CN109696082B - Rocket launching electric connector quick falling device - Google Patents
Rocket launching electric connector quick falling device Download PDFInfo
- Publication number
- CN109696082B CN109696082B CN201910005271.9A CN201910005271A CN109696082B CN 109696082 B CN109696082 B CN 109696082B CN 201910005271 A CN201910005271 A CN 201910005271A CN 109696082 B CN109696082 B CN 109696082B
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- China
- Prior art keywords
- rotating arm
- plug
- cover plate
- rocket
- shifting fork
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
-
- 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 discloses a rocket launching electric connector quick falling device which comprises a plug shell, a rotating arm shaft, a rotating arm bracket, a base, a tension spring, a traction rope, a shifting fork, a gas cover plate and a pressure spring linkage mechanism, wherein the plug shell is provided with a plug hole; the plug shell is used for fixing a plug of an external electric connector, the plug shell is hinged with the rotating arm, the rotating arm is movably connected with the rotating arm support through a rotating arm shaft, the rotating arm support is fixed on the base, and the tension spring is fixed between the rotating arm and the base; one end of the shifting fork is fixed with the rotating arm shaft, the other end of the shifting fork props against the gas cover plate, and the middle part of the shifting fork is connected with the rotating arm through a traction rope; when the rocket is ignited, the plug shell is driven to move horizontally, the rotating arm drives the plug shell to rotate around the rotating arm shaft under the action of the tension spring, the plug is separated from a socket on the rocket, meanwhile, the rotating arm drives the shifting fork to rotate through the traction rope, the limit of the gas cover plate is relieved, and the pressure spring linkage mechanism drives the gas cover plate to cover the plug. The invention can ensure that the electric connector is ignited firstly and then falls off, and the rocket is reliably and accurately launched.
Description
Technical Field
The invention relates to the technical field of rocket electrical plugs, in particular to a quick dropping device of a rocket launching electrical connector.
Background
The falling off of the electrical plug is a very important link when the rocket is launched. The general electrical plug falls off and is separated by external force before ignition, for example, the electrical plug falls off and is firstly fallen off and then ignited by utilizing a motor to drive a mechanical plug mechanism, an electromagnetic pin spring plug mechanism and other electrical plug falling off devices. The devices have the problems of complex structure, long installation and test process period, easy damage, difficult maintenance work and the like, and the accuracy of the rocket launching starting zero point is influenced by the procedure of firstly dropping and then igniting.
Therefore, a device which is efficient, simple and easy to maintain and can realize quick falling of the electrical plug needs to be designed so as to complete the working procedure of firstly igniting and then passively falling of the electrical connector and reliably guarantee the rocket launching task.
Disclosure of Invention
In view of the above, the invention provides a rapid dropping device for a rocket launching electric connector, which can make the electric connector drop after ignition, and the rocket launching is reliable and accurate.
The specific embodiment of the invention is as follows:
a rocket launching electric connector quick falling device comprises a plug shell, a rotating arm shaft, a rotating arm bracket, a base, a tension spring, a traction rope, a shifting fork, a gas cover plate and a pressure spring linkage mechanism;
the plug shell is used for fixing a plug of an external electric connector, the plug shell is hinged with the rotating arm, the rotating arm is movably connected with the rotating arm support through a rotating arm shaft, the rotating arm support is fixed on the base, one end of the tension spring is fixedly connected with the rotating arm, and the other end of the tension spring is fixedly connected with the base; one end of the shifting fork is fixedly connected with the rotating arm shaft, the other end of the shifting fork props against the gas cover plate for limiting, and meanwhile, the middle part of the shifting fork is connected with the rotating arm through a traction rope;
when the rocket is ignited, the plug shell is driven to move horizontally, the rotating arm drives the plug shell to rotate around the rotating arm shaft under the action of the tension spring, a plug of an external electric connector is separated from a socket on the rocket, meanwhile, the rotating arm drives the shifting fork to rotate through the traction rope, the limit of the gas cover plate is relieved, and the pressure spring linkage mechanism provides power for the gas cover plate to enable the gas cover plate to cover the plug on the plug shell.
Furthermore, the pressure spring linkage mechanism comprises a pressure spring, a sliding block, a movable pulley and a steel wire rope;
one end of the steel wire rope is fixedly connected with the gas cover plate, the other end of the steel wire rope rounds a movable pulley and is fixedly connected with an external rocket direction finder, the movable pulley is fixed on a sliding block, and the pressure spring is compressed and limited by the sliding block.
Furthermore, a kidney-shaped hole is formed in the rotating arm, and a rotating arm shaft in the kidney-shaped hole can slide relative to the kidney-shaped hole.
Has the advantages that:
1. the invention adopts the spring connecting rod to realize the falling of the electrical plug, has simple structure, realizes the procedure of the electric connector falling after ignition, adopts mechanical separation and has high reliability; meanwhile, the follow-up unlocking pressure spring linkage mechanism drives the gas cover plate to slide to cover the plug on the plug shell, so that gas is blocked, and the electric connector and the falling-off device can be prevented from being ablated by rocket tail flames.
2. The pressure spring linkage mechanism adopts the principle form of a movable pulley, effectively increases the speed and the stroke of the gas cover plate in a limited space, and solves the problem of increasing the motion amplitude of the gas cover plate in an effective acting force range.
3. According to the invention, the waist-shaped hole is formed in the rotating arm, so that on one hand, the socket and the plug of the electric connector can reliably fall off, the bending of the contact pin is avoided, and the plug cannot be short-circuited or broken; on the other hand, the rotating arm shaft and the waist-shaped hole can slide relatively, so that the installation sizes of the socket on the rocket and the plug on the device can be adjusted conveniently, and the launching requirements of rockets of different models can be met.
Drawings
FIG. 1 is a front view of the present invention;
FIG. 2 is a top view of the present invention;
fig. 3 is a right side view of the present invention.
The device comprises a plug shell 1, a rotating shaft screw 2, a rotating arm 3, a rotating arm shaft 4, a tension spring 5, a rotating arm support 6, a base 7, a shifting fork 8, a sliding block 9, a pressure spring 10, a movable pulley 11, a steel wire rope 12, a sliding block rail 13, a cover plate rail 14, a rocket support rail 15, a traction rope 16 and a gas cover plate 17.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a rocket launching electric connector quick falling device which is arranged on a launcher orientator and comprises a plug shell 1, a rotating shaft screw 2, a rotating arm 3, a rotating arm shaft 4, a tension spring 5, a rotating arm bracket 6, a base 7, a shifting fork 8, a sliding block 9, a compression spring 10, a movable pulley 11, a steel wire rope 12, a traction rope 16 and a gas cover plate 17 as shown in figures 1-3.
The plug shell 1 is used for fixing a plug of an external electric connector, the plug shell 1 is hinged with the rotating arm 3 through the rotating shaft screw 2, the rotating arm 3 is movably connected with the rotating arm support 6 through the rotating arm shaft 4, a waist-shaped hole is formed in the rotating arm 3, the rotating arm shaft 4 is located in the waist-shaped hole, and the rotating arm shaft 4 can slide relative to the waist-shaped hole.
The rotating arm bracket 6 is fixed on the base 7, one end of the tension spring 5 is fixedly connected with the rotating arm 3, and the other end is fixedly connected with the base 7. One end of the shifting fork 8 is fixedly connected with the rotating arm shaft 4, the other end of the shifting fork supports against the gas cover plate 17 and is used for limiting the position of the gas cover plate 17, and meanwhile, the middle part of the shifting fork 8 is connected with the rotating arm 3 through a traction rope 16.
The launcher orientator is provided with a cover plate track 14 for a gas cover plate 17 to slide, the gas cover plate 17 is fixedly connected with one end of a steel wire rope 12, and the other end of the steel wire rope 12 bypasses a movable pulley 11 and is fixedly connected with the launcher orientator. The launcher orientator is provided with a slide block track 13 for a slide block to slide, the slide block 9 is positioned in the slide block track 13, a movable pulley 11 is fixed on the slide block 9, and a pressure spring 10 is positioned in the slide block track 13 and is compressed and limited by the slide block 9.
The socket on the rocket is vertically butted with the plug on the plug shell 1, the plug shell 1 is driven to horizontally move when the rocket is ignited, meanwhile, under the action of the tension spring 5, the rotating arm 3 drives the plug shell 1 to rotate around the rotating arm shaft 4, and the plug is separated from the socket on the rocket. When the plug falls off, the rotating arm 3 drives the shifting fork 8 to rotate through the traction rope 16, the limit of the gas cover plate 17 is relieved, and the pressure spring 10 pushes the sliding block 9 to horizontally move along the sliding block track 13 to drive the gas cover plate 17 to horizontally move until the plug on the plug shell 1 is covered. By reasonably designing the structural parameters of the pressure spring 10, the gas cover plate 17 can quickly cover the working area of the electric connector on the launcher orientator in an effective stroke, and the rocket tail flame is prevented from ablating the plug of the electric connector.
During specific application, according to the conditions of the position of an actual rocket disengaging center, the size of an electric connector and the like, the length of the rotating arm 3 and the length of the tension spring 5 of the disengaging device are adjusted in an adjustable range by matching with the installation space of the launcher orientation device, the installation mode is optimized, and each part is reasonably assembled. Firstly, a pressure spring 10 and a sliding block 9 are installed in a sliding block track 13, and a movable pulley 11 is installed and fixed on the sliding block 9. Then, the boom support 6 is mounted on the base 7, and the boom 3 is mounted on the boom support 6 through the boom shaft 4. Then, the plug shell 1 is hinged on the upper part of the rotating arm 3 by two rotating shaft screws 2 and is connected with a tension spring 5. Finally, the steel wire rope 12 is wound around the movable pulley 11 and connected to the gas cover plate 17.
Because the socket on the rocket and the plug on the plug shell 1 are vertically connected, namely the connection line after the butt joint of the plug and the socket is vertical to the axis of the rocket cabin body, after the rocket is loaded in place through the rocket support leg track 15, the rotating arm 3 is pulled to be in a vertical state, and the socket and the plug of the electric connector are in butt joint. The shifting fork 8 is fixedly arranged on the rotating arm shaft 4, the shifting fork 8 and the rotating arm shaft 4 are connected into a whole through threads, and then a traction rope 16 between the rotating arm 3 and the shifting fork 8 is connected. The length of the pressure spring 10 is adjusted, so that the shifting fork 8 can limit the gas cover plate 17.
When the rocket electric system works, the electric plug is utilized to firstly complete the detection of the whole rocket electric system. When the rocket is ignited and moves, the plug shell 1 is driven to horizontally move along the rocket leg rail 15, and meanwhile, the rotating arm 3 is under the action of the pulling force of the pull spring 5 of the shedding device, so that the rotating arm 3 rotates around the rotating arm shaft 4 and completes the shedding action of the plug by matching with the kidney-shaped hole on the rotating arm 3. For reliable detachment, the plug housing 1 can be rotated about the spindle screw 2; when the plug falls off, the rotating arm 3 drives the rotating arm shaft 4 and the shifting fork 8 to rotate together through the traction rope 16, and the rotating arm 3 and the rotating arm support 6 can move relatively through the kidney-shaped hole, so that the gas cover plate 17 is unlocked. At the moment, the sliding block 9 is quickly pushed to move horizontally along the sliding block track 13 by the pressure spring 10, and finally the gas cover plate 17 moves horizontally along the cover plate track 14 through the steel wire rope 12 and the movable pulley 11. The working area of the electric connector and the shedding mechanism on the launcher orientator is quickly covered in an effective stroke, and the electric connector and the mechanism are effectively prevented from being ablated by rocket tail flame.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. A rocket launching electric connector quick falling device is characterized by comprising a plug shell, a rotating arm shaft, a rotating arm bracket, a base, a tension spring, a traction rope, a shifting fork, a gas cover plate and a pressure spring linkage mechanism;
the plug shell is used for fixing a plug of an external electric connector, the plug shell is hinged with the rotating arm, the rotating arm is movably connected with the rotating arm support through a rotating arm shaft, the rotating arm support is fixed on the base, one end of the tension spring is fixedly connected with the rotating arm, and the other end of the tension spring is fixedly connected with the base; one end of the shifting fork is fixedly connected with the rotating arm shaft, the other end of the shifting fork props against the gas cover plate for limiting, and meanwhile, the middle part of the shifting fork is connected with the rotating arm through a traction rope;
when the rocket is ignited, the plug shell is driven to move horizontally, the rotating arm drives the plug shell to rotate around the rotating arm shaft under the action of the tension spring, a plug of an external electric connector is separated from a socket on the rocket, meanwhile, the rotating arm drives the shifting fork to rotate through the traction rope, the limit of the gas cover plate is relieved, and the pressure spring linkage mechanism provides power for the gas cover plate to enable the gas cover plate to cover the plug on the plug shell;
the pressure spring linkage mechanism comprises a pressure spring, a sliding block, a movable pulley and a steel wire rope; one end of the steel wire rope is fixedly connected with the gas cover plate, the other end of the steel wire rope rounds a movable pulley and is fixedly connected with an external rocket direction finder, the movable pulley is fixed on a sliding block, and the pressure spring is compressed and limited by the sliding block.
2. A rocket launch electrical connector quick release device as recited in claim 1, wherein said pivoted arm is provided with a kidney-shaped hole, and a pivoted arm shaft in said kidney-shaped hole is capable of sliding relative to said kidney-shaped hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910005271.9A CN109696082B (en) | 2019-01-03 | 2019-01-03 | Rocket launching electric connector quick falling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910005271.9A CN109696082B (en) | 2019-01-03 | 2019-01-03 | Rocket launching electric connector quick falling device |
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| Publication Number | Publication Date |
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| CN109696082A CN109696082A (en) | 2019-04-30 |
| CN109696082B true CN109696082B (en) | 2021-03-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910005271.9A Active CN109696082B (en) | 2019-01-03 | 2019-01-03 | Rocket launching electric connector quick falling device |
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| CN110386268B (en) * | 2019-07-04 | 2020-09-15 | 蓝箭航天空间科技股份有限公司 | Drop-out containment system for launch vehicle launch connectors |
| CN110635309A (en) * | 2019-08-20 | 2019-12-31 | 西安航天动力技术研究所 | Guide rail type retractable separating mechanism |
| CN112762762B (en) * | 2020-12-23 | 2022-10-04 | 中国船舶重工集团有限公司第七一0研究所 | Autonomous type firing line shearing device |
| CN112758352B (en) * | 2020-12-29 | 2022-05-24 | 北京中科宇航技术有限公司 | Auxiliary pulling device for rocket launcher |
| CN112774060B (en) * | 2021-02-05 | 2022-12-02 | 魏晶晶 | High-rise building unmanned aerial vehicle fire extinguishing systems |
| CN114459285B (en) * | 2021-03-22 | 2023-05-30 | 北京天兵科技有限公司 | Pulling-out device for recyclable rocket and installation method |
| CN113745906B (en) * | 2021-08-24 | 2023-11-17 | 上海机电工程研究所 | Axial falling-off separating structure of box spring electric connector |
| CN114156694B (en) * | 2021-10-29 | 2023-08-01 | 北京宇航系统工程研究所 | Design method for arrow ground interface of electrical system for improving fault tolerance |
| CN114678729B (en) * | 2022-03-07 | 2023-11-17 | 上海机电工程研究所 | Missile cross double-shifting plate type electric plug falling mechanism |
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| US6193535B1 (en) * | 2000-02-10 | 2001-02-27 | G&H Technology, Inc. | Connector assembly with extreme temperature protective ceramic deadface |
| CN101820127A (en) * | 2009-11-23 | 2010-09-01 | 泰兴市航联电连接器有限公司 | Separation-type switching control electric connector |
| CN203339403U (en) * | 2013-05-15 | 2013-12-11 | 中航光电科技股份有限公司 | Separating fall-off type electric connector assembly |
| CN104064933A (en) * | 2014-05-30 | 2014-09-24 | 航天东方红卫星有限公司 | Recycling and fixing mechanism for pull-off plug outside satellite |
| CN105129105A (en) * | 2015-09-02 | 2015-12-09 | 北京航天发射技术研究所 | Disengagement recycling mechanism |
| CN109088225A (en) * | 2018-07-26 | 2018-12-25 | 泰兴市创航电连接器有限公司 | Unexplosive electric connector |
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2019
- 2019-01-03 CN CN201910005271.9A patent/CN109696082B/en active Active
Patent Citations (6)
| 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 |
| CN101820127A (en) * | 2009-11-23 | 2010-09-01 | 泰兴市航联电连接器有限公司 | Separation-type switching control electric connector |
| CN203339403U (en) * | 2013-05-15 | 2013-12-11 | 中航光电科技股份有限公司 | Separating fall-off type electric connector assembly |
| CN104064933A (en) * | 2014-05-30 | 2014-09-24 | 航天东方红卫星有限公司 | Recycling and fixing mechanism for pull-off plug outside satellite |
| CN105129105A (en) * | 2015-09-02 | 2015-12-09 | 北京航天发射技术研究所 | Disengagement recycling mechanism |
| CN109088225A (en) * | 2018-07-26 | 2018-12-25 | 泰兴市创航电连接器有限公司 | Unexplosive electric connector |
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| Publication number | Publication date |
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| CN109696082A (en) | 2019-04-30 |
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