CN114563202A - Cable disengagement system of rocket root bending moment monitoring system - Google Patents
Cable disengagement system of rocket root bending moment monitoring system Download PDFInfo
- Publication number
- CN114563202A CN114563202A CN202210139138.4A CN202210139138A CN114563202A CN 114563202 A CN114563202 A CN 114563202A CN 202210139138 A CN202210139138 A CN 202210139138A CN 114563202 A CN114563202 A CN 114563202A
- Authority
- CN
- China
- Prior art keywords
- rocket
- transmission terminal
- lever
- cable
- connector
- Prior art date
- 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.)
- Granted
Links
- 238000012544 monitoring process Methods 0.000 title claims abstract description 19
- 238000005452 bending Methods 0.000 title claims abstract description 17
- 230000005540 biological transmission Effects 0.000 claims abstract description 49
- 230000007246 mechanism Effects 0.000 claims abstract description 19
- 238000003780 insertion Methods 0.000 claims description 7
- 230000037431 insertion Effects 0.000 claims description 7
- 230000005389 magnetism Effects 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims description 4
- 238000000926 separation method Methods 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 230000003993 interaction Effects 0.000 abstract description 3
- 230000009471 action Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
Abstract
The invention discloses a cable disengaging system of a rocket root bending moment monitoring system, belonging to the technical field of rocket cable disengaging, and particularly comprising a main body and a disengaging device arranged on the main body, wherein the disengaging device comprises a shell and a cable inserted in the shell, a first transmission terminal is arranged in the shell, the cable is provided with a connector, an inserting groove is arranged in the connector, a second transmission terminal is arranged in the inserting groove, the second transmission terminal is inserted in the inserting groove, and a first magnetic block is arranged in the connector, the connector is inserted on the transmission terminal to carry out output transmission and interaction, and is limited by a lever limiting mechanism, when a rocket is launched, the lever limiting mechanism can be controlled to cancel limiting, and traction force generated during rocket launching can separate the connector from the terminal, so that the quick disengaging is realized, and additional mass can not be brought to rocket launching, the launching state of the rocket is influenced, and meanwhile, the disengaging mode is safe, and potential safety hazards cannot exist.
Description
Technical Field
The invention relates to the technical field of rocket cable separation, in particular to a cable separation system of a rocket root bending moment monitoring system.
Background
In order to obtain the wind load of the rocket body under the action of shallow wind in a target range and verify the effects of wind load design and a wind-proof load-reducing structure, a rocket root bending moment monitoring system is often adopted to monitor the projectile body. Because the monitoring system does not rise along with the rocket, the monitoring system not only meets the requirement of real-time monitoring of the root bending moment before the takeoff of the rocket, but also does not influence the safe takeoff of the rocket. The requirements for cable disconnection are: firstly, reliable disconnection of the cable is guaranteed on the premise that the state of the rocket is not changed, and then transmission of a strain signal is guaranteed before rocket transmission and launching.
The existing rocket root cable disconnection method is that the cable is usually pulled to be broken through traction force generated by rocket launching, firstly, the disconnection method can bring additional quality to the rocket launching and influence the rocket launching state, and secondly, because the cable is various in types, quality problems are easy to generate, and potential safety hazards can exist in a forced pulling-to-break mode.
Disclosure of Invention
The invention aims to provide a cable disengagement system of a rocket root bending moment monitoring system, which aims to solve the problems that the rocket launching state is influenced, the quality problem is easy to generate and the potential safety hazard exists in a forced snapping mode in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme: a cable releasing system of a rocket root bending moment monitoring system comprises a main body and a releasing device arranged on the main body, wherein the releasing device comprises a shell and a cable inserted in the shell, and a first transmission terminal is arranged in the shell, a connector is arranged on the cable, an inserting groove is arranged in the connector, a second transmission terminal is arranged in the inserting groove, the second transmission terminal is inserted in the inserting groove, a first magnetic block is arranged in the connector, a second magnetic block with the opposite magnetism to the first magnetic block is arranged in the transmission terminal II, the outer wall of the connector is provided with a lever limiting mechanism, the outer wall of one transmission terminal is provided with an annular flange, and the limit end of the lever limit mechanism is clamped on the annular flange, the shell is provided with an extension end, and the extension end is inserted in the main body, an elastic limiting mechanism is arranged in the main body, and the limiting end of the elastic limiting mechanism is inserted in the extension end.
Preferably, the lever limiting mechanism comprises a hydraulic device, a pressing block, a lever rod and a spring, the hydraulic device is arranged above and below the shell respectively, and the telescopic end of the hydraulic device is connected with the pressing block.
Preferably, the lever stick transversely articulates on the connector outer wall, and the vertical outside extension of one end of lever stick, the extension end and the lever stick of lever stick are each other perpendicular, and the extension end card of lever stick establishes on cyclic annular flange, the one end fixed establishment of spring is on the connector, and the other end of spring is connected with the free end of lever stick.
Preferably, the center point of the pressing block is consistent with the center point of the lever rod, and the lever rod is a carbon fiber lever rod.
Preferably, elasticity stop gear includes rotor plate, direct current magnet, and spacing inserted block, be equipped with in the main part and handle the end, and the other end of transmission terminal two transversely runs through casing, main body cover and handles the end and be connected, the rotor plate articulates on handling the end, and spacing inserted block establishes on the rotor plate, it has the spacing groove that can hold spacing inserted block to extend to hold.
Preferably, a groove is formed in one side, away from the limiting insertion block, of the rotating plate, a third magnetic block is installed in the groove, the center point of the direct current electromagnet is consistent with the center point of the third magnetic block, and the direct current electromagnet is used for changing the direction of the magnetic field to adsorb or repel the third magnetic block.
Preferably, an installation groove capable of accommodating the second transmission terminal is formed in the first transmission terminal, and the second transmission terminal is inserted into the installation groove.
Preferably, the housing is made of PPS or POM, a through groove is formed in one side of the housing, and the cable is located in the through groove.
Compared with the prior art, the invention has the beneficial effects that:
1) the connector is inserted into the transmission terminal to carry out output transmission and interaction, and is limited by the lever limiting mechanism, when the rocket is launched, the lever limiting mechanism can be controlled to cancel limiting, and the connector is separated from the transmission terminal by traction force generated during rocket launching, so that quick release is realized, additional quality cannot be brought to rocket launching, the launching state of the rocket is not influenced, and meanwhile, the release mode is safe, and potential safety hazards cannot exist.
2) The shell is fixed on the main body through the elastic limiting mechanism, and the limitation on the shell can be cancelled by controlling the operation of the elastic limiting mechanism, so that the shell is separated from the main body, and the self weight of the rocket during launching is reduced.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the internal structure of the housing according to the present invention;
FIG. 3 is a schematic structural diagram of a first magnetic block of the present invention;
FIG. 4 is a schematic view of the structure of the mounting groove of the present invention;
FIG. 5 is a schematic view of the elastic limiting mechanism of the present invention;
FIG. 6 is an enlarged view of the point A in FIG. 5 according to the present invention.
In the figure: the device comprises a main body 1, a shell 2, a cable 3, a through groove 4, a connector 5, a transmission terminal 6, a first magnetic block 7, a spring 8, a lever rod 9, a hydraulic device 10, a pressing block 11, a transmission terminal 12, a second magnetic block 13, an annular flange 14, an extending end 15, a limiting groove 16, a mounting groove 17, a rotating plate 18, a limiting inserting block 19, a direct current electromagnet 20 and a magnetic block 21.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
The embodiment is as follows:
referring to fig. 1-6, the present invention provides a technical solution: a cable disengagement system of a rocket root bending moment monitoring system comprises a main body 1 and a disengagement device arranged on the main body 1, wherein the disengagement device comprises a shell 2 and a cable 3 inserted in the shell 2, a transmission terminal I12 is arranged in the shell 2, a connector 5 is arranged on the cable 3, a slot is formed in the connector 5, a transmission terminal II 6 is arranged in the slot, the transmission terminal II 6 is inserted in the slot, the transmission terminal I12 is connected with the transmission terminal II 6 to realize data transmission and interaction, a magnetic block I7 is arranged in the connector 5, a magnetic block II 13 with the magnetism opposite to that of the magnetic block I7 is arranged in the transmission terminal II 6, the connector 5 can move from the transmission terminal I12 due to the force generated by mutual repulsion of the magnetic block I7 and the magnetic block II 13, and the cable 3, the cable can be separated from the transmission terminal I12 by combining with the traction force generated during rocket launching, so that the cable 3 and the cable can be separated from the transmission terminal II, The connector 5 shifts out from the casing 2 through the through groove 4, realizes the action of breaking away, the 5 outer walls of connector are equipped with lever stop gear, transmission terminal 12 outer walls are equipped with annular flange 14, and lever stop gear's spacing end card is established on annular flange 14, can control lever stop gear's spacing end and the separation of annular flange 14, and it is spacing to cancel, and the traction force that produces during rocket launch can make connector 5 and transmission terminal 12 separate to realized breaking away fast, can not bring additional quality to the rocket launch, be equipped with extension 15 on the casing 2, and extension 15 inserts and establish in main part 1, be equipped with elasticity stop gear in the main part 1, and elasticity stop gear's spacing end is inserted and is established in extension 15.
The lever limiting mechanism comprises a hydraulic device 10, a pressing block 11, a lever rod 9 and a spring 8, wherein the hydraulic device 10 is respectively arranged above and below the shell 2, the telescopic end of the hydraulic device 10 is connected with the pressing block 11, the lever rod 9 is transversely hinged on the outer wall of the connector 5, one end of the lever rod 9 longitudinally extends outwards, the extending end of the lever rod 9 is perpendicular to the lever rod 9, the extending end of the lever rod 9 is clamped on the annular flange 14, when the main body 1 emits light, the hydraulic device 10 works to drive the pressing block 11 to extend out, the pressing block 11 presses the free end of the lever rod 9, so that the other end of the lever rod 9 is tilted, the other end of the lever rod 9 is separated from the annular flange 14, the limit of the connector 5 on the transmission terminal I12 is cancelled, one end of the spring 8 is fixedly arranged on the connector 5, and the other end of the spring 8 is connected with the free end of the lever rod 9, spring 8 can pull lever stick 9, realizes restoring to the throne of lever stick 9, the central point of briquetting 11 is unanimous with the central point of lever stick 9, and lever stick 9 is the carbon fiber lever stick, alleviates lever stick 9's weight and strengthens intensity simultaneously.
The elastic limiting mechanism comprises a rotating plate 18, a direct current electromagnet 20 and a limiting insertion block 19, a processing end is arranged in the main body 1, the other end of the transmission terminal II 6 transversely penetrates through the shell 2 and the shell of the main body 1 to be connected with the processing end, the rotating plate 18 is hinged on the processing end, the limiting insertion block 19 is arranged on the rotating plate 18, a limiting groove 16 capable of containing the limiting insertion block 19 is formed in the extending end 15, a groove is formed in one side, away from the limiting insertion block 19, of the rotating plate 18, a magnetic block III 21 is arranged in the groove, the center point of the direct current electromagnet 20 is consistent with the center point of the magnetic block III 21, the direct current electromagnet 20 is used for changing the direction of a magnetic field to adsorb or repel the magnetic block III 21, the direct current electromagnet 20 works to change the direction of current, and accordingly the magnetism is changed, the direct current electromagnet 20 adsorbs the magnetic block III 21 to drive the rotating plate 18 to move, the rotating plate 18 moves towards the direction of the direct current electromagnet 20 to drive the limiting insertion block 19 to move out of the limiting groove 16, and the limitation on the extension end 15 is cancelled, so that the shell 2 can be taken off from the main body 1, and the self weight of the main body 1 is reduced.
The transmission terminal I12 is internally provided with a mounting groove 17 capable of accommodating the transmission terminal II 6, the transmission terminal II 6 is inserted into the mounting groove 17, the shell 2 is made of PPS or POM, the weight is lighter, the hardness is higher, one side of the shell 2 is provided with a through groove 4, and the cable 3 is positioned in the through groove 4.
The working principle is as follows: when the rocket launcher is used, when the main body 1 launches, the hydraulic device 10 works to drive the press block 11 to stretch out, the press block 11 presses the free end of the lever rod 9, so that the other end of the lever rod 9 tilts, the other end of the lever rod 9 is separated from the annular flange 14, the limit of the connector 5 on the transmission terminal I12 is cancelled, meanwhile, the connector 5 can move from the transmission terminal I12 due to the force generated by mutual repulsion of the magnetic block I7 and the magnetic block II 13, the cable 3 and the connector 5 can move out of the shell 2 through the through groove 4 by combining the traction force generated during rocket launching, the disengaging action is realized, meanwhile, the direct current electromagnet 20 works to change the direction of current, so that the magnetism is changed, the direct current electromagnet 20 adsorbs the magnetic block III 21 to drive the rotating plate 18 to move, the rotating plate 18 moves towards the direction of the direct current electromagnet 20 to drive the limit inserting block 19 to move out of the limit groove 16, the limit of the extension end 15 is eliminated, so that the shell 2 can be taken off from the main body 1, and the weight of the main body 1 is reduced.
While there have been shown and described the fundamental principles and essential features of the invention and advantages thereof, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof; the present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein, and any reference signs in the claims are not to be construed as limiting the claims.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The utility model provides a rocket root bending moment monitoring system's cable system of breaking away, includes main part (1) and establishes the disengaging gear on main part (1), its characterized in that: the separation device comprises a shell (2) and a cable (3) inserted into the shell (2), a first transmission terminal (12) is arranged in the shell (2), a connector (5) is arranged on the cable (3), a slot is formed in the connector (5), a second transmission terminal (6) is arranged in the slot, the second transmission terminal (6) is inserted into the slot, a first magnetic block (7) is arranged in the connector (5), a second magnetic block (13) with the magnetism opposite to that of the first magnetic block (7) is arranged in the second transmission terminal (6), a lever limiting mechanism is arranged on the outer wall of the connector (5), an annular flange (14) is arranged on the outer wall of the first transmission terminal (12), a limiting end of the lever limiting mechanism is clamped on the annular flange (14), an extension end (15) is arranged on the shell (2), and the extension end (15) is inserted into the main body (1), an elastic limiting mechanism is arranged in the main body (1), and a limiting end of the elastic limiting mechanism is inserted into the extending end (15).
2. The cable release system of a rocket root bending moment monitoring system according to claim 1, wherein: the lever limiting mechanism comprises a hydraulic device (10), a pressing block (11), a lever rod (9) and a spring (8), wherein the hydraulic device (10) is arranged above and below the shell (2) respectively, and the telescopic end of the hydraulic device (10) is connected with the pressing block (11).
3. The cable release system of a rocket root bending moment monitoring system according to claim 2, wherein: lever stick (9) transversely articulates on connector (5) outer wall, and the vertical outside extension of one end of lever stick (9), the extension end and the lever stick (9) of lever stick (9) are each other perpendicular, and the extension end card of lever stick (9) establishes on annular flange (14), the one end of spring (8) is fixed to be established on connector (5), and the other end of spring (8) is connected with the free end of lever stick (9).
4. The cable release system of a rocket root bending moment monitoring system according to claim 3, wherein: the central point of the pressing block (11) is consistent with the central point of the lever rod (9), and the lever rod (9) is a carbon fiber lever rod.
5. The cable release system of a rocket root bending moment monitoring system according to claim 1, wherein: elasticity stop gear includes rotor plate (18), direct current magnet (20), with spacing inserted block (19), be equipped with in main part (1) and handle the end, and the other end of transmission terminal two (6) transversely runs through casing (2), main part (1) shell and handles the end and be connected, rotor plate (18) articulate and handle and serve, and just establish on rotor plate (18) spacing inserted block (19), set up spacing groove (16) that can hold spacing inserted block (19) in extension end (15).
6. The cable release system of a rocket root bending moment monitoring system according to claim 5, wherein: one side of the rotating plate (18) deviating from the limiting insertion block (19) is provided with a groove, a third magnetic block (21) is installed in the groove, the central point of the direct current electromagnet (20) is consistent with the central point of the third magnetic block (21), and the direct current electromagnet (20) is used for changing the direction of the magnetic field to adsorb or repel the third magnetic block (21).
7. The cable release system of a rocket root bending moment monitoring system according to claim 1, wherein: an installation groove (17) capable of accommodating the second transmission terminal (6) is formed in the first transmission terminal (12), and the second transmission terminal (6) is inserted into the installation groove (17).
8. The cable release system of a rocket root bending moment monitoring system according to claim 1, wherein: the casing (2) is made of PPS or POM, a through groove (4) is formed in one side of the casing (2), and the cable (3) is located in the through groove (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210139138.4A CN114563202B (en) | 2022-02-15 | 2022-02-15 | Cable disconnection system of rocket root bending moment monitoring system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210139138.4A CN114563202B (en) | 2022-02-15 | 2022-02-15 | Cable disconnection system of rocket root bending moment monitoring system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114563202A true CN114563202A (en) | 2022-05-31 |
| CN114563202B CN114563202B (en) | 2023-10-27 |
Family
ID=81714378
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210139138.4A Active CN114563202B (en) | 2022-02-15 | 2022-02-15 | Cable disconnection system of rocket root bending moment monitoring system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114563202B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0439200A (en) * | 1990-06-06 | 1992-02-10 | Natl Space Dev Agency Japan<Nasda> | Launch-lock system applied to small pocket/micro-gravity experimental device |
| EP0685702A1 (en) * | 1994-06-02 | 1995-12-06 | AEROSPATIALE Société Nationale Industrielle | Launching installation for a wire-guided rocket |
| KR20110091132A (en) * | 2010-02-05 | 2011-08-11 | 김준영 | Antenna of terminal box and locking/unlocking apparatus for automatic meter reading apparatus |
| EP2383633A1 (en) * | 2010-04-27 | 2011-11-02 | Giga-Byte Technology Co., Ltd. | Mouse device with a separable transmission cable |
| US20130007935A1 (en) * | 2010-02-11 | 2013-01-10 | Chin Howard M | Rocket Launch System and Supporting Apparatus |
| CN108731958A (en) * | 2018-04-04 | 2018-11-02 | 北京强度环境研究所 | A kind of cable disengaging gear of rocket root bending moment monitoring system |
| JP2020120502A (en) * | 2019-01-24 | 2020-08-06 | 株式会社高橋国際商事 | Charging cable and charging cable system |
| US20210016194A1 (en) * | 2019-07-18 | 2021-01-21 | Ace Light & Electronic Tech (Ningbo) Co., Ltd. | Rocket with landing cabin |
-
2022
- 2022-02-15 CN CN202210139138.4A patent/CN114563202B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0439200A (en) * | 1990-06-06 | 1992-02-10 | Natl Space Dev Agency Japan<Nasda> | Launch-lock system applied to small pocket/micro-gravity experimental device |
| EP0685702A1 (en) * | 1994-06-02 | 1995-12-06 | AEROSPATIALE Société Nationale Industrielle | Launching installation for a wire-guided rocket |
| KR20110091132A (en) * | 2010-02-05 | 2011-08-11 | 김준영 | Antenna of terminal box and locking/unlocking apparatus for automatic meter reading apparatus |
| US20130007935A1 (en) * | 2010-02-11 | 2013-01-10 | Chin Howard M | Rocket Launch System and Supporting Apparatus |
| EP2383633A1 (en) * | 2010-04-27 | 2011-11-02 | Giga-Byte Technology Co., Ltd. | Mouse device with a separable transmission cable |
| CN108731958A (en) * | 2018-04-04 | 2018-11-02 | 北京强度环境研究所 | A kind of cable disengaging gear of rocket root bending moment monitoring system |
| JP2020120502A (en) * | 2019-01-24 | 2020-08-06 | 株式会社高橋国際商事 | Charging cable and charging cable system |
| US20210016194A1 (en) * | 2019-07-18 | 2021-01-21 | Ace Light & Electronic Tech (Ningbo) Co., Ltd. | Rocket with landing cabin |
Non-Patent Citations (2)
| Title |
|---|
| 吴华兵;尹贻国;陈志红;姜铁华;: "运载火箭火工品分离装置电磁发射测量与分析", 微波学报, no. 3 * |
| 杨森;赵宪斌;曾志;张乐;高昱;: "火箭发射装置上一种插拔机构改进设计", 山东工业技术, no. 18 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114563202B (en) | 2023-10-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110007405A (en) | With self-locking twin fiber cable connector and its assembling structure and disassembly and unlocking tool | |
| CN104022397B (en) | A kind of reduce contact engaging and separating force and be convenient to plug connector | |
| CN114563202A (en) | Cable disengagement system of rocket root bending moment monitoring system | |
| CN109755433A (en) | A kind of lithium battery | |
| CN102147510A (en) | Cable assembly having floatable optical module | |
| CN111348194A (en) | Microminiature unmanned aerial vehicle guided missile mounting and releasing device integrated with fire control system | |
| CN111409843A (en) | Task equipment connecting mechanism | |
| CN103807252A (en) | Electromagnetic chuck type remote control locking and releasing device | |
| CN2906972Y (en) | Grating type tube-spring jack multiple-locking rectangular electric connector | |
| CN207731835U (en) | A kind of disengaging electrical conduction mechanism | |
| CN208979100U (en) | One kind is to ammunition locking arrangement and aircraft | |
| US2816341A (en) | Connector | |
| CN216611612U (en) | Electromagnetic releasing mechanism | |
| CN219875979U (en) | Driving lever type intelligent sound system | |
| CN213619374U (en) | Locking mechanism of charging gun | |
| CN218734321U (en) | Optical module with easy-to-pull structure | |
| CN215956374U (en) | HDMI + USB wireless transmitter | |
| CN203850512U (en) | Miniature rectangular electric connector | |
| CN203631862U (en) | Separating, pressing and pulling mechanism | |
| CN219759845U (en) | Battery locking device and aircraft | |
| CN208923490U (en) | The connector of combined type flexible printed circuit board | |
| CN216057714U (en) | Temperature measurement module mounting structure of connector | |
| CN112072278B (en) | Unmanned aerial vehicle antenna | |
| CN108974362A (en) | To ammunition locking arrangement and aircraft | |
| CN218489480U (en) | Charging gun |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |