CN113959257A - Missile individual soldier launching tube - Google Patents
Missile individual soldier launching tube Download PDFInfo
- Publication number
- CN113959257A CN113959257A CN202111211905.XA CN202111211905A CN113959257A CN 113959257 A CN113959257 A CN 113959257A CN 202111211905 A CN202111211905 A CN 202111211905A CN 113959257 A CN113959257 A CN 113959257A
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- Prior art keywords
- missile
- plug
- launching
- barrel
- barrel body
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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
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
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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
- 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
- H01R13/639—Additional means for holding or locking coupling parts together, after engagement, e.g. separate keylock, retainer strap
Abstract
The invention discloses a missile individual soldier launching tube which comprises a tube body with a launching through cavity, wherein a shedding plug used for being electrically connected with a matching connector on a missile, a plug-in connector used for being electrically connected with a socket on launching control equipment and a detachable connecting assembly used for being connected with the launching control equipment are arranged on the tube body, the shedding plug is electrically connected with the plug-in connector, a window is formed in the tube wall of the tube body, the shedding plug is arranged in the window in a mode of being capable of moving between a first position and a second position through a movable connecting mechanism, the shedding plug is located in the launching through cavity when in the first position, the shedding plug is located outside the launching through cavity when in the second position, and an elastic mechanism used for forcing the shedding plug to move to the second position is further arranged on the tube body. The missile individual-soldier launching canister has the advantages of simple and convenient installation of the missile, capability of preventing the missile from being damaged, high missile launching quality, high stability and reliability and the like.
Description
Technical Field
The invention relates to the technical field of missile launching equipment, in particular to a missile individual soldier launching canister.
Background
In order to meet the requirements of storage, transportation and individual launching of novel anti-armored universal missiles, an individual launching tube integrating storage, transportation and launching needs to be designed. Under the condition of meeting the storage and transportation functions, the individual soldier launching tube has the characteristics that the individual soldier is portable when carried, the individual soldier launching tube can be rapidly assembled with individual soldier launching control equipment by a single person, the centers of gravity of the individual person and the individual soldier launching control equipment and the individual soldier launching tube are stable, and the individual person can conveniently resist launching; in the launching process, the individual launching tube meets the requirements that the rear end cover is pressed and broken, the fuel gas is decompressed and sprayed out, a shooter is not unstable under the action of recoil force, the health is not affected, the structure of the launching tube is not damaged, and the like.
The individual launch canister needs to be provided with two sets of joint mechanisms which are respectively used for connecting the launch control equipment and the guided missile, the two sets of joint mechanisms are connected through a lead so as to realize the electrical connection between the launch control equipment and the guided missile, and meanwhile, the individual launch canister needs to be provided with a detachable connecting component which is used for being connected with the launch control equipment. The joint mechanism for connecting the missile in the existing individual missile launcher is characterized in that a falling plug capable of moving along the radial direction of a barrel body is arranged on the barrel body of the individual missile launcher, and the falling plug is pressed radially towards the interior of the barrel body after the missile is loaded into the barrel body, so that the falling plug is spliced with a matching joint on the missile. Meanwhile, the falling plug and the matching joint are mutually inserted along the radial direction of the barrel, the falling plug and the matching joint are not easy to fall off in the missile launching process, safety risks are easy to cause, and the pins of the plug are easy to damage. In addition, the detachable connecting component for connecting the existing individual transmitting tube with the transmitting and controlling equipment has the defects of complex structure, inconvenient control and low connection stability and reliability.
Disclosure of Invention
The invention aims to solve the technical problem of overcoming the defects in the prior art and provides a missile individual launching tube which is simple and convenient to install, can prevent the missile from being damaged, and has high missile launching quality, stability and reliability.
In order to solve the technical problems, the invention adopts the following technical scheme:
a missile individual soldier launching barrel comprises a barrel body with a launching through cavity, wherein a falling plug, a plug-in connector and a detachable connection assembly are mounted on the barrel body, the falling plug is used for being electrically connected with a matching connector on a missile, the plug-in connector is used for being electrically connected with a socket on launching control equipment, the detachable connection assembly is used for being connected with the launching control equipment, the falling plug is electrically connected with the plug-in connector, a window is formed in the barrel wall of the barrel body, the falling plug is mounted in the window in a mode of being capable of moving between a first position and a second position through a movable connection mechanism, the falling plug is located in the launching through cavity when in the first position, the falling plug is located outside the launching through cavity when in the second position, and an elastic mechanism used for forcing the falling plug to move to the second position is further mounted on the barrel body.
As a further improvement of the above technical solution:
the falling plug can be inserted into the matching joint on the guided missile moving along the opposite ejection direction in the cylinder body and can be separated from the matching joint on the guided missile moving along the ejection direction in the cylinder body when being positioned at the first position.
The movable connecting mechanism comprises a swinging piece, the swinging piece is hinged on the cylinder body, and the falling plug is arranged on the swinging piece and moves between a first position and a second position through the swinging movement of the swinging piece.
The elastic mechanism comprises a torsion spring arranged between the cylinder body and the swinging piece.
And a sealing cover for sealing the window is detachably arranged on the cylinder body.
A window frame is detachably mounted in the window, and the swinging piece is hinged to the window frame.
The barrel is of a square tubular structure made of carbon fiber, a wire passing groove and an ignition wire groove are formed in the outer wall of the barrel, the falling plug is electrically connected with the plug connector through a wire penetrating the wire passing groove, the ignition wire groove extends from the window to the rear end of the barrel and is used for enabling an ignition wire to be wired, a carbon fiber cloth layer is wound outside the barrel and covers and hides the wire passing groove and the wire; the missile launching device is characterized in that an openable front end cover is installed at the front end of the barrel for missile launching, and an openable rear end cover made of breakable material is installed at the rear end of the barrel for missile loading.
More than one blocking piece for preventing the missile launching engine from falling off the barrel when the missile is launched is arranged at the position, close to the front end for launching the missile, of the barrel, and the blocking piece is arranged in a mounting hole formed in the barrel wall in a penetrating mode and partially extends into the launching through cavity.
The detachable connection assembly comprises a hanging rod for hanging a fixed hook, a positioning hole for inserting a bolt and a locking hook for hanging the locking hook in a matching manner with a rotating hook, the hanging rod, the positioning hole and the locking hook are sequentially arranged on the barrel at intervals along the axial direction of the barrel, and the plug-in connector is used for being positioned between the hanging rod and the locking hook and matching with the micro-motion separation socket.
The hanging connecting rod, the positioning hole and the locking hook are arranged on a base, and the base is detachably arranged on the barrel.
Compared with the prior art, the invention has the advantages that:
in the missile individual soldier launching tube, the falling plug is arranged in the window in a mode of moving between the first position and the second position through the movable connecting mechanism, the falling plug is positioned in the launching through cavity when in the first position, the falling plug is positioned outside the launching through cavity when in the second position, the tube body is also provided with an elastic mechanism for forcing the falling plug to move to the second position, when a missile is not installed in the launching through cavity of the tube body, the falling plug is kept at the second position outside the launching through cavity under the action of the elastic mechanism, after the missile is installed in the launching through cavity, the falling plug is manually forced to move to the first position under the action of the elastic mechanism, the falling plug can extend into the launching through cavity to be connected with a matching joint on the missile, and the installation of the missile is simple and convenient. In the missile launching process, after the matched joint moves along with the missile and is separated from the drop plug, the drop plug can move to a second position outside the launching through cavity under the action of the elastic mechanism, and the drop plug cannot be in contact with the missile in the launching through cavity, so that the normal launching of the missile can be avoided, the damage to the missile is prevented, and the missile launching quality is ensured, and the missile launching quality is stable and reliable.
Drawings
Fig. 1 is a schematic perspective view of a missile individual launch canister.
FIG. 2 is a schematic perspective view of a missile individual launch canister with a closure cap removed.
Fig. 3 is an enlarged partial schematic view of the removable connection assembly and the drop plug at an installed position.
FIG. 4 is a schematic perspective view of a missile individual launch canister with the closure cap and the front end cap removed.
Fig. 5 is a schematic view of the structure of the missile individual-soldier launch canister.
FIG. 6 is a schematic top view of a missile individual launch canister.
Illustration of the drawings:
1. a barrel; 10. a launch through cavity; 11. a window; 12. a closure cap; 13. a window frame; 14. a front end cover; 15. a rear end cover made of a breakable disintegrator material; 16. a blocking member; 17. a wire passing groove; 18. an ignition wire groove; 2. the plug is dropped; 3. a plug-in connector; 4. a detachable connection assembly; 41. hanging a connecting rod; 42. positioning holes; 43. locking the hook; 44. a base; 5. an oscillating member.
Detailed Description
The invention is described in further detail below with reference to the figures and specific examples.
As shown in fig. 1 to 6, the missile individual soldier launching canister of the embodiment includes a canister body 1 having a launching through cavity 10, a drop plug 2 for electrically connecting with a mating connector on a missile, a plug connector 3 for electrically connecting with a socket on a launch control device, and a detachable connection assembly 4 for connecting the launch control device are installed on the canister body 1, the drop plug 2 is electrically connected with the plug connector 3, a window 11 is opened on a canister wall of the canister body 1, the drop plug 2 is installed in the window 11 in a manner of being capable of moving between a first position and a second position through a movable connection mechanism, the drop plug 2 is located in the launching through cavity 10 when in the first position, the drop plug 2 is located outside the launching through cavity 10 when in the second position, and an elastic mechanism for forcing the drop plug 2 to move to the second position is further installed on the canister body 1.
In the missile individual-soldier launching barrel, the falling plug 2 is arranged in the window 11 in a mode of moving between a first position and a second position through the movable connecting mechanism, the falling plug 2 is positioned in the launching through cavity 10 when in the first position, the falling plug 2 is positioned outside the launching through cavity 10 when in the second position, the barrel 1 is also provided with an elastic mechanism for forcing the falling plug 2 to move towards the second position, when a missile is not installed in the launching through cavity 10 of the barrel 1, the falling plug 2 is kept at the second position outside the launching through cavity 10 under the action of the elastic mechanism, after the missile is installed in the launching through cavity 10, the falling plug 2 is manually forced to move towards the first position under the action of the elastic mechanism, the falling plug 2 can extend into the launching through cavity 10 to be connected with a matching joint on the missile, and the installation of the missile is simple and convenient. In the missile launching process, after the matched joint moves along with the missile and is separated from the falling plug 2, the falling plug 2 can move to a second position outside the launching through cavity 10 under the action of the elastic mechanism, and the falling plug 2 cannot be in contact with the missile in the launching through cavity 10, so that the normal launching of the missile can be avoided, the damage to the missile is prevented, and the missile launching quality and stability and reliability are ensured.
In this embodiment, the release plug 2 can be plugged into the mating connector of the missile moving in the opposite shooting direction in the barrel 1 and can be disengaged from the mating connector of the missile moving in the shooting direction in the barrel 1 at the first position. That is, by configuring the angle of the release plug 2 at the first position and the angle of the mating connector on the missile, when the missile loaded into the launching through cavity 10 moves in the opposite launching direction, the mating connector can be just plugged with the release plug 2 at the first position, and when the missile launches, the missile can drive the mating connector to be separated from the release plug 2 at the first position. Therefore, after the guided missile is installed into the launching through cavity 10 during guided missile installation, the drop-off plug 2 is manually forced to move to the first position in the launching through cavity 10, and then the guided missile in the launching through cavity 10 is pushed to move in the opposite launching direction, so that the matching connection between the matching joint and the drop-off plug 2 can be realized, and the guided missile is more convenient and faster to install and assemble. When the missile is launched, the direction in which the missile drives the matching joint to move and the falling plug 2 is the direction in which the matching joint and the falling plug 2 are mutually inserted, so that the matching joint and the falling plug 2 are easily and smoothly separated, the stability and the reliability of the separation action are ensured, and the safety risk that the separation is not timely and cannot be carried out is avoided. Moreover, the mutual inserting direction of the matching connector and the falling plug 2 is consistent with the launching direction of the missile, and the inserting structure between the matching connector and the falling plug 2 is not easy to deform and damage in the separation process.
In this embodiment, as shown in fig. 3, the movable connection mechanism includes a swinging member 5, the swinging member 5 is hingedly mounted on the cylinder 1, and the drop plug 2 is mounted on the swinging member 5 and moves between the first position and the second position by the swinging movement of the swinging member 5. The movable connecting mechanism has the advantages of simple and compact structure, low cost, easy manufacture and assembly, and stable and reliable work. Preferably, the swinging piece 5 comprises two swinging rods which are coaxially hinged, the falling plug 2 is installed between the two swinging rods, the structure is simple, the compactness is better, and the falling plug 2 is convenient to install and has good stability. In other embodiments, the movable connection mechanism may also be in the form of a sliding mechanism, etc., as long as it can allow the breakaway plug 2 to enter and exit the launch through cavity 10.
In this embodiment, the elastic mechanism includes the torsional spring of installing between barrel 1 and swinging member 5, and the torsional spring direct mount is in the articulated department of barrel 1 and swinging member 5, and its simple structure is compact, with low costs, job stabilization is reliable.
In the embodiment, as shown in fig. 1, a sealing cover 12 for sealing the window 11 is detachably mounted on the cylinder 1, and on one hand, the sealing cover 12 can prevent high-temperature gas generated during missile launching from being discharged from the window 11, so that safety is ensured; on the other hand, when the falling plug 2 is ejected out of the launching through cavity 10 under the action of the elastic mechanism, the falling plug can be prevented from being ejected out to a launcher. Preferably, a sealing strip is arranged between the closing cover 12 and the barrel 1.
In this embodiment, as shown in fig. 3, a window frame 13 is detachably mounted in the window opening 11, and the swinging member 5 is hingedly mounted on the window frame 13. During manufacturing and assembling, the swinging piece 5 can be installed on the window frame 13 in a hinged mode, then the window frame 13 is assembled on the cylinder body 1, and the swinging piece 5 can be installed, so that the swinging piece 5 is installed more conveniently. Preferably, the window frame 13 is mounted on the cylinder 1 by screws or bolts, and the closing cover 12 is mounted on the window frame 13 by screws or bolts.
In this embodiment, as shown in fig. 1 to 5, the barrel 1 is a square tubular structure made of carbon fiber, a line passing groove 17 and an ignition line groove 18 are arranged on the outer wall of the barrel 1, the shedding plug 2 is electrically connected with the plug connector 3 through a wire penetrating through the line passing groove 17, the ignition line groove 18 extends from the window 11 to the rear end of the barrel 1 for the ignition line to run, a carbon fiber cloth layer is wound around the outside of the barrel 1, and the carbon fiber cloth layer covers and hides the line passing groove 17 and the wire; the front end of the cylinder 1 for the missile to be ejected is provided with an openable front end cover 14, and the rear end of the cylinder 1 for the missile to be loaded is provided with an openable rear end cover 15 made of breakable material. Preferably, the front end cover 14 is hinged to the barrel 1 in a manner that the front end cover can be turned over and opened towards one side of the front end of the barrel 1, and is clamped and fixed by a clamping mechanism when the front end cover 14 closes the front end. The cylinder body 1 has the advantages of light weight, high structural strength and portability, the structural strength is enough to bear the fuel gas effect of a launching engine, the inner surface of the cylinder body 1 is smooth, no clamping stagnation exists between the missile entering cylinder assembly and the launching process, the cylinder body 1 adopts a square cylinder design, and the cylinder body can be effectively used for storing, transporting and launching the missile which is in a square structure after a steering engine and a tail wing are folded on the basis of ensuring the structural strength, and is wide in application range. Meanwhile, the wiring mode that the groove is used for embedding wires and the carbon fiber cloth layer is used for coating and hiding is adopted, so that the wire has the advantages of simple circuit, neat appearance, reliable wiring and the like; the rear end cover 15 made of the breakable disintegrating material is designed to be a breakable cover, so that the rear end cover 15 made of the breakable disintegrating material can be broken and disintegrated under the action of gas pressure sprayed by the launching engine.
In this embodiment, preferably, the barrel 1 is further provided with a shoulder pad made of hard foam material, and the center of gravity of the barrel bullet is arranged in front of the shoulder of the shooter, so that the requirement of shoulder-carried launch stability can be met.
In the present embodiment, as shown in fig. 4 and 6, more than one blocking piece 16 for preventing the missile launching engine from falling off the barrel 1 when the missile is launched is arranged at the position of the barrel 1 close to the front end for launching the missile, and the blocking piece 16 is arranged in the mounting hole arranged on the barrel wall of the barrel 1 in a penetrating way and partially extends into the launching through cavity 10. The installation form of the blocking member 16 has the advantages of simple structure, easy manufacture and assembly and low cost. Preferably, the stops 16 are provided in two sets, the two sets being arranged symmetrically with respect to the axial direction of the cartridge 1.
In this embodiment, as shown in fig. 1 to 4 and fig. 6, the detachable connection assembly 4 includes a hooking rod 41 for hooking a fixed hook, a positioning hole 42 for inserting a plug pin, and a locking hook 43 for hooking a rotating hook, the hooking rod 41, the positioning hole 42, and the locking hook 43 are sequentially disposed on the barrel 1 at intervals along the axial direction of the barrel 1, the plug connector 3 is a connector located between the hooking rod 41 and the locking hook 43 and used for matching and butting with the micro-motion separation socket, the plug connector 3 and the micro-motion separation socket have a micro-motion characteristic in cooperation, and the plug connector 3 and the micro-motion separation socket are favorably butted quickly and smoothly. This kind of can dismantle coupling assembling 4 when being connected with the accuse equipment, through set up fixed couple, bolt, rotation couple and fine motion separation socket on the accuse equipment, wherein, fixed couple can articulate on the head rod 41 and can rotate around the head rod 41, the bolt can be when fixed couple rotates around the head rod 41 insert the locating hole 42 in restriction accuse equipment and barrel 1 relative displacement on perpendicular to barrel 1 axial direction, it is preferred, locating hole 42 is equipped with two altogether, cooperate with two bolts respectively. The rotating hook is used for being connected with the locking hook 43 in a hanging mode and matching with the hanging effect of the fixed hook and the hanging rod 41 to lock and attach the launch control equipment and the barrel body 1 mutually, the rotating hook can be rotatably arranged and provided with a torsional spring (similar to an elastic buckle), and automatic hanging with the locking hook 43 can be achieved. The micro-motion separation socket is matched and butted with the plug connector 3 in the hanging process of the rotating hook and the locking hook 43, so that the connection fixation and the electrical connection between the launch control equipment and the barrel body 1 can be realized. Therefore, the detachable connection assembly 4 is adopted, the corresponding matching mechanism is arranged on the sending control equipment in a matching mode, accurate and quick connection of the sending control equipment and the barrel body 1 can be achieved, the structure is simple and compact, the mechanical strength is high, the processing and assembly are convenient, the connection operation is simple and convenient, and the butt joint precision of the sending control equipment and the barrel body 1 is easy to guarantee.
In this embodiment, the hooking rod 41, the positioning hole 42 and the locking hook 43 are provided on a base 44, and the base 44 is detachably mounted on the cylinder 1. The base 44, the hanging rod 41, the positioning hole 42 and the locking hook 43 can be manufactured separately and then installed on the barrel 1, so that the processing, manufacturing and maintenance are facilitated. Preferably, a sinking groove is formed in the outer wall of the cylinder 1, and the base 44 is accommodated and positioned in the sinking groove, so that the base 44 can be conveniently installed and positioned, and the stability after installation is improved; the hanging rod 41, the positioning hole 42 and the locking hook 43 are connected with the base 44 to form reinforcing ribs, so that the structural strength can be improved. The base 44 is preferably mounted to the barrel 1 by screws or bolts.
When the missile individual soldier launching canister is loaded into a missile, cabin sections such as a missile (without a launching engine) guide head and the like are matched with an adapter of the missile to enter the canister from the rear end of a canister body 1 section by section, the front part of the guide head adapter is pushed out from the front end of the canister body 1, then a swinging piece 5 is pressed to enable a falling plug 2 to move to a first position in a launching through cavity 10, the falling plug 2 is aligned with a plug on the missile, meanwhile, the thumb is used for pushing the guide head adapter to move towards the rear end, a matching joint of the missile is butted with the falling plug 2, the electrical connection of the missile and the launching canister is completed, and the structural positioning is realized. The closure cap 12 (including the sealing strip) is then fitted over the window frame 13 for sealing. And then assembling the launching engine and the adapter thereof from the rear end of the barrel body 1, installing a rear end cover 15 made of easily-broken and disintegrated materials after the launching engine enters the barrel, and closing the front end cover 14 to finish missile assembly.
When the launch control equipment is assembled with the individual soldier launch canister, the canister body 1 is reversely arranged on the right side of the shooter, the shooter holds the launch control equipment handle by two hands, the launch control equipment is inverted by bending over, the fixed hook on the launch control equipment is hooked with the hooking rod 41 of the detachable connecting component 4, the launcher holds the launch control equipment handle by two hands and presses downwards, the bolt on the launch control equipment is inserted into the positioning hole 42 of the detachable connecting component 4, the left-right positioning effect is achieved, the floating plug opening of the micro-motion separation socket on the launch control equipment is sleeved into the plug-in connector 3 of the detachable connecting component 4, the micro-motion separation socket is butted with the plug-in connector 3, and the electrical connection of the launch control equipment and the canister body 1 is achieved. Meanwhile, a rotating hook on the launch control equipment is clamped with a locking hook 43 of the detachable connecting component 4, and the mechanical and electrical connection between the individual launch control equipment and the barrel 1 is realized.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-described embodiments. Modifications and variations that may occur to those skilled in the art without departing from the spirit and scope of the invention are to be considered as within the scope of the invention.
Claims (10)
1. The utility model provides a guided missile individual soldier launch canister, passes through barrel (1) of chamber (10) including having the transmission, install on barrel (1) be used for with the guided missile on the cooperation connect electrical connection drop plug (2), be used for with launch the socket electrical connection on the accuse equipment plug connector (3) and be used for connecting the removable connection subassembly (4) of launching the accuse equipment, drop plug (2) and plug connector (3) electrical connection, its characterized in that: the novel anti-dropping device is characterized in that a window (11) is formed in the wall of the barrel body (1), the dropping plug (2) is installed in the window (11) in a mode of moving between a first position and a second position through a movable connecting mechanism, the dropping plug (2) is located in the emission through cavity (10) when in the first position, the dropping plug (2) is located outside the emission through cavity (10) when in the second position, and an elastic mechanism used for forcing the dropping plug (2) to move towards the second position is further installed on the barrel body (1).
2. The missile individual soldier launch canister of claim 1, wherein: the falling plug (2) can be inserted into a matching joint on a guided missile moving along the shooting direction in the barrel body (1) and can be separated from a matching joint on a guided missile moving along the shooting direction in the barrel body (1) when in the first position.
3. The missile individual soldier launch canister of claim 1, wherein: the movable connecting mechanism comprises a swinging piece (5), the swinging piece (5) is hinged to the cylinder body (1), and the falling plug (2) is installed on the swinging piece (5) and moves between a first position and a second position through the swinging movement of the swinging piece (5).
4. The missile individual soldier launch canister of claim 3, wherein: the elastic mechanism comprises a torsion spring arranged between the cylinder body (1) and the swinging piece (5).
5. The missile individual soldier launch canister of claim 2, wherein: the cylinder body (1) is detachably provided with a sealing cover (12) for sealing the window (11).
6. The missile individual soldier launch canister of claim 4, wherein: a window frame (13) is detachably mounted in the window opening (11), and the swinging piece (5) is hinged on the window frame (13).
7. The missile individual soldier launch canister of claim 1, wherein: the ignition plug is characterized in that the barrel body (1) is of a square tubular structure made of carbon fiber, a line passing groove (17) and an ignition line groove (18) are formed in the outer wall of the barrel body (1), the falling plug (2) is electrically connected with the plug connector (3) through a wire penetrating through the line passing groove (17), the ignition line groove (18) extends from the window (11) to the rear end of the barrel body (1) and is used for enabling an ignition line to be wired, a carbon fiber cloth layer is wound outside the barrel body (1), and the line passing groove (17) and the wire are covered and hidden by the carbon fiber cloth layer; the missile launching device is characterized in that an openable front end cover (14) is mounted at the front end of the barrel (1) for missile launching, and an openable rear end cover (15) made of easily-broken disintegrating material is mounted at the rear end of the barrel (1) for missile loading.
8. The missile individual soldier launch canister of claim 1, wherein: more than one blocking piece (16) used for preventing a missile launching engine from falling off the barrel body (1) when the missile is launched is arranged at the position, close to the front end for the missile launching, of the barrel body (1), and the blocking pieces (16) are arranged in mounting holes formed in the barrel wall of the barrel body (1) in a penetrating mode and partially extend into the launching through cavity (10).
9. The missile individual soldier launch canister as claimed in any one of claims 1 to 8, wherein: detachable connecting subassembly (4) including be used for supplying fixed couple articulate hanging rod (41), be used for supplying bolt male locating hole (42) and be used for articulating complex locking couple (43) with rotating the couple, it connects pole (41), locating hole (42) and locking couple (43) to set up on barrel (1) along barrel (1) axial interval in proper order, plug connector (3) are for being located hang and are used for the joint that matches the butt joint with fine motion separation socket between pole (41) and locking couple (43).
10. The missile individual launcher of claim 9, wherein: the hanging and connecting rod (41), the positioning hole (42) and the locking hook (43) are arranged on a base (44), and the base (44) is detachably arranged on the barrel body (1).
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| CN202111211905.XA CN113959257A (en) | 2021-10-18 | 2021-10-18 | Missile individual soldier launching tube |
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|---|---|---|---|
| CN202111211905.XA CN113959257A (en) | 2021-10-18 | 2021-10-18 | Missile individual soldier launching tube |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2243479C2 (en) * | 2003-01-20 | 2004-12-27 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Portable antitank rocket complex and method for installation of container with rocket on luncher |
| CN102290673A (en) * | 2011-06-15 | 2011-12-21 | 北京机械设备研究所 | Obliquely-pulling plug dropping device |
| CN105953646A (en) * | 2016-04-29 | 2016-09-21 | 上海机电工程研究所 | Electric plug plug-in and pulling mechanism rebound prevention device for firing box |
| CN108134262A (en) * | 2018-01-17 | 2018-06-08 | 河南天海电器有限公司 | A kind of New connector position ensures the adapter assembly of CPA device |
| CN108521051A (en) * | 2018-06-15 | 2018-09-11 | 四川永贵科技有限公司 | A kind of secondary locking and the unlocking structure that is delayed |
| 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 |
| CN112747633A (en) * | 2020-12-24 | 2021-05-04 | 彩虹无人机科技有限公司 | Plug-pull mechanism movement interference determination method |
| CN113237395A (en) * | 2021-04-26 | 2021-08-10 | 上海机电工程研究所 | Bullet fixing device based on lever mechanism |
-
2021
- 2021-10-18 CN CN202111211905.XA patent/CN113959257A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2243479C2 (en) * | 2003-01-20 | 2004-12-27 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Portable antitank rocket complex and method for installation of container with rocket on luncher |
| CN102290673A (en) * | 2011-06-15 | 2011-12-21 | 北京机械设备研究所 | Obliquely-pulling plug dropping device |
| CN105953646A (en) * | 2016-04-29 | 2016-09-21 | 上海机电工程研究所 | Electric plug plug-in and pulling mechanism rebound prevention device for firing box |
| CN108134262A (en) * | 2018-01-17 | 2018-06-08 | 河南天海电器有限公司 | A kind of New connector position ensures the adapter assembly of CPA device |
| CN108521051A (en) * | 2018-06-15 | 2018-09-11 | 四川永贵科技有限公司 | A kind of secondary locking and the unlocking structure that is delayed |
| 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 |
| CN112747633A (en) * | 2020-12-24 | 2021-05-04 | 彩虹无人机科技有限公司 | Plug-pull mechanism movement interference determination method |
| CN113237395A (en) * | 2021-04-26 | 2021-08-10 | 上海机电工程研究所 | Bullet fixing device based on lever mechanism |
Non-Patent Citations (4)
| Title |
|---|
| 祁载康等: "《制导弹药技术》", 31 December 2002, 北京理工大学出版社, pages: 351 - 352 * |
| 秦延景: "低空飞机杀手:红缨-5单兵导弹", 《轻武器》 * |
| 秦延景: "低空飞机杀手:红缨-5单兵导弹", 《轻武器》, no. 17, 31 August 2012 (2012-08-31), pages 10 - 13 * |
| 秦延景: "低空飞机杀手:红缨-5单兵导弹", 轻武器, no. 2012, pages 10 - 13 * |
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