CN211996150U - Empty bullet device and projectile body carrier - Google Patents
Empty bullet device and projectile body carrier Download PDFInfo
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- CN211996150U CN211996150U CN201922440714.5U CN201922440714U CN211996150U CN 211996150 U CN211996150 U CN 211996150U CN 201922440714 U CN201922440714 U CN 201922440714U CN 211996150 U CN211996150 U CN 211996150U
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Abstract
The utility model relates to an unmanned vehicles technical field specifically provides an air-drop bullet device and projectile body carry ware, can solve the problem that the system structure of throwing is complicated among the prior art, the reliability is poor. The projectile body loader comprises an aircraft connecting seat, and a mounting structure used for being connected with an aircraft is arranged on the aircraft connecting seat; the aircraft connecting base is provided with a projectile body connecting base, the projectile body connecting base is in plug fit with the top end of a projectile body through a plug structure, a closed cavity is defined at the plug structure when the projectile body connecting base and the projectile body are in plug fit, gunpowder is filled in the closed cavity, and the gunpowder is used for generating high-pressure gas to push the projectile body out of the projectile body connecting base when burning; an ignition device for igniting gunpowder is also arranged on the projectile body loader.
Description
Technical Field
The utility model relates to an unmanned vehicles technical field, concretely relates to air-drop bullet device and projectile body carry ware.
Background
With the increasing maturity of unmanned aerial vehicle technology, technicians can accomplish specific tasks such as using tear-gas shells to disperse people, using fire extinguishing shells to perform fire extinguishing operations, etc. by loading different air bombs on the unmanned aerial vehicle such as an unmanned aerial vehicle. Patent documents with the publication number of CN105667794B and the publication date of 2017.09.26 disclose an unmanned aerial vehicle projectile shooting system, which comprises a launching tube and rocker arm pairs arranged on two sides of the launching tube, wherein clamping parts of the rocker arm pairs can stretch into the launching tube and clamp tear-gas shells in the launching tube.
In the throwing system, a shifting fork gear is arranged in the middle of the movable end of a rocker arm pair, the shifting fork gear is driven by a steering engine to rotate, a main gear is further arranged between the steering engine and the shifting fork gear, the main gear is directly in transmission connection with the gear part of the shifting fork gear, and the shifting fork part in the shifting fork gear is driven by the gear part to open the movable end of the rocker arm pair, so that the tear shells are hung off. This system of throwing bomb can carry a plurality of tear-gas shells and realize accurate input on the fuselage, but some problems also exist: the rocker arm in the throwing system needs to be driven by a shifting fork gear, and a main gear is arranged between the shifting fork gear and the steering engine, so that the whole transmission links are more, the transmission structure is complex, and the transmission reliability is poor.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a projectile body loader, which can solve the problems of complex structure and poor reliability of a projectile throwing system in the prior art; another object of the present invention is to provide an air-drop bomb device using the bomb carrier, which has a simple structure and high reliability.
In order to achieve the above object, the utility model provides a projectile body carrier adopts following technical scheme:
the projectile body loader comprises an aircraft connecting seat, and a mounting structure used for being connected with an aircraft is arranged on the aircraft connecting seat;
the aircraft connecting base is provided with a projectile body connecting base, the projectile body connecting base is in plug fit with the top end of a projectile body through a plug structure, a closed cavity is defined at the plug structure when the projectile body connecting base and the projectile body are in plug fit, gunpowder is filled in the closed cavity, and the gunpowder is used for generating high-pressure gas to push the projectile body out of the projectile body connecting base when burning;
an ignition device for igniting gunpowder is also arranged on the projectile body loader.
The beneficial effects are that: gunpowder is filled in a closed cavity between the projectile body and the projectile body connecting seat, and the ignition device arranged in the projectile body loader is matched, so that high-pressure gas generated after the gunpowder is ignited directly acts on the end part of the projectile body, and the projectile body is separated from the insertion matching with the projectile body connecting seat to realize projection. The projectile body throws the thrust that relies on is high-pressure gas, and the grafting cooperation relation between projectile body and the projectile body connecting seat also can provide the direction for the motion of projectile body, need not set up complicated transmission structure in projectile body carry ware and brings the realization projectile body and throw, simple structure, also relatively more stable, reliable.
Further, the elastomer connecting seat is in interference fit with the elastomer.
The beneficial effects are that: the projectile body and the projectile body connecting seat are in interference fit, the matching structure is simple, and the implementation is convenient.
Further, be provided with the draw-in groove on aircraft connecting seat and the projectile body connecting seat between the two, be provided with the dop on the other, aircraft connecting seat and projectile body connecting seat realize releasable connection through the joint structure of compriseing draw-in groove and dop.
The beneficial effects are that: set up to detachable connection structure between projectile body connecting seat and the aircraft connecting seat, be convenient for make, dismouting.
Furthermore, the aircraft connecting seat is provided with a plug-in convex part protruding towards the projectile body connecting seat on the end face used for being connected with the projectile body connecting seat in a clamping manner, the plug-in convex part is inserted into the plug-in cavity of the projectile body connecting seat when the projectile body connecting seat is connected with the aircraft connecting seat in a clamping manner, and the projectile body and the inner wall of the plug-in cavity are enclosed to form the closed cavity.
The beneficial effects are that: the splicing cavity of the splicing convex part inserted into the elastomer connecting seat can ensure that the elastomer connecting seat is more stable in detachable connection with the aircraft connecting seat through the splicing matching between the splicing convex part and the splicing cavity, and the sealing performance of the closed cavity can also be ensured.
Furthermore, a sealing plate is arranged at an opening at the lower part of the projectile body loader, and a sealing plate opening structure for opening the sealing plate during projectile throwing is arranged in the projectile body loader.
The beneficial effects are that: the lower opening of the projectile body loader is provided with the sealing plate, so that the projectile body can be prevented from being interfered by other factors when the aircraft moves, and the safety and the reliability of the projectile body before projectile throwing can be effectively guaranteed.
Further, a hollow cylinder is arranged in the projectile carrier, an inserting column is arranged on the sealing plate and used for being inserted into a cavity of the hollow cylinder to be connected with the projectile carrier, gunpowder used for generating high-pressure gas pushing the sealing plate away when the high-pressure gas is ignited is filled in the hollow cylinder, and the sealing plate opening structure is formed by the hollow cylinder.
The beneficial effects are that: the shrouding is opened to high-pressure gas that uses gunpowder to explode equally, can utilize the structure in the projectile carries the seat to open the shrouding, need not arrange other opening structure, and the structure is fairly simple.
In order to achieve the above object, the utility model provides an air-drop bullet device adopts following technical scheme:
the air-drop projectile device comprises a projectile body loader and a projectile body loaded in the projectile body loader;
the projectile body loader comprises an aircraft connecting seat, and a mounting structure used for being connected with an aircraft is arranged on the aircraft connecting seat;
the aircraft connecting base is provided with a projectile body connecting base, the projectile body connecting base is in plug fit with the top end of a projectile body through a plug structure, a closed cavity is defined at the plug structure when the projectile body connecting base and the projectile body are in plug fit, gunpowder is filled in the closed cavity, and the gunpowder is used for generating high-pressure gas to push the projectile body out of the projectile body connecting base when burning;
an ignition device for igniting gunpowder is also arranged on the projectile body loader.
The beneficial effects are that: gunpowder is filled in a closed cavity between the projectile body and the projectile body connecting seat, and the ignition device arranged in the projectile body loader is matched, so that high-pressure gas generated after the gunpowder is ignited directly acts on the end part of the projectile body, and the projectile body is separated from the insertion matching with the projectile body connecting seat to realize projection. The projectile body throws the thrust that relies on is high-pressure gas, and the grafting cooperation relation between projectile body and the projectile body connecting seat also can provide the direction for the motion of projectile body, need not set up complicated transmission structure in projectile body carry ware and brings the realization projectile body and throw, simple structure, also relatively more stable, reliable.
Further, the elastomer connecting seat is in interference fit with the elastomer.
The beneficial effects are that: the projectile body and the projectile body connecting seat are in interference fit, the matching structure is simple, and the implementation is convenient.
Further, be provided with the draw-in groove on aircraft connecting seat and the projectile body connecting seat between the two, be provided with the dop on the other, aircraft connecting seat and projectile body connecting seat realize releasable connection through the joint structure of compriseing draw-in groove and dop.
The beneficial effects are that: set up to detachable connection structure between projectile body connecting seat and the aircraft connecting seat, be convenient for make, dismouting.
Furthermore, the aircraft connecting seat is provided with a plug-in convex part protruding towards the projectile body connecting seat on the end face used for being connected with the projectile body connecting seat in a clamping manner, and the projectile body and the inner wall of the plug-in cavity are enclosed into the closed cavity when the plug-in convex part is inserted into the plug-in cavity of the projectile body connecting seat when the projectile body connecting seat is connected with the aircraft connecting seat in a clamping manner.
The beneficial effects are that: the splicing cavity of the splicing convex part inserted into the elastomer connecting seat can ensure that the elastomer connecting seat is more stable in detachable connection with the aircraft connecting seat through the splicing matching between the splicing convex part and the splicing cavity, and the sealing performance of the closed cavity can also be ensured.
Furthermore, a sealing plate is arranged at an opening at the lower part of the projectile body loader, and a sealing plate opening structure for opening the sealing plate during projectile throwing is arranged in the projectile body loader.
The beneficial effects are that: the lower opening of the projectile body loader is provided with the sealing plate, so that the projectile body can be prevented from being interfered by other factors when the aircraft moves, and the safety and the reliability of the projectile body before projectile throwing can be effectively guaranteed.
Further, a hollow cylinder is arranged in the projectile carrier, an inserting column is arranged on the sealing plate and used for being inserted into a cavity of the hollow cylinder to be connected with the projectile carrier, gunpowder used for generating high-pressure gas pushing the sealing plate away when the high-pressure gas is ignited is filled in the hollow cylinder, and the sealing plate opening structure is formed by the hollow cylinder.
The beneficial effects are that: the shrouding is opened to high-pressure gas that uses gunpowder to explode equally, can utilize the structure in the projectile carries the seat to open the shrouding, need not arrange other opening structure, and the structure is fairly simple.
Further, the afterbody of the projectile body is provided with the detonator that is used for igniting the projectile body, and the detonator stretches into in the projectile body connecting seat when the projectile body is pegged graft with the projectile body connecting seat and is cooperated to realize igniting the detonator when gunpowder is ignited.
The beneficial effects are that: the fuse of the projectile body is ignited by gunpowder, the projectile body explosion is controlled on the basis of the existing structure, and the structure is simpler.
Drawings
Fig. 1 is a schematic view of the hollow projectile throwing device of the present invention in cooperation with an unmanned aerial vehicle;
fig. 2 is a schematic structural view of the hollow projectile throwing device of the present invention;
FIG. 3 is a schematic view of a structure of an aircraft connection mount;
FIG. 4 is a schematic view of the structure of the projectile connecting seat;
fig. 5 is a schematic view of the connection structure between the projectile body and the projectile body connection seat of the present invention;
fig. 6 is a schematic structural view of an inner cavity in the projectile connecting seat.
In the figure: 10-unmanned aerial vehicle; 20-air-drop ammunition device; 21-a plate body; 22-a sleeve body; 23-a projectile-containing cartridge; 221-card interface; 231-a bump; 232-base plate; 233-card slot; 234-chuck; 235-a plug-in boss; 236-a hollow cylinder; 30-an elastomer; 40-elastomer plug sockets; 50-closed chamber.
Detailed Description
The present invention will be described with reference to the accompanying drawings in detail with reference to an air-drop device and a projectile carrier.
As shown in fig. 1 and fig. 2, an embodiment of the hollow projectile shooting device of the present invention is: empty device of throwing 20 includes projectile carrier and loads the tear-gas shells in projectile carrier, fixes the lower extreme at unmanned aerial vehicle 10 through the aircraft connecting seat when using, and unmanned aerial vehicle 10 and empty device of throwing 20 realize signal transmission with the operating personnel or the control station on ground through signal transceiver, can reach assigned position after unmanned aerial vehicle 10 with the tear-gas shells of dress in projectile carrier put in appointed place. The unmanned aerial vehicle 10 in this embodiment is any unmanned aerial vehicle in the prior art that can drive the air-dropping device 20 to act, and therefore the following embodiments mainly focus on the structure and the function of the air-dropping device 20.
As shown in fig. 2, the projectile loader comprises an aircraft connecting seat and a projectile connecting seat of a split structure, the aircraft connecting seat mainly comprises a plate body 21 connected with the bottom surface of the unmanned aerial vehicle 10 and a sleeve body 22 arranged on the bottom surface of the plate body 21, and the plate body 21 is provided with a fastener perforation forming a mounting structure for connecting the plate body 21 and the unmanned aerial vehicle 10 in a detachable manner through a threaded fastener. The projectile connecting seat comprises a projectile containing cylinder 23 for containing the projectile, and the sleeve body 22 of the aircraft connecting seat is used for inserting the projectile containing cylinder 23, so that the connection between the projectile containing cylinder 23 and the unmanned aerial vehicle 10 is realized. A clip interface 221 is provided on the side wall of the case body 22, and a clip joint that fits with the clip interface 221 is provided on the outer wall of the bomb-receiving tube 23. The snap-in interface 221 on the sleeve body 22 has an axial portion extending along the axis of the sleeve body 22 and a circumferential portion disposed along the circumference of the sleeve body 22, and the structure of the snap-in interface is a projection 231 disposed on the outer wall surface of the projectile body accommodating barrel 23 and extending along the circumference. When the bomb accommodating barrel 23 is inserted into the sleeve body 22 and moves axially along the sleeve body 22, the axial part of the clamping interface 221 can avoid the movement of the projection 231, after the bomb accommodating barrel 23 moves in place in the axial direction, the bomb accommodating barrel 23 is rotated to enable the projection 231 to move axially, and the projection 231 is clamped into the circumferential part to realize the connection of the bomb accommodating barrel 23 and the aircraft connector. A fastener is further provided between the jacket body 22 and the bomb-receiving tube 23 to secure the relative positions of the two.
As shown in fig. 3, 5 and 6, a bottom plate 232 is disposed at one end of the bomb-containing tube 23 to make the bomb-containing tube 23 have a structure with one open end and one closed end, and the bomb 30 is hung in the inner cavity of the bomb-containing tube 23 through the bomb-inserting seat 40. The bullet body socket 40 is a cylindrical barrel, the middle part of which is provided with a plugging cavity for plugging the bullet body 30, and the bullet body 30 and the plugging cavity are in interference fit. And the periphery of cylinder barrel is gone up the symmetry and is provided with two dops 234 that are used for with the bottom plate 232 joint of a projectile body holding section of thick bamboo 23, be provided with on the bottom plate 232 of a projectile body holding section of thick bamboo 23 with the draw-in groove 233 of dop 234 joint on the connecting seat, draw-in groove 233 has the major diameter part that radial dimension is great and the minor diameter part that radial dimension is less, major diameter part dodges dop 234 when the connecting seat along projectile body holding section of thick bamboo 23 axial motion, the connecting seat is after the axial direction motion targets in place, self rotation so that dop 234 on the connecting seat enters into in the minor diameter part and with the partial. On the side of the small-diameter portion, a wedge structure is provided which gradually increases in height in a direction from the large-diameter portion into the small-diameter portion, and the cartridge 234 gradually rises along the wedge structure to chuck the bullet 30 in the bullet-receiving barrel 23.
As shown in fig. 4, the protrusion 231 on the projectile accommodation barrel 23 is disposed at an end position of the projectile accommodation barrel 23, and the clip interface 221 of the aircraft connector, which is matched with the protrusion 231, is disposed at a middle position of the sheath body 22, so that when the projectile accommodation barrel 23 is connected with the aircraft connector, a space is formed between the bottom plate 232 of the projectile accommodation barrel 23 and the plate body 21 of the sheath body 22 of the aircraft connector, and the space formed by the whole space is used for accommodating a control module for controlling the projection of the projectile 30. And the bottom plate 232 of the projectile body accommodating cylinder 23 is also provided with an inserting convex part 235 protruding towards the projectile body inserting seat 40 corresponding to each projectile body 30, when the projectile body inserting seat 40 is connected with the projectile body accommodating cylinder 23, one end of the projectile body inserting seat 40 close to the bottom plate 232 of the projectile body accommodating cylinder 23 is provided with a cavity in inserting fit with the outer wall surface of the inserting convex part 235, so that the connection between the projectile body inserting seat 40 and the aircraft connecting seat is more reliable and stable.
A closed chamber 50 surrounded by the bullet socket 40, the bullet 30 and the bottom plate 232 of the bullet containing barrel 23 is arranged between one side of the bullet socket 40 close to the bullet 30 and the bottom of the bullet 30, the whole space in the closed chamber 50 is filled with gunpowder, after the gunpowder is ignited in the firing chamber, the gas in the closed chamber 50 expands and the pressure rises to push the tail end of the bullet 30, so that the bullet 30 overcomes the friction force of the inner wall of the bullet socket 40 and is separated from the bullet socket 40. The bottom plate 232 is provided with a through hole for an operator to fill powder into the closed chamber 50, the control module located in the aircraft connector is connected with an electric heating wire as an ignition device through a lead, the electric heating wire enters the closed chamber 50 through the through hole, and after the control module is electrically connected with the electric heating wire through the lead, the electric heating wire is heated up to detonate the powder to generate high-pressure gas for pushing the projectile body 30 to move. The tail of the projectile 30 is provided with a fuse, also located in the closed chamber 50, which, when the powder is ignited, will ignite to cause the projectile 30 to explode after emerging from the projectile socket 40. In order to prevent the explosive from affecting the control module through the through hole after detonation, a blocking object is filled in the inner cavity of the insertion convex part 235 to block the through hole.
In this embodiment, when unmanned aerial vehicle 10 carries out the task, still be provided with the shrouding that carries out the shutoff to a projectile body holding section of thick bamboo 23 at projectile body holding section of thick bamboo 23 lower part opening part, when projectile body 30 throws, need open the shrouding so that projectile body 30 can throw smoothly. Three hollow cylinders 236 are provided in the bullet-receiving socket 23 in the axial direction of the bullet-receiving socket 23. The hollow cylinder 236 has an opening at one end connected to the bottom plate 232 of the projectile-containing cylinder 23, and an opening at the other end connected to the insertion post disposed on the sealing plate, and the sealing plate is fixed to the bottom of the projectile-containing cylinder 23 through the insertion post. A small amount of gunpowder is arranged in the hollow cylinder 236, and some heating wires extending into the hollow cylinder 236 to ignite the gunpowder are led out from the control module, and the heating wires can ignite the gunpowder in the hollow cylinder 236 after being electrified, so that high-pressure gas can be generated in the hollow cylinder 236 in a short time due to the explosion of the gunpowder. The high pressure gas within the three hollow cylinders 236 pushes the sealing plate away from engagement with the cartridge 23. The control module in this embodiment is in communication connection with the signal receiving module in the unmanned aerial vehicle 10, and the signal receiving module of the unmanned aerial vehicle 10 is utilized to transmit signals with a control station or an operator on the ground.
Use at operating personnel the utility model provides an during air-drop bullet device 20, when utilizing signal receiving module control unmanned aerial vehicle 10 action in unmanned aerial vehicle 10, also can control the input of projectile body 30 to the control module input instruction in the air-drop bullet device 20 simultaneously. After unmanned aerial vehicle 10 arrived the position, operating personnel sent signal to unmanned aerial vehicle 10 subaerial, signal reception module in unmanned aerial vehicle 10 sends control body 30's signal for control module, control module is earlier through the heating wire circular telegram of wire with setting up in hollow cylinder 236, gunpowder detonating and producing high-pressure gas in the twinkling of an eye in hollow cylinder 236, the shrouding that carries out the shutoff to the opening that the bullet held a section of thick bamboo 23 is pushed away by the high-pressure gas in the hollow cylinder 236. Then the control module detonates the gunpowder at the tail part of the bullet 30 through a lead, so that the bullet 30 is separated from the bullet socket 40 and makes free-falling body movement under the action of self weight.
In other embodiments, a connection end for inserting into the projectile body may be disposed on the projectile body connection seat, the connection end and the projectile body are in interference fit, and the closed cavity is defined by the connection end and the projectile body. Also, in other embodiments, the enclosed chamber may be filled with only some powder, rather than a solution in which the powder completely fills the enclosed chamber.
In other embodiments, a structure for hoisting the projectile inserted into the projectile connecting seat into the insertion cavity may be provided between the projectile and the projectile connecting seat, for example, a rope which is blown by flame or pulled by external force when gunpowder is ignited may be used, or a connecting arm with limited pulling force may be used, and the connecting arm is broken after gunpowder is ignited, so that the projectile is pulled out from the projectile connecting seat; at this time, the mode of interference fit between the projectile body and the projectile body connecting seat can be omitted.
In other embodiments, the projectile attachment mount may be of unitary construction with the aircraft attachment mount, rather than being of a split construction.
In other embodiments, the closing plate opening structure may be replaced by other forms, for example, a push rod controlled by the control module may be disposed in the projectile body connecting seat, the push rod is disposed along the extending direction of the single body, and the closing plate can be pushed open when the push rod extends downwards.
In other embodiments, the lower portion of the projectile attachment seat may no longer be provided with a sealing plate.
The utility model provides an air-drop bomb device can adopt different types of air-drop bombs such as smog bomb, fire extinguishing bomb to come to be connected with projectile body carry ware to accomplish different tasks.
The utility model discloses well projectile carrier's structure is the same with the projectile carrier structure in the above-mentioned empty bullet device embodiment to application method is also the same, and the difference only lies in not loading the projectile in the projectile carrier, consequently no longer duplicate explanation about the embodiment of projectile carrier.
The above-mentioned embodiments further explain the objects, technical solutions and advantages of the present invention in detail, it should be understood that the above-mentioned embodiments are only embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. Projectile body carrier, its characterized in that:
the aircraft connecting seat is provided with a mounting structure for connecting with an aircraft;
the aircraft connecting base is provided with a projectile body connecting base, the projectile body connecting base is in plug fit with the top end of a projectile body through a plug structure, a closed cavity is defined at the plug structure when the projectile body connecting base and the projectile body are in plug fit, gunpowder is filled in the closed cavity, and the gunpowder is used for generating high-pressure gas to push the projectile body out of the projectile body connecting base when burning;
an ignition device for igniting gunpowder is also arranged on the projectile body loader.
2. The projectile mount of claim 1, wherein: and the elastomer connecting seat is in interference fit with the elastomer.
3. The projectile mount of claim 2, wherein: aircraft connecting seat and projectile body connecting seat are provided with the draw-in groove on one of them between the two, are provided with the dop on the other, and aircraft connecting seat and projectile body connecting seat realize releasable connection through the joint structure of constituteing by draw-in groove and dop.
4. The projectile mount of claim 3, wherein: the end face, used for being connected with the projectile body connecting seat in a clamped mode, of the projectile body connecting seat is provided with a plug-in convex portion protruding towards the projectile body connecting seat, the plug-in convex portion is inserted into a plug-in cavity of the projectile body connecting seat when the projectile body connecting seat is connected with the projectile body connecting seat in a clamped mode, and the projectile body and the inner wall of the plug-in cavity are enclosed to form the closed cavity.
5. The projectile mount of any one of claims 1-4, wherein: a sealing plate is arranged at the lower opening of the missile loader, and a sealing plate opening structure for opening the sealing plate during missile throwing is arranged in the missile loader.
6. The projectile mount of claim 5, wherein: the projectile body carrier is provided with a hollow cylinder, the sealing plate is provided with an inserting column which is used for being inserted into a cavity of the hollow cylinder to be connected with the projectile body carrier, gunpowder used for generating high-pressure gas pushing the sealing plate away when ignition is conducted is filled in the hollow cylinder, and the hollow cylinder forms the sealing plate opening structure.
7. Air-drop bullet device, its characterized in that:
comprises a projectile body loader and a projectile body loaded in the projectile body loader; the projectile mount as defined in any one of claims 1 to 6.
8. The aerial delivery device of claim 7, wherein: the afterbody of projectile body is provided with the detonator that is used for igniting the projectile body, and the detonator stretches into in the projectile body connecting seat when projectile body and projectile body connecting seat grafting cooperation to the realization ignites the detonator when gunpowder is ignited.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922440714.5U CN211996150U (en) | 2019-12-30 | 2019-12-30 | Empty bullet device and projectile body carrier |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922440714.5U CN211996150U (en) | 2019-12-30 | 2019-12-30 | Empty bullet device and projectile body carrier |
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| CN211996150U true CN211996150U (en) | 2020-11-24 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113247263A (en) * | 2021-07-05 | 2021-08-13 | 天津天羿科技有限公司 | Multi-mode missile throwing device for aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113247263A (en) * | 2021-07-05 | 2021-08-13 | 天津天羿科技有限公司 | Multi-mode missile throwing device for aircraft |
| CN113247263B (en) * | 2021-07-05 | 2021-10-01 | 天津天羿科技有限公司 | Multi-mode missile throwing device for aircraft |
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