CN113745906A - Box elastic electric connector axial falling and separating structure - Google Patents
Box elastic electric connector axial falling and separating structure Download PDFInfo
- Publication number
- CN113745906A CN113745906A CN202110976870.2A CN202110976870A CN113745906A CN 113745906 A CN113745906 A CN 113745906A CN 202110976870 A CN202110976870 A CN 202110976870A CN 113745906 A CN113745906 A CN 113745906A
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- Prior art keywords
- missile
- separable
- cable cover
- box
- electrical connector
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- 230000005540 biological transmission Effects 0.000 claims abstract description 4
- 238000000926 separation method Methods 0.000 claims description 41
- 238000009434 installation Methods 0.000 claims description 6
- 230000009970 fire resistant effect Effects 0.000 claims description 2
- 230000007246 mechanism Effects 0.000 abstract description 5
- 230000010354 integration Effects 0.000 abstract description 4
- 230000000670 limiting effect Effects 0.000 description 3
- 230000008054 signal transmission Effects 0.000 description 3
- 230000000903 blocking effect Effects 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
- 230000008569 process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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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
- H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
- H01R13/629—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances
- H01R13/633—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for disengagement only
Abstract
The invention provides an axial falling and separating structure of a box missile electric connector, which comprises a box body, a missile, a separable electric connector, a stop column and a cable cover. The cable cover is installed on the missile, one end of the separable electric connector is installed in the cable cover, and the other end of the separable electric connector penetrates through the cable cover to be connected with the stop pillar; the retaining column is arranged on the box body; the separable electrical connector has a connected state and a separated state; when the missile is statically placed in the box body, the separable electric connector is in a connected state and allows electric signals to be transmitted; when the missile launches, the separable electrical connector is in a separated state and does not allow transmission of electrical signals. Compared with a traditional complex electric connector falling mechanism, the invention reduces the section area of the launching box and improves the integration level of a weapon system.
Description
Technical Field
The invention belongs to the technical field of missile launching, and particularly relates to an axial falling-off separation structure of a box missile electric connector.
Background
The shedding electric connector is mainly used for electric line connection and automatic separation among various missile stages (between a first stage and a second stage) and between a missile, ground equipment and an aircraft hanging rack, is an important part of a missile electric system, ensures reliable connection before the missile is launched, can be separated quickly and reliably in the launching process, and is a key of a shedding cable connection scheme. In order to realize reliable signal transmission before missile launching and reliable unlocking during launching, an electric connector dropping mechanism is arranged on the side surface of the existing domestic and foreign launching box, so that the section of the launching box is inevitably larger, and the improvement of the weapon system integration level is not facilitated.
Patent document CN207398534U discloses a vertical separation type electrical connector, which includes a plug, a socket for inserting the plug, and a slider, wherein a socket shell of the socket is provided with a large guide hole and a small guide hole, the socket shell is rectangular, four corners of the periphery of the socket shell are provided with threaded holes, and the periphery of the front surface of the socket shell is provided with a slope surface; the plug shell of the plug is provided with a large guide post and a small guide post, and the periphery of the plug shell is provided with a first mounting hole; the slider is triangle-shaped, and slider inside is provided with the second mounting hole. The electric connector is still arranged on the side face of the missile body, so that the problem that the section of the launching box is larger is still not solved.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an axial falling-off separation structure of a box spring electric connector.
The invention provides an axial falling-off separation structure of a box missile electric connector, which comprises a box body, a missile, a separable electric connector, a stop column and a cable cover.
The cable cover is installed on the missile, one end of the separable electric connector is installed in the cable cover, and the other end of the separable electric connector penetrates through the cable cover to be connected with the stop pillar; the retaining column is arranged on the box body;
the separable electrical connector has a connected state and a separated state;
when the missile is statically placed in the box body, the separable electric connector is in a connected state and allows electric signals to be transmitted;
when the missile launches, the separable electrical connector is in a separated state and does not allow transmission of electrical signals.
Preferably, the separable electrical connector comprises a separation socket and a separation plug;
the separation socket is arranged in the cable cover, and the separation plug is connected with the blocking column.
Preferably, the separable electrical connector is detachably connected to the separable plug when the separable electrical connector is in the connected state;
the separable electrical connector is configured to be separated from the separable plug when the separable electrical connector is in a separated state.
Preferably, the cable cover is installed on the circumference of the missile and located at the tail of the missile, and the separation socket and the separation plug are both arranged along the axial direction of the missile.
Preferably, the catch matches the installation position of the cable cover.
Preferably, the cable cover is installed at the circumferential bottom end of the tail of the missile, and the stop pillar is located on the inner bottom surface of the tail of the box body.
Preferably, the installation position of the cable cover and the retaining column is any one of the following positions:
the cable cover is arranged at the circumferential top end of the tail part of the guided missile, and the stop pillar is positioned on the inner top surface of the tail part of the box body;
the cable cover is arranged on the circumferential side face of the tail of the guided missile, and the stop pillar is located on the inner side face of the tail of the box body.
Preferably, one end of the separation plug is provided with a pull ring structure, and the pull ring structure is sleeved on the retaining column.
Preferably, the cable cover and the separable electrical connector are both made of a fire resistant material.
Preferably, the separation socket is close to one end of the tail end of the missile, and does not exceed the tail end of the missile in the axial direction of the missile.
Compared with the prior art, the invention has the following beneficial effects:
1. compared with a traditional complex electric connector falling mechanism, the invention reduces the section area of the launching box and improves the integration level of a weapon system.
2. The electric connector adopted by the invention can be repeatedly used, and the cost of the missile system can be reduced.
3. The design of axial arrangement of the invention avoids the problem that the flight resistance of the missile is obviously increased by using the traditional electric connector falling mechanism as a large-scale projection of the missile, and the flight performance of the missile is influenced.
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 side view of the electrical separable connector of the present invention in a connected state;
FIG. 2 is a schematic top view of the electrical separable connector of the present invention in the connected state;
FIG. 3 is a schematic front view of the electrical separable connector of the present invention in the connected state;
FIG. 4 is a schematic structural diagram of the electrical separable connector of the present invention in the connected state;
fig. 5 is a schematic side view of the separable electrical connector of the present invention in a separated state;
fig. 6 is a schematic top view of the separable electrical connector of the present invention in a separated state;
fig. 7 is a schematic structural view of the detachable electrical connector of the present invention in a detached state.
The figures show that:
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.
The invention provides an axial falling-off separation structure of a box missile electric connector, which comprises a box body 1, a missile 2, a separable electric connector, a stop column 5 and a cable cover 6.
The cable cover 6 is installed on the missile 2, and preferably, the cable cover 6 is installed on the circumference of the missile 2 and is positioned at the tail part of the missile 2. One end of the separable electric connector is arranged in the cable cover 6, and the other end of the separable electric connector penetrates through the cable cover 6 to be connected with the retaining column 5; the bumping post 5 is installed on the box body 1.
The separable electrical connector has a connected state and a separated state; when the missile 2 is statically placed in the box body 1, the missile 2 is supported by the box body 1, and the separable electric connector is in a connected state and allows electric signals to be transmitted; when the missile 2 is launched, the separable electrical connectors are in a separated state and do not allow transmission of electrical signals. In a preferred embodiment, the separable electrical connector is a 48-core rectangular separable connector of the JF22 series, medium-air electro-optical technologies, inc.
The separable electric connector comprises a separation socket 3 and a separation plug 4, wherein the separation socket 3 is installed in the cable cover 6, and the separation socket 3 and the separation plug 4 are both arranged along the axial direction of the missile 2.
The disconnection plug 4 is connected to the catch 5. In a preferred embodiment, as shown in fig. 1 to 7, the separation plug 4 has a pull ring at one end, the pull ring has a long kidney-shaped hole, and the pull ring is sleeved on the catch 5.
As shown in fig. 1 to 4, when the separable electrical connector is in a connected state, the separation receptacle 3 is detachably connected to the separation plug 4; as shown in fig. 5 to 7, when the separable electrical connector is in the separated state, the separation receptacle 3 is separated from the separation plug 4.
The stop column 5 is matched with the installation position of the cable cover 6.
In a preferred embodiment, as shown in fig. 1 to 7, the cable cover 6 is mounted at the circumferential bottom end of the tail part of the missile 2, and the stop pillar 5 is positioned at the inner bottom surface of the tail part of the missile body.
In another preferred example, the installation position of the cable cover 6 and the catch 5 may be any one of the following:
the cable cover 6 is arranged at the circumferential top end of the tail part of the missile 2, and the stop pillar 5 is positioned on the inner top surface of the tail part of the box body;
the cable cover 6 is arranged on the circumferential side face of the tail of the missile 2, and the stop pillar 5 is positioned on the inner side face of the tail of the box body.
In order to avoid the fire from the tail end of the missile during the flight of the missile, the cable cover 6 and the separable electrical connector are made of fireproof materials, and as shown in fig. 5 and 7, the end of the separable socket 3 close to the tail end of the missile 2 does not exceed the tail end of the missile 2 in the axial direction of the missile 2.
The working principle of the invention is as follows:
when the missile 2 is placed in the box body 1 in a static mode, the separation plug 4 and the separation socket 3 are inserted in place, the middle of the pull ring long waist-shaped hole in the separation plug 4 is sleeved on the blocking column 5, and the separation socket 3 and the separation plug 4 are connected to achieve reliable signal transmission before missile launching.
In the launching process of the missile 2, the separation plug 4 is mechanically separated from the separation socket 3 under the limiting effect of the stop column 5 on the pull ring long waist-shaped hole of the separation plug 4, so that reliable unlocking is realized when the missile 2 is launched.
After the missile 2 is launched, the separation plug 4 sleeved on the stop pillar 5 can be repeatedly used for many times, so that the cost of the missile system is reduced.
In addition, the invention avoids the adoption of a traditional complex electric connector falling-off mechanism, improves the reliability of signal transmission before missile launching and unlocking during missile launching, reduces the section of the launching box and improves the integration level of a weapon system.
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. The utility model provides a case bullet electric connector separation structure that drops axially which characterized in that includes box (1), guided missile (2), separable electric connector, bumping post (5) and cable cover (6).
The cable cover (6) is installed on the missile (2), one end of the separable electric connector is installed in the cable cover (6), and the other end of the separable electric connector penetrates through the cable cover (6) to be connected with the stop column (5); the retaining column (5) is arranged on the box body (1);
the separable electrical connector has a connected state and a separated state;
when the missile (2) is statically placed in the box body (1), the separable electric connector is in a connected state and allows electric signals to be transmitted;
when the missile (2) launches, the separable electrical connectors are in a separated state and do not allow transmission of electrical signals.
2. The box spring electrical connector axial disengagement structure according to claim 1, wherein the separable electrical connector comprises a separation socket (3) and a separation plug (4);
the separation socket (3) is arranged in the cable cover (6), and the separation plug (4) is connected with the stop column (5).
3. The box spring electrical connector axial disengagement structure according to claim 2, wherein the disengagement socket (3) is detachably connected to the disengagement plug (4) when the electrical separable connector is in the connected state;
when the separable electrical connector is in a separated state, the separation socket (3) is separated from the separation plug (4).
4. The box-missile electrical connector axial disengagement structure according to claim 1, wherein the cable shield (6) is mounted in the circumferential direction of the missile (2) and located at the tail of the missile (2), and the disengagement socket (3) and the disengagement plug (4) are both arranged axially along the missile (2).
5. The box spring electrical connector axial disengagement structure according to claim 4, wherein the catch (5) matches the installation position of the cable cover (6).
6. The box-missile electric connector axial falling-off separation structure as claimed in claim 5, wherein the cable cover (6) is installed at the circumferential bottom end of the tail part of the missile (2), and the stop pillar (5) is positioned on the inner bottom surface of the tail part of the box body.
7. The box spring electrical connector axial disengagement structure according to claim 5, wherein the installation position of the cable cover (6) and the catch (5) is any one of the following:
the cable cover (6) is installed at the circumferential top end of the tail of the missile (2), and the stop pillar (5) is located on the inner top surface of the tail of the box body;
the cable cover (6) is installed on the circumferential side face of the tail of the missile (2), and the stop column (5) is located on the inner side face of the tail of the box body.
8. The box-spring electrical connector axial disengagement structure according to claim 2, wherein one end of the disengagement plug (4) has a pull ring structure, which is fitted over the catch (5).
9. The box spring electrical connector axial disengagement structure according to claim 1, wherein the cable cover (6) and the separable electrical connector are made of a fire-resistant material.
10. The box-and-fire electrical connector axial disengagement structure according to claim 2, characterized in that the disengagement socket (3) is located near the end of the tail end of the missile (2), and does not exceed the tail end of the missile (2) in the axial direction of the missile (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110976870.2A CN113745906B (en) | 2021-08-24 | 2021-08-24 | Axial falling-off separating structure of box spring electric connector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110976870.2A CN113745906B (en) | 2021-08-24 | 2021-08-24 | Axial falling-off separating structure of box spring electric connector |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113745906A true CN113745906A (en) | 2021-12-03 |
| CN113745906B CN113745906B (en) | 2023-11-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110976870.2A Active CN113745906B (en) | 2021-08-24 | 2021-08-24 | Axial falling-off separating structure of box spring electric connector |
Country Status (1)
| Country | Link |
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| CN (1) | CN113745906B (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6193535B1 (en) * | 2000-02-10 | 2001-02-27 | G&H Technology, Inc. | Connector assembly with extreme temperature protective ceramic deadface |
| CN101212101A (en) * | 2006-12-26 | 2008-07-02 | 贵州航天电器股份有限公司 | Vertically split electric connector |
| CN105576461A (en) * | 2016-01-28 | 2016-05-11 | 中国航天科工集团第六研究院四十一所 | Electrical separation device for aircraft |
| CN106972318A (en) * | 2017-04-07 | 2017-07-21 | 北京机械设备研究所 | A kind of pull-off plug passively pulls mechanism |
| CN207250846U (en) * | 2017-08-15 | 2018-04-17 | 贵州航天天马机电科技有限公司 | One kind comes off push-pull structure |
| CN207398534U (en) * | 2017-11-14 | 2018-05-22 | 西安捷高电子科技有限公司 | A kind of vertical separation formula electric connector |
| CN109309318A (en) * | 2017-07-27 | 2019-02-05 | 中航光电科技股份有限公司 | A kind of umbilical connector and umbilical connector component |
| CN109378635A (en) * | 2018-09-13 | 2019-02-22 | 红色江山(湖北)导航技术有限公司 | A kind of declined inserting type falls off electric connection structure |
| CN109510028A (en) * | 2018-12-28 | 2019-03-22 | 天津航天长征火箭制造有限公司 | A kind of electric connector automatic separation system and method |
| CN109696082A (en) * | 2019-01-03 | 2019-04-30 | 西安航天动力技术研究所 | A kind of rocket launching electric connector fast-falling device |
| CN110021855A (en) * | 2019-06-05 | 2019-07-16 | 上海传输线研究所（中国电子科技集团公司第二十三研究所） | A kind of bracing wire separating type mechanical mechanism |
-
2021
- 2021-08-24 CN CN202110976870.2A patent/CN113745906B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6193535B1 (en) * | 2000-02-10 | 2001-02-27 | G&H Technology, Inc. | Connector assembly with extreme temperature protective ceramic deadface |
| CN101212101A (en) * | 2006-12-26 | 2008-07-02 | 贵州航天电器股份有限公司 | Vertically split electric connector |
| CN105576461A (en) * | 2016-01-28 | 2016-05-11 | 中国航天科工集团第六研究院四十一所 | Electrical separation device for aircraft |
| CN106972318A (en) * | 2017-04-07 | 2017-07-21 | 北京机械设备研究所 | A kind of pull-off plug passively pulls mechanism |
| CN109309318A (en) * | 2017-07-27 | 2019-02-05 | 中航光电科技股份有限公司 | A kind of umbilical connector and umbilical connector component |
| CN207250846U (en) * | 2017-08-15 | 2018-04-17 | 贵州航天天马机电科技有限公司 | One kind comes off push-pull structure |
| CN207398534U (en) * | 2017-11-14 | 2018-05-22 | 西安捷高电子科技有限公司 | A kind of vertical separation formula electric connector |
| CN109378635A (en) * | 2018-09-13 | 2019-02-22 | 红色江山(湖北)导航技术有限公司 | A kind of declined inserting type falls off electric connection structure |
| CN109510028A (en) * | 2018-12-28 | 2019-03-22 | 天津航天长征火箭制造有限公司 | A kind of electric connector automatic separation system and method |
| CN109696082A (en) * | 2019-01-03 | 2019-04-30 | 西安航天动力技术研究所 | A kind of rocket launching electric connector fast-falling device |
| CN110021855A (en) * | 2019-06-05 | 2019-07-16 | 上海传输线研究所（中国电子科技集团公司第二十三研究所） | A kind of bracing wire separating type mechanical mechanism |
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| Publication number | Publication date |
|---|---|
| CN113745906B (en) | 2023-11-17 |
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Address after: No. 1333-1 Zhongchun Road, Minhang District, Shanghai, 201109 Applicant after: SHANGHAI INSTITUTE OF ELECTROMECHANICAL ENGINEERING Address before: No. 3888, Yuanjiang Road, Minhang District, Shanghai, 201100 Applicant before: SHANGHAI INSTITUTE OF ELECTROMECHANICAL ENGINEERING |
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