019-05-24 | 2020-01-10 | 苏州天孚光通信股份有限公司 | LC flip structure adapter |
| CN111370908A (en) * | 2020-03-12 | 2020-07-03 | 贵州航天电器股份有限公司 | A kind of interface unit |
| CN212587786U (en) * | 2020-05-29 | 2021-02-23 | 东莞市勤本电子科技有限公司 | Contact pin type electric connector with dustproof function |
-
2021
- 2021-09-03 CN CN202111034391.5A patent/CN113783021A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4214031A1 (en) * | 1992-04-29 | 1993-11-04 | Berker Geb | Hinged joint for flap covering electrical socket outlet - uses leaf spring on spacer for tensioning and for ensuring positive closure and holding flap upright in open position |
| EP1732175A2 (en) * | 2005-06-08 | 2006-12-13 | Lapp Engineering & Co | Angular connector housing with cover |
| CN107230882A (en) * | 2017-06-08 | 2017-10-03 | 郑州航天电子技术有限公司 | A kind of connector ends protector |
| CN108598770A (en) * | 2018-04-28 | 2018-09-28 | 北京机械设备研究所 | A kind of electric connector and blindmate method of reliable blindmate |
| CN209880939U (en) * | 2019-04-19 | 2019-12-31 | 江苏富浩电子科技有限公司 | Rain-proof device that drenches for connector |
| CN209928067U (en) * | 2019-05-24 | 2020-01-10 | 苏州天孚光通信股份有限公司 | LC flip structure adapter |
| CN111370908A (en) * | 2020-03-12 | 2020-07-03 | 贵州航天电器股份有限公司 | A kind of interface unit |
| CN212587786U (en) * | 2020-05-29 | 2021-02-23 | 东莞市勤本电子科技有限公司 | Contact pin type electric connector with dustproof function |
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