CN114537669A - Unmanned aerial vehicle machine carries system of throwing - Google Patents
Unmanned aerial vehicle machine carries system of throwing Download PDFInfo
- Publication number
- CN114537669A CN114537669A CN202111629327.1A CN202111629327A CN114537669A CN 114537669 A CN114537669 A CN 114537669A CN 202111629327 A CN202111629327 A CN 202111629327A CN 114537669 A CN114537669 A CN 114537669A
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- limiting
- projectile
- ammunition
- unmanned aerial
- aerial vehicle
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- 238000004804 winding Methods 0.000 claims description 18
- 230000033001 locomotion Effects 0.000 claims description 6
- 238000005381 potential energy Methods 0.000 claims description 3
- IMACFCSSMIZSPP-UHFFFAOYSA-N phenacyl chloride Chemical compound ClCC(=O)C1=CC=CC=C1 IMACFCSSMIZSPP-UHFFFAOYSA-N 0.000 abstract description 18
- 239000003491 tear gas Substances 0.000 abstract description 18
- 238000010586 diagram Methods 0.000 description 6
- 230000007246 mechanism Effects 0.000 description 6
- 238000010304 firing Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000003491 array Methods 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 231100000252 nontoxic Toxicity 0.000 description 1
- 230000003000 nontoxic effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides an airborne missile launching system of an unmanned aerial vehicle, which comprises: the control box, the projectile throwing device and the limiting device; the control box is provided with a projectile shooting device below, the projectile shooting device is internally provided with symmetrical projectile shooting barrels, ammunition is arranged in the projectile shooting barrels, the limiting device is arranged at the bottom end of the projectile shooting barrels through a hinge, the limiting device is used for limiting the ammunition inside the projectile shooting barrels, and the control box is used for controlling the limiting device to release the ammunition. According to the invention, the limit bolt is used for limiting the limit top cover, so that when a throwing instruction is not sent, the tear-gas shells are completely restrained in the throwing cylinder, and the mistaken throwing is prevented; the system realizes accurate delivery, helps police officers to realize remote task execution, and avoids unnecessary loss.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an airborne missile launching system of an unmanned aerial vehicle.
Background
The Chinese utility model patent CN201159623Y discloses a nontoxic pollution-free environment-friendly tear-gas shells, which can be triggered by pulling out a lead when in use, and can not realize accurate striking because of throwing when in use, and the striking range is extremely limited;
the Chinese invention patent CN105667794A discloses an unmanned aerial vehicle projectile throwing system, which utilizes a spring and a rocker arm to limit the position of a clamping part for loading a tear-gas projectile, and when the force generated by a compression spring in a launching tube breaks through the friction force of a clamping device on the tear-gas projectile in the flight process of the unmanned aerial vehicle, the accidental firing is easy to occur.
Disclosure of Invention
In view of the above problems, the invention aims to provide an airborne tear-gas shells system of an unmanned aerial vehicle, which can mount tear-gas shells with different quantities onto the unmanned aerial vehicle, limit the position of a limiting top cover through a limiting bolt, and completely restrain the tear-gas shells in a shell throwing cylinder when a throwing instruction is not sent, so as to prevent the occurrence of mistaken throwing; through every single move cloud platform adjustment tear-gas shells launch angle, get into to put in the position at unmanned aerial vehicle and back finely tune through every single move cloud platform, later throw or penetrate directly, realize accurate putting in, help police service personnel realize remote executive task, avoid unnecessary loss.
In order to achieve the purpose, the invention adopts the following specific technical scheme:
the invention provides an airborne missile launching system of an unmanned aerial vehicle, which comprises: the control box, the projectile throwing device and the limiting device;
the control box is provided with a projectile shooting device below, the projectile shooting device is internally provided with symmetrical projectile shooting barrels, ammunition is arranged in the projectile shooting barrels, the limiting device is arranged at the bottom end of the projectile shooting barrels through a hinge, the limiting device is used for limiting the ammunition inside the projectile shooting barrels, and the control box is used for controlling the limiting device to release the ammunition.
Preferably, the projectile firing device comprises: a projectile barrel base, a spring and ammunition;
the projectile tube base is fixed at one end of the projectile tube and is integrated with the projectile tube; one end of the spring is fixed on the base of the projectile barrel, ammunition is loaded into the projectile barrel, the spring is compressed, elastic potential energy is stored, and the ammunition is limited in the projectile barrel through the limiting device.
Preferably, the base of the projectile shooting barrel is provided with a central hole, the side surface of the base of the projectile shooting barrel is provided with semicircular bulges, and the bulges are respectively provided with mounting holes;
a first limiting block and a second limiting block are arranged on the projectile tube base, central holes are formed in the first limiting block and the second limiting block respectively, and fan-shaped holes are uniformly distributed around the central holes of the first limiting block.
Preferably, the projectile firing device further comprises: the winding shaft is provided with a small hole;
the winding shaft respectively passes through the center holes of the first limiting block and the second limiting block, and the lead of the ammunition sequentially passes through the center hole and the small hole of the projectile barrel base and is wound on the winding shaft.
Preferably, one end of the winding shaft is provided with a fixed platform, and the fixed platform is provided with a limiting bulge;
one side of the limiting bulge is an inclined plane, and the other side of the limiting bulge is a plumb bob surface; the limiting bulge is inserted into the fan-shaped hole and used for limiting the winding shaft to rotate in one direction.
Preferably, the stop device comprises: a limiting top cover and a steering engine;
the limiting top cover is hinged to the bottom end of the projectile barrel; a connecting piece is arranged at the edge of the limiting top cover;
the steering engine is fixed on the side surface of the bottom end of the projectile shooting barrel, a steering engine arm is mounted on the steering engine, and the steering engine is used for controlling the steering engine arm to rotate; the tail end of the rudder arm is provided with a connecting rod, and the tail end of the connecting rod is provided with a limiting bolt; the limiting bolt is used for limiting the movement of the connecting piece;
the steering engine arm, the connecting rod and the limiting bolt are movably connected, the connecting rod is driven to move when the steering engine arm rotates, and the connecting rod drives the limiting bolt to move.
Preferably, the stop device comprises: the top end of the guide sleeve is provided with two extending fixing rods which are respectively fixedly connected with the connecting piece and the steering engine, and the guide sleeve is used for controlling the movement direction of the limiting bolt.
Preferably, the connecting piece is the U-shaped structure, and the gyro wheel is installed through the axis of rotation in the inside of connecting piece, and the gyro wheel is used for reducing the frictional force between spacing bolt and the connecting piece.
Preferably, every single move cloud platform and control box are provided with the counter bore for lighten unmanned aerial vehicle machine carries the dead weight of the system of throwing a bullet.
Preferably, the unmanned aerial vehicle further comprises a pitching cloud platform, the pitching cloud platform is installed below the unmanned aerial vehicle through a quick-release assembly, a control box is installed below the pitching cloud platform, and the control box is in rotary connection with the pitching cloud platform;
compared with the prior art, the tear bomb is completely restrained in the bomb tube by limiting the top cover through the bolt when a throwing instruction is not sent, so that the occurrence of mistaken throwing is prevented; through every single move cloud platform adjustment tear-gas shells launch angle, finely tune through the cloud platform after unmanned aerial vehicle gets into the input position, later cast or penetrate directly, realize accurate input, help police officer realizes remote executive task, avoids unnecessary loss.
Drawings
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle loading system provided in an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of an airborne missile system of an unmanned aerial vehicle provided in an embodiment of the invention.
Fig. 3 is a schematic internal structural diagram of a single projectile device of the airborne projectile shooting system of the unmanned aerial vehicle provided by the embodiment of the invention.
Fig. 4 is a schematic structural diagram of a projectile tube base and a spool of an airborne projectile shooting system of an unmanned aerial vehicle provided by the embodiment of the invention.
Fig. 5 is a schematic structural diagram of a limiting device of an airborne missile throwing system of an unmanned aerial vehicle, provided by the embodiment of the invention.
Fig. 6 is a schematic diagram of a control box of an airborne missile system of an unmanned aerial vehicle provided according to an embodiment of the invention.
Wherein the reference numerals include: pitching cloud platform 1, throwing device 2, spool 21, stopper 211, throwing barrel base 22, first stopper 221, second stopper 222, sector hole 223, spring 23, tear-gas shells 24, throwing barrel 25, camera 3, control box 4, array board 4-1, stop device 5, stop bolt 51, stop top cover 52, connecting piece 521, gyro wheel 522, connecting rod 53, steering wheel 54, rudder horn 55, uide bushing 56, quick detach subassembly 6 and notch 7.
Detailed Description
Hereinafter, embodiments of the present invention will be described with reference to the drawings. In the following description, the same reference numerals are used for the same blocks. In the case of the same reference numerals, their names and functions are also the same. Therefore, detailed description thereof will not be repeated.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention.
Fig. 1 shows a loading system for a drone provided according to an embodiment of the invention.
Fig. 2 shows an airborne missile system for unmanned aerial vehicles according to an embodiment of the invention.
As shown in fig. 1 and fig. 2, an airborne missile system of an unmanned aerial vehicle provided by an embodiment of the present invention includes: pitching cloud platform 1, the device of throwing 2, camera 3, control box 4, stop device 5 and quick detach subassembly 6.
Every single move cloud platform 1 passes through quick detach subassembly 6 to be installed in unmanned aerial vehicle's below, is fixed connection between every single move cloud platform 1, quick detach subassembly 6 and the unmanned aerial vehicle three. Control box 4 is installed in the below of every single move cloud platform 1, is connected for rotating between control box 4 and the every single move cloud platform 1, and every single move cloud platform 1 passes through dead axle and notch 7, through steering wheel drive realization control box 4 regulation of every single move degree of freedom, and the extreme position of 4 every single move angle changes of control box can not take place to interfere with other devices in the unmanned aerial vehicle loading system. In order to facilitate wiring, the camera 3 is installed at one end of the control box 4; and transmitting the ground information obtained by the camera back to the manipulator in real time for aiming. The camera 3 is oriented in the same direction as the transmission direction, which makes the ground information acquired by the camera 3 exactly the angle the transmission system is oriented. The wiring of the whole system is clear and attractive, the occurrence of interference is reduced, all controllers and the flat cables are arranged inside the control box 4, and the flat cables are used for supplying power to the actuating mechanism and transmitting control signals.
The fixed shaft and the notch 7 enable the control box 4 to rotate around the fixed shaft, so that the pitch angle is adjusted, and the notch 7 is limited, so that the pitch angle cannot be excessively adjusted to cause instability of the unmanned aerial vehicle
A projectile device 2 is mounted below the control box 4.
Fig. 3 shows the internal structure of a single projectile device of the projectile shooting system on board an unmanned aerial vehicle provided according to an embodiment of the present invention.
Fig. 4 shows a cartridge base and a spool of the airborne cartridge system of the unmanned aerial vehicle provided according to an embodiment of the invention.
As shown in fig. 3 and 4, the projectile shooting device 2 includes: the tear-gas shells comprise a winding shaft 21, a limiting protrusion 211, a shell base 22, a first limiting block 221, a second limiting block 222, a fan-shaped hole 223, a spring 23, tear shells 24 and a shell feeding barrel 25.
The side surface of the projectile tube base 22 is provided with uniform semicircular bulges, and the bulges are respectively provided with mounting holes; a first limiting block 221 and a second limiting block 222 are arranged on the projectile tube base 22, the centers of the first limiting block 221 and the second limiting block 222 are on the same straight line, a central hole is formed in the first limiting block 221, a plurality of fan-shaped holes 223 are formed in the periphery of the central hole, the fan-shaped holes 223 are evenly distributed in the periphery of the central hole, and the number of the fan-shaped holes in the airborne projectile system of the unmanned aerial vehicle is 4; the second stopper 222 is provided with a center hole, and the center holes of the first stopper 221 and the second stopper 222 have the same height.
One end of the winding shaft 21 is provided with a fixed platform, the fixed platform is provided with a plurality of limiting bulges 211, one side of each limiting bulge 211 is an inclined plane, and the other side of each limiting bulge 211 is a plumb surface; the number of the limiting protrusions 211 in the airborne missile system of the unmanned aerial vehicle is 4, the winding shaft 21 respectively penetrates through the center holes of the first limiting block 221 and the second limiting block 222, the limiting protrusions 211 are inserted into the fan-shaped holes 223, the winding shaft 21 rotates in a single direction and can easily rotate towards the direction of an inclined plane, and when the winding shaft rotates in the reverse direction, the fan-shaped holes 223 of the base 22 of the missile barrel limit the winding shaft 21 and limit the reverse rotation of the winding shaft 21.
The projectile tube 25 is provided with a spring 23 and a tear-gas shells 24, the spring 23 is loaded into the projectile tube 25, one end of the spring 23 is fixed on the projectile tube base 22, and the projectile tube 25 plays a guiding role on the spring 23, so that the spring can be prevented from generating radial deformation when being compressed. After the tear-gas shells 24 are loaded into the shell throwing barrel 25, the springs 23 are compressed, and elastic potential energy is stored; the lead of the tear-gas shells 24 passes through the central hole of the projectile tube base 22 and is wound on the winding shaft 21; the winding shaft 21 is provided with a small hole, and a lead of the tear-gas bomb 24 passes through the small hole and is wound on the winding shaft 21, so that the lead and the winding shaft 21 are prevented from sliding.
The tear-gas shells 24 are limited to be ejected by the limiting device 5. The limiting device 5 is positioned at the bottom end of the projectile barrel 25.
Fig. 5 shows a limiting device of an airborne missile throwing system of an unmanned aerial vehicle, provided by the embodiment of the invention.
As shown in fig. 5, the stopper 5 includes: spacing bolt 51, spacing top cap 52, connecting piece 521, gyro wheel 522, connecting rod 53, steering wheel 54, steering wheel arm 55 and uide bushing 56.
The limiting top cover 52 is positioned at the bottom end of the projectile shooting barrel 25, and the limiting top cover 52 is installed on the projectile shooting barrel 25 through a hinge mechanism; the limiting top cover 52 is rotatably connected with the projectile tube 25, a connecting piece 521 is arranged at the edge of the limiting top cover 52, and the position of the connecting piece 521 corresponds to the position of the hinge. When the roller 522 is mounted on the link 521, the link 521 has a U-shaped structure, and the roller 522 is mounted inside the link 521 through a rotating shaft. The roller 522 is used to change a sliding friction force into a rolling friction force, so as to reduce a friction force generated when the limit latch 51 moves with the connecting member 521.
Two extending fixing rods are arranged at the top end of the guide sleeve 56, and the fixing rods at the top end of the guide sleeve 56 are fixedly connected with the connecting piece 521 and the steering engine 54 respectively. The guide sleeve 56 is used for controlling the motion track of the limit bolt 52.
The steering engine 54 is fixed on the side surface of the bottom end of the projectile shooting barrel 25, a steering engine arm 55 is mounted on the steering engine 54, and the steering engine 54 can control the steering engine arm 55 to rotate; the tail end of the rudder arm 55 is provided with a connecting rod 53, and the tail end of the connecting rod 53 is provided with a limiting bolt 51;
the rudder arm 55, the connecting rod 53 and the limiting bolt 51 form a crank slider mechanism, the rudder arm 55, the connecting rod 53 and the limiting bolt 51 are movably connected, the connecting rod 53 is driven to move when the rudder arm 55 rotates, and the connecting rod 53 drives the limiting bolt 51 to move in the guide sleeve 56.
The left side of fig. 5 is the state of the limiting device 5 in limiting, when the limiting device 5 is in limiting, the steering engine 55 drives the slider-crank mechanism to move, so that the limiting bolt 51 moves in the guide sleeve 56 to enter a limiting position, the limiting top cover 52 is closed, and the tear-gas shells 24 are limited in the shell throwing barrel 25.
The state of spacing bolt 51 when 5 right sides in for the release, when stop device 5 was in the release state, steering wheel 55 drive slider-crank mechanism moved, made spacing bolt 51 move in uide bushing 56 and break away from limit position, and spacing top cap 52 is opened, and ejection spring promotes tear-gas shells 24 and puts in, and at the in-process of putting in, the pull ring is fixed on the spool, and the lead wire is pulled out simultaneously.
In the motion interval of the limit and release positions of the limit bolt 51, the slider-crank mechanism cannot have a self-locking position.
Fig. 6 shows a control box of the unmanned aerial vehicle airborne missile system provided according to the embodiment of the invention.
As shown in fig. 6, the control box 4 includes an array plate 4-1. The array plate 4-1 is used for installing the bomb-throwing device 2, so that the unmanned aerial vehicle can mount throwing devices with different quantities according to working conditions, when the requirement on the throwing quantity is low, the flight operation time of the unmanned aerial vehicle can be prolonged, and when the array plate is used, the unmanned aerial vehicle can execute tasks, other performances such as other external equipment mounting, flight time prolonging and the like can be considered
In order to reduce the dead weight of the airborne missile throwing system of the unmanned aerial vehicle and increase the endurance time, the invention makes necessary weight reduction, makes counter bore weight reduction design for a pitching cradle head and a control box, and has low requirements on strength, such as the following components: the array plate 4-1 and the control box 4 are covered by carbon fiber plates.
The tear shells of the unmanned aerial vehicle airborne missile system are in 2 x 4 arrays, and in actual situations, different numbers of tear shells can be selected to be mounted according to different loading capacities of different unmanned aerial vehicles and different task requirements.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
The above embodiments of the present invention should not be construed as limiting the scope of the present invention. Any other corresponding changes and modifications made according to the technical idea of the present invention should be included in the protection scope of the claims of the present invention.
Claims (10)
1. An unmanned aerial vehicle machine carries bullet system that throws, its characterized in that includes: the control box, the projectile throwing device and the limiting device;
the ammunition throwing device is installed below the control box, symmetrical ammunition throwing cylinders are installed in the ammunition throwing device, ammunition is installed in the ammunition throwing cylinders, the limiting device is installed at the bottom end of the ammunition throwing cylinders through hinges and used for limiting the ammunition inside the ammunition throwing cylinders, and the control box is used for controlling the limiting device to release the ammunition.
2. The system of claim 1, wherein the projectile apparatus comprises: a projectile barrel base, a spring and ammunition;
the projectile tube base is fixed at one end of the projectile tube and is of an integrated structure with the projectile tube; one end of the spring is fixed on the projectile barrel base, the ammunition is loaded into the projectile barrel, the spring is compressed, elastic potential energy is stored, and the ammunition is limited in the projectile barrel through the limiting device.
3. The unmanned aerial vehicle airborne missile system of claim 2, wherein the missile launcher base is provided with a central hole, the lateral surface of the missile launcher base is provided with semicircular bulges, and the bulges are respectively provided with mounting holes;
the projectile tube base is provided with a first limiting block and a second limiting block, the first limiting block and the second limiting block are respectively provided with a central hole, and fan-shaped holes are uniformly distributed around the central hole of the first limiting block.
4. The airborne missile system of claim 3, wherein the missile device further comprises: the winding shaft is provided with a small hole;
the bobbin penetrates through the center holes of the first limiting block and the second limiting block respectively, and the lead of the ammunition sequentially penetrates through the center hole of the projectile tube base and the small hole and is wound on the bobbin.
5. The unmanned aerial vehicle airborne missile system of claim 4, wherein a fixed platform is arranged at one end of the spool, and a limiting protrusion is arranged on the fixed platform;
one side of the limiting bulge is an inclined plane, and the other side of the limiting bulge is a plumb bob surface; the limiting protrusion is inserted into the fan-shaped hole and used for limiting the winding shaft to rotate in one direction.
6. The airborne missile system of claim 5, wherein the stop device comprises: a limiting top cover and a steering engine;
the limiting top cover is hinged to the bottom end of the projectile barrel; a connecting piece is arranged at the edge of the limiting top cover;
the steering engine is fixed on the side face of the bottom end of the projectile shooting barrel, a steering engine arm is mounted on the steering engine, and the steering engine is used for controlling the steering engine arm to rotate; the tail end of the rudder horn is provided with a connecting rod, and the tail end of the connecting rod is provided with a limiting bolt; the limiting bolt is used for limiting the movement of the connecting piece;
the steering engine arm, the connecting rod and the limiting bolt are movably connected, the steering engine arm drives the connecting rod to move when rotating, and the connecting rod drives the limiting bolt to move.
7. The airborne missile system of claim 6, wherein the stop device comprises: the top end of the guide sleeve is provided with two extending fixing rods, the fixing rods are respectively fixedly connected with the connecting piece and the steering engine, and the guide sleeve is used for controlling the movement direction of the limiting bolt.
8. The airborne missile system of claim 7, wherein the connecting piece is of a U-shaped structure, rollers are mounted inside the connecting piece through rotating shafts, and the rollers are used for reducing friction between the limiting bolts and the connecting piece.
9. The unmanned aerial vehicle airborne missile system of claim 8, wherein the pitch pan/tilt head and the control box are provided with counter bores for reducing the self weight of the unmanned aerial vehicle airborne missile system.
10. The airborne missile system of claim 9, further comprising a pitch pan and tilt head, wherein the pitch pan and tilt head is mounted below the unmanned aerial vehicle through a quick release assembly, a control box is mounted below the pitch pan and tilt head, and the control box is rotatably connected with the pitch pan and tilt head.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111629327.1A CN114537669A (en) | 2021-12-28 | 2021-12-28 | Unmanned aerial vehicle machine carries system of throwing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111629327.1A CN114537669A (en) | 2021-12-28 | 2021-12-28 | Unmanned aerial vehicle machine carries system of throwing |
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| Publication Number | Publication Date |
|---|---|
| CN114537669A true CN114537669A (en) | 2022-05-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111629327.1A Pending CN114537669A (en) | 2021-12-28 | 2021-12-28 | Unmanned aerial vehicle machine carries system of throwing |
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| Country | Link |
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| CN (1) | CN114537669A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116443251A (en) * | 2023-06-09 | 2023-07-18 | 四川观想科技股份有限公司 | System ammunition throwing device for unmanned aerial vehicle |
| WO2024112916A1 (en) * | 2022-11-22 | 2024-05-30 | Ball Dillon Casidhe Evan | Load balancing aerial munitions delivery system |
-
2021
- 2021-12-28 CN CN202111629327.1A patent/CN114537669A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024112916A1 (en) * | 2022-11-22 | 2024-05-30 | Ball Dillon Casidhe Evan | Load balancing aerial munitions delivery system |
| CN116443251A (en) * | 2023-06-09 | 2023-07-18 | 四川观想科技股份有限公司 | System ammunition throwing device for unmanned aerial vehicle |
| CN116443251B (en) * | 2023-06-09 | 2023-08-22 | 四川观想科技股份有限公司 | System ammunition throwing device for unmanned aerial vehicle |
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