CN114563202B - Cable disconnection system of rocket root bending moment monitoring system - Google Patents
Cable disconnection system of rocket root bending moment monitoring system Download PDFInfo
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- CN114563202B CN114563202B CN202210139138.4A CN202210139138A CN114563202B CN 114563202 B CN114563202 B CN 114563202B CN 202210139138 A CN202210139138 A CN 202210139138A CN 114563202 B CN114563202 B CN 114563202B
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- rocket
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- cable
- connector
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 17
- 238000005452 bending Methods 0.000 title claims abstract description 12
- 230000005540 biological transmission Effects 0.000 claims abstract description 46
- 230000007246 mechanism Effects 0.000 claims abstract description 17
- 238000012545 processing Methods 0.000 claims description 9
- 230000005389 magnetism Effects 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 230000003993 interaction Effects 0.000 abstract description 3
- 230000009471 action Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000000034 method 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
Classifications
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- 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
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Details Of Connecting Devices For Male And Female Coupling (AREA)
Abstract
The invention discloses a cable disengaging system of a rocket root bending moment monitoring system, which belongs to the technical field of rocket cable disengaging, and particularly relates to a cable disengaging system of a rocket root bending moment monitoring system, which comprises 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, a connector is arranged on the cable, a slot is arranged in the connector, a second transmission terminal is arranged in the slot, a first magnetic block is arranged in the connector, the connector is inserted on the transmission terminal for output transmission and interaction, and the lever limiting mechanism is used for limiting, when a rocket is launched, the lever limiting mechanism can be controlled to cancel limiting, and the connector is separated from the transmission terminal due to traction force generated during rocket launching, so that quick disengaging is realized, additional quality is not brought to rocket launching, rocket launching state is influenced, meanwhile, the disengaging mode is safer, and potential safety hazards are avoided.
Description
Technical Field
The invention relates to the technical field of rocket cable detachment, in particular to a cable detachment 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, the effects of wind load design and wind-proof load shedding structures are verified, and 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 monitoring the root bending moment of the rocket before taking off in real time, but also does not influence the safe taking off of the rocket. Requirements are set for cable disconnection: firstly, the reliable disconnection of the cable is ensured on the premise of not changing the rocket state, and then the transmission of strain signals before rocket transmission and emission is ensured.
The existing rocket root cable disconnection mode is usually that the cable is broken through traction force generated by rocket launching, the disconnection method firstly brings additional mass to rocket launching and influences the rocket launching state, and secondly, the cable is various and easy to generate quality problems and potential safety hazards exist in a forced breaking mode.
Disclosure of Invention
The invention aims to provide a cable disconnection system of a rocket root bending moment monitoring system, which solves the problems that the state of rocket launching is influenced, the quality problem is easy to generate, and the potential safety hazard exists in a forced breaking mode.
In order to achieve the above purpose, the present invention provides the following technical solutions: the utility model provides a cable release system of rocket root moment of flexure monitoring system, includes the main part and establishes the disengaging gear in the main part, disengaging gear includes the casing and inserts the cable of establishing in the casing, and is equipped with transmission terminal one in the casing, be equipped with the connector on the cable, and seted up the slot in the connector, be equipped with transmission terminal two in the slot, transmission terminal two inserts and establishes in the slot, and is equipped with magnet one in the connector, be equipped with magnet two opposite with magnet one magnetism in the transmission terminal two, the connector outer wall is equipped with lever stop gear, transmission terminal one outer wall is equipped with annular flange, and lever stop gear's spacing end card is established on annular flange, be equipped with the extension end on the casing, and the extension end inserts and establish in the main part, be equipped with elasticity stop gear in the main part, and elasticity stop gear's spacing end inserts and establish in the extension end.
Preferably, the lever limiting mechanism comprises a hydraulic device, a pressing block, a lever rod and a spring, wherein the hydraulic device is respectively arranged above and below the shell, and the telescopic end of the hydraulic device is connected with the pressing block.
Preferably, the lever rod is transversely hinged on the outer wall of the connector, one end of the lever rod longitudinally extends outwards, the extending end of the lever rod is perpendicular to the lever rod, the extending end of the lever rod is clamped on the annular flange, one end of the spring is fixedly arranged on the connector, and the other end of the spring is connected with the free end of the lever rod.
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, the elastic limiting mechanism comprises a rotating plate, a direct current electromagnet and a limiting plug block, a processing end is arranged in the main body, the other end of the second transmission terminal transversely penetrates through the shell and the main body shell to be connected with the processing end, the rotating plate is hinged to the processing end, the limiting plug block is arranged on the rotating plate, and a limiting groove capable of accommodating the limiting plug block is formed in the extending end.
Preferably, a groove is formed in one side, away from the limiting insertion block, of the rotating plate, a third magnetic block is arranged 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, the first transmission terminal is provided with a mounting groove capable of accommodating the second transmission terminal, and the second transmission terminal is inserted into the mounting groove.
Preferably, the shell is made of PPS or POM, a through groove is formed on one side of the shell, 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 on the transmission terminal for output transmission and interaction, and is limited by the 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 transmission terminal, so that quick release is realized, additional quality cannot be brought to rocket launching, the launching state of the rocket is influenced, and meanwhile, the release mode is safer and no potential safety hazard exists.
2) The shell is fixed on the main body through the elastic limiting mechanism, and the limiting of the shell can be canceled by controlling the operation of the elastic limiting mechanism, so that the shell is taken off from the main body, and the weight of the rocket during launching is reduced.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view of the internal structure of the housing of the present invention;
FIG. 3 is a schematic diagram of a magnetic block according to 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 schematic view of fig. 5 a in accordance with the present invention.
In the figure: the magnetic circuit comprises a main body 1, a housing 2, a cable 3, a through groove 4, a connector 5, a transmission terminal 6, a magnetic block 7, a spring 8, a lever 9, a hydraulic device 10, a pressing block 11, a transmission terminal 12, a 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 plug 19, a direct current electromagnet 20 and a magnetic block 21.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Examples:
referring to fig. 1-6, the present invention provides a technical solution: the utility model provides a cable release system of rocket root moment of flexure monitoring system, includes main part 1 and establishes the disengaging gear on main part 1, disengaging gear includes casing 2 and inserts the cable 3 of establishing in casing 2, and is equipped with transmission terminal one 12 in the casing 2, be equipped with connector 5 on the cable 3, and set up the slot in the connector 5, be equipped with transmission terminal two 6 in the slot, transmission terminal two 6 inserts and establishes in the slot, transmission terminal one 12 and transmission terminal two 6 are connected and can realize transmission and interaction of data, and be equipped with magnetic path one 7 in the connector 5, be equipped with in transmission terminal two 6 with magnetic path two 13 opposite to magnetic path one 7, because magnetic path one 7 and magnetic path two 13 mutually repel the power that produces for connector 5 can follow transmission terminal one 12 and remove, the traction force that produces when combining the rocket launches can make cable 3, connector 5 shift out from casing 2 through logical groove 4, the connector 5 outer wall is equipped with stop gear, transmission terminal one 12 outer wall is equipped with annular flange 14, and the annular stop gear establishes the end and can realize the transmission with annular stop gear, and stop gear can realize the annular stop gear and the end is equipped with in the annular flange 14, and the end 15 is set up in the annular stop gear is can not extended to the main part 1, and the end 15 is realized to the end is launched to the extension in the extension of the main part 1, and the end is realized to the extension, and the end is extended to the end is realized to the end 15 is launched to the extension to the rocket.
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 inside of 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 to 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 and the lever rod 9 are perpendicular to each other, the extending end of the lever rod 9 is clamped on the annular flange 14, when the main body 1 is launched, the hydraulic device 10 works to drive the pressing block 11 to extend, 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 first transmission terminal 12 is canceled, one end of the spring 8 is fixedly arranged on the connector 5, the other end of the spring 8 is connected with the free end of the lever rod 9, the spring 8 can pull the lever rod 9, the center point of the pressing block 11 is consistent with the center point of the lever rod 9, the lever rod 9 is realized, and the weight of the lever rod 9 is improved, and the weight of the lever rod 9 is also improved.
The elastic limiting mechanism comprises a rotating plate 18, a direct-current electromagnet 20 and a limiting insert block 19, wherein 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 and is connected with the processing end, the rotating plate 18 is hinged to the processing end, the limiting insert block 19 is arranged on the rotating plate 18, a limiting groove 16 capable of accommodating the limiting insert block 19 is formed in the extending end 15, a groove is formed in one side, deviating from the limiting insert 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 a current, so that magnetism is changed, the direct-current electromagnet 20 adsorbs and drives the rotating plate 18 to move, the limiting insert block 19 is moved out of the limiting groove 16, and the limiting of the extending end 15 is canceled, so that the shell 2 can be detached from the main body 1.
The first transmission terminal 12 is internally provided with a mounting groove 17 capable of accommodating the second transmission terminal 6, the second transmission terminal 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.
Working principle: when the rocket type electromagnetic rotating device is used, when the main body 1 is launched, the hydraulic device 10 works to drive the pressing block 11 to extend, the pressing block 11 presses the free end of the lever rod 9, so that the other end of the lever rod 9 is lifted, the other end of the lever rod 9 is separated from the annular flange 14, the limit of the connector 5 on the first transmission terminal 12 is canceled, meanwhile, due to the force generated by mutual repulsion of the first magnetic block 7 and the second magnetic block 13, the connector 5 can move from the first transmission terminal 12, the cable 3 and the connector 5 can be moved out of the shell 2 through the through groove 4 in combination with 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, the magnetism is changed, the direct current electromagnet 20 adsorbs the magnetic block three 21 to drive the rotating plate 18 to move, the rotating plate 18 moves the limit plug 19 to move out of the limit groove 16 towards the direction of the direct current electromagnet 20, and the limit of the extension end 15 is canceled, and the shell 2 can be taken off from the main body 1, and the self weight of the main body 1 is lightened.
While the fundamental and principal features of the invention and advantages of the invention have been shown and described, 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 may be embodied in 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.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. The utility model provides a cable uncoupling system of rocket root moment of flexure monitoring system, includes main part (1) and sets up the uncoupling device on main part (1), its characterized in that: the disengaging device comprises a shell (2) and a cable (3) inserted in the shell (2), wherein 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, a first magnetic block (7) is arranged in the connector (5), a second magnetic block (13) with opposite magnetism to 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), the limiting end of the lever limiting mechanism is clamped on the annular flange (14), an extending end (15) is arranged on the shell (2), the extending end (15) is inserted in a main body (1), an elastic limiting mechanism is arranged in the main body (1), and the limiting end of the elastic limiting mechanism is inserted in the extending end (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 inside of the shell (2), and the telescopic end of the hydraulic device (10) is connected with the pressing block (11);
the lever rod (9) is transversely hinged to 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), 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);
the shell (2) is made of PPS or POM, a through groove (4) is formed in one side of the shell (2), and the cable (3) is located in the through groove (4).
2. A cable disconnect system for a rocket root bending moment monitoring system according to claim 1, wherein: the center point of the pressing block (11) is consistent with the center point of the lever rod (9), and the lever rod (9) is a carbon fiber lever rod.
3. A cable disconnect system for a rocket root bending moment monitoring system according to claim 1, wherein: the elastic limiting mechanism comprises a rotating plate (18), a direct-current electromagnet (20) and a limiting inserting block (19), wherein a processing end is arranged in the main body (1), the other end of the second transmission terminal (6) transversely penetrates through the shell (2) and the shell of the main body (1) and is connected with the processing end, the rotating plate (18) is hinged to the processing end, the limiting inserting block (19) is arranged on the rotating plate (18), and a limiting groove (16) capable of containing the limiting inserting block (19) is formed in the extending end (15).
4. A cable disconnect system for a rocket root bending moment monitoring system according to claim 3, wherein: the rotating plate (18) is provided with a groove on one side deviating from the limiting plug block (19), 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), and the direct current electromagnet (20) is used for changing the direction of a magnetic field to adsorb or repel the magnetic block III (21).
5. A cable disconnect system for a rocket root bending moment monitoring system according to claim 1, wherein: a mounting 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 mounting groove (17).
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 CN114563202A (en) | 2022-05-31 |
| CN114563202B true CN114563202B (en) | 2023-10-27 |
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| 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 |
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| CN (1) | CN114563202B (en) |
Citations (6)
| 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 |
| 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 |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SG183205A1 (en) * | 2010-02-11 | 2012-09-27 | Howard M Chin | Rocket launch system and supporting apparatus |
| CN210583656U (en) * | 2019-07-18 | 2020-05-22 | 宁波艾森光电科技有限公司 | Landing rocket |
-
2022
- 2022-02-15 CN CN202210139138.4A patent/CN114563202B/en active Active
Patent Citations (6)
| 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 |
| 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 |
Non-Patent Citations (4)
| 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.2012,(第S3期), * |
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