Unmanned aerial vehicle launch canister
By using a gas generator as a power source in the drone launch tube, the problem of excessive tube pressure caused by the combustion of pyrotechnics has been solved, enabling a safer and more flexible drone launch method.
Patent Information
- Application Number
- CN202423086793.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-13
- Publication Date
- 2025-10-31
- Estimated Expiration
- 2034-12-13
AI Technical Summary
Existing drone launch tubes use pyrotechnic combustion as a power source, resulting in violent reactions and high temperatures, causing excessive tube pressure and easily damaging the launch tube and related components.
Using a gas generator as a power source, high-pressure gas is generated by the combustion of a gas generator to propel the sabot device and launch the drone. The gas generator works in conjunction with the inner wall of the cylinder and the bottom of the drone to reduce noise, temperature and pressure, and improve safety.
It reduces noise, temperature, and pressure on the launch tube during launch, improves launch safety and the flexibility and reliability of the gas generator, and enhances safety during transportation.
Smart Images
Figure CN223494802U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of drone launcher technology, and in particular to a drone launcher. Background Technology
[0002] Existing drone launch tubes all use pyrotechnic combustion as a power source. However, the reaction of pyrotechnic combustion is violent and the temperature is high, which can lead to excessive tube pressure, causing a large impact on the launch tube and related accessories, and easily causing damage. Utility Model Content
[0003] The main purpose of this invention is to propose a drone launch tube that aims to improve the safety of drone launch tubes.
[0004] To achieve the above objectives, the UAV launch tube proposed in this utility model includes:
[0005] Base;
[0006] The cylindrical body is located on the base;
[0007] A gas generator, disposed on the base and located within the cylinder, the gas generator comprising a gas generating agent and an igniter; and
[0008] A sabot is movably disposed within the cylinder. The sabot includes a first plate and a second plate. The first plate is located above the gas generator, and its shape matches the structure of the inner wall of the cylinder. The second plate is fixed to the first plate and located above it. The second plate is used to abut against the lower end of the UAV.
[0009] Optionally, the ejector device further includes a plurality of connecting rods extending axially along the cylinder, with one end of the plurality of connecting rods fixed to the first plate and the other end fixed to the first plate.
[0010] Optionally, the drone launch tube further includes a cover movably mounted on the tube body. The cover has a closed position and an open position. In the closed position, the cover closes to the launch port of the tube body. In the open position, the cover is spaced apart from the launch port of the tube body.
[0011] Optionally, the cap is provided with a limiting member, the shape of which matches the structure of the top of the drone. When the cap is in the closed position, the limiting member abuts against the top of the drone.
[0012] Optionally, a torsion spring is provided between the cap and the body, the torsion spring having an elastic deformation to return the cap from the closed position to the open position, and the body is provided with a movable locking pin, which is inserted into the cap to limit the cap in the closed position.
[0013] Optionally, the base is provided with a plurality of support rods that extend along the extension direction of the cylinder, and the first plate is placed at the upper end of the plurality of support rods.
[0014] Optionally, the drone launch tube includes a limiting rope, the lower end of which is fixed to the base, and the upper end of which is connected to the lower end of the first plate.
[0015] Optionally, the base is provided with a mounting seat, which is detachably mounted on the base from the bottom end of the base, the gas generator is mounted on the mounting seat, and the lower end of the limiting rope is fixed to the mounting seat.
[0016] Optionally, the upper end of the second plate is provided with a limiting groove, and the UAV is provided with a limiting protrusion that matches the shape of the limiting groove.
[0017] This invention utilizes a cylindrical base with a movable launcher device. The launcher device comprises a first plate and a second plate fixed to each other. The shape of the first plate matches the structure of the inner wall of the cylindrical base, while the shape of the second plate matches the structure of the drone's bottom. The second plate is positioned above the first plate. When the drone is mounted in the launcher, the second plate rests against the lower end of the drone. A gas generator is installed on the base. Triggering the gas generator detonates the igniter inside, igniting the gas generating agent. The high-pressure gas generated at the moment of ignition enters between the base and the first plate through the gas generator, pushing the first plate upwards at high speed. This, in turn, propels the second plate, launching the drone from the cylindrical base. Compared to launching drones with solid fuel using pyrotechnics, this method of launching drones with high-pressure gas generated by the combustion of the gas generating agent results in lower noise, lower temperature, and lower pressure on the launch tube during combustion, making launch safer. Furthermore, the gas generator offers greater flexibility and is safer and more reliable for storage and transportation. Attached Figure Description
[0018] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.
[0019] Figure 1 This is a schematic diagram of the structure of an embodiment of the UAV launch tube of this utility model;
[0020] Figure 2 for Figure 1 Structural diagram of the anti-tank device and its base;
[0021] Figure 3 for Figure 2 A structural schematic diagram of the anti-ballistic device and its base from another perspective;
[0022] Figure 4 for Figure 2 A schematic diagram of the structure of the base and the gas generator;
[0023] Figure 5 for Figure 1 A schematic diagram of the middle cylinder cover.
[0024] Explanation of icon numbers:
[0025] label name label name 10 base 42 Second plate 11 Mounting base 421 Limiting groove 12 support rod 43 Connecting rod 13 quick-connect plug 50 cylinder lid 20 cylinder 51 Limiting components 30 Gas generator 60 Torsion spring 40 sabot 70 Lock pin 41 First plate 80 Limiting rope
[0026] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation
[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.
[0028] It should be noted that if the embodiments of this utility model involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicators will also change accordingly.
[0029] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text is to include three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution that simultaneously satisfies A and B. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.
[0030] This utility model proposes a drone launch tube.
[0031] In the embodiments of this utility model, such as 1 to Figure 5 As shown, the drone's launch tube,
[0032] The device includes a base 10, a cylinder 20, a gas generator 30, and a ejector device 40. The cylinder 20 is disposed on the base 10. The gas generator 30 is disposed on the base 10 and located inside the cylinder 20. The gas generator 30 is provided with a gas generating agent and an igniter. The ejector device 40 is movably disposed inside the cylinder 20. The ejector device 40 includes a first plate 41 and a second plate 42. The first plate 41 is located above the gas generator 30, and the shape of the first plate 41 matches the structure of the inner wall of the cylinder 20. The second plate 42 is fixed to the first plate 41 and located above the first plate 41. The second plate 42 is used to abut against the lower end of the drone.
[0033] Specifically, after the drone is installed in the cylinder 20, the lower end of the drone abuts against the second plate 42. When the drone is launched, the igniter inside the gas generator 30 is detonated by triggering the gas generator 30, which in turn ignites the gas generating agent inside the gas generator 30. The high-pressure gas generated at the moment of ignition enters between the base 10 and the first plate 41 through the gas generator 30, thereby pushing the first plate 41 and causing it to move at high speed toward the upper end of the cylinder 20. This causes the second plate 42 to push the drone and launch it from inside the cylinder 20.
[0034] This utility model's technical solution involves setting a cylinder 20 on a base 10 and installing a movable launcher device 40 on the cylinder 20. The launcher device 40 includes a first plate 41 and a second plate 42 fixed to each other. The shape of the first plate 41 matches the structure of the inner wall of the cylinder 20, and the shape of the second plate 42 matches the structure of the bottom of the drone. The second plate 42 is located above the first plate 41. When the drone is installed inside the cylinder 20, the second plate 42 abuts against the lower end of the drone. Then, a gas generator 30 is set on the base 10. By triggering the gas generator 30, the igniter inside the gas generator 30 is detonated, thereby igniting the gas generating agent inside the gas generator 30. The high-pressure gas generated at the moment of ignition enters between the base 10 and the first plate 41 through the gas generator 30, thereby pushing the first plate 41, causing the first plate 41 to move at high speed towards the upper end of the cylinder 20, thereby causing the second plate 42 to push the drone and launch the drone from inside the cylinder 20. Launching drones using high-pressure gas generated by the combustion of a gaseous propellant is safer than launching drones using solid fuel and pyrotechnics. The gaseous propellant produces less noise, lower temperature, and less pressure on the launch tube during triggering. Furthermore, the gas generator 30 offers greater flexibility and is more reliable and safer to store and transport.
[0035] In some embodiments, the sabot device 40 further includes a plurality of connecting rods 43 extending axially along the cylinder 20, with one end of each connecting rod 43 fixed to the first plate 41 and the other end fixed to the first plate 41. Specifically, this arrangement of multiple connecting rods 43 separates the first plate 41 and the second plate 42, thus isolating the high temperature and high pressure generated by the gas generator during combustion from the drone, preventing damage to the drone and making the drone safer during launch.
[0036] In some embodiments, the drone launch tube further includes a cover 50, which is movably mounted on the top of the tube body 20. The cover 50 has a closed position and an open position. In the closed position, the cover 50 is closed over the launch port of the tube body 20. In the open position, the cover 50 is spaced apart from the launch port of the tube body 20. Specifically, when the drone is stored in the tube body and not being launched, the cover 50 is in the closed position, sealing the tube body 20 to protect the drone and facilitate transporting the drone and the launch tube together. When the drone is being launched, the cover 50 is in the open position, avoiding obstruction of the drone and not affecting its launch.
[0037] In some embodiments, the cap 50 is provided with a limiting member 51, the shape of which matches the structure of the top of the drone. When the cap 50 is in the closed position, the limiting member 51 abuts against the top of the drone. Specifically, when the drone's inner tube 20 is transported together with the drone launch tube, the limiting member 51 abuts against the top of the drone, preventing the drone from moving relative to the inner tube 20, and further improving the safety of the drone during transport inside the drone launch tube.
[0038] In some embodiments, a torsion spring 60 is provided between the cap 50 and the cylinder 20. The torsion spring 60 has an elastic deformation that resets the cap 50 from a closed position to an open position. The cylinder 20 is provided with a movable locking pin 70. In the closed position, the locking pin 70 is inserted into the cap 50 to limit the cap 50. Specifically, when the locking pin 70 is inserted into the cap 50, the cap 50 is locked in the closed position, preventing the cap 50 from moving and affecting the cooperation between the drone and the cylinder 20 when the drone is transported inside the drone launch tube. When the drone needs to be launched, the locking pin 70 can be removed, and the torsion spring 60 resets the cap 50 from the closed position to the open position, facilitating the launch of the drone from the cylinder 20.
[0039] In some embodiments, the base 10 is provided with a plurality of support rods 12 extending along the extension direction of the cylinder 20, and a first plate 41 is placed at the upper end of the plurality of support rods 12. Specifically, the plurality of support rods 12 support the first plate 41, and the first plate 41 does not contact the gas generator 30. Compared with the structure of providing support for the first plate 41 on the inner wall of the cylinder 20, the structure of providing support rods 12 on the base 10 is simpler.
[0040] In some embodiments, the lower end of the first plate 41 is provided with multiple positioning grooves corresponding to multiple support rods 12, so that the first plate 41 is placed on the upper end of the support rods 12 through the positioning grooves, thus preventing the spring support device 40 from rotating relative to the base 10.
[0041] In some embodiments, the drone launch tube includes a limiting rope 80, the lower end of which is fixed to the base 10, and the upper end of which is connected to the lower end of the first plate 41. Specifically, this way, when the drone is launched, and the ejector device 40 pushes the drone out of the tube 20, the limiting rope 80 is connected to the lower end of the first plate 41, preventing the ejector device 40 from being pushed out of the tube 20 by high pressure.
[0042] In some embodiments, the base 10 is provided with a mounting base 11, which is detachably mounted on the base 10 from the bottom end of the base 10. The gas generator 30 is mounted on the mounting base 11, and the lower end of the limiting rope 80 is fixed to the mounting base 11. Specifically, this allows the gas generator 30 to be disassembled together with the mounting base 11 by removing it from the bottom end of the base 10, avoiding the need to first disassemble the spring support device 40 when disassembling the gas generator 30. This simplifies the operation steps and facilitates the maintenance or replacement of the gas generator 30.
[0043] In some embodiments, the cylinder 20 is detachably mounted on the base 10 using threaded fasteners. The threaded fasteners ensure a more stable installation of the cylinder 20 and the base 10, and facilitate the replacement or repair of components on the base 10 after disassembling the cylinder 20. Furthermore, the cylinder 20 is cylindrical. This ensures that the high pressure generated during drone operation is evenly distributed around the inner wall of the cylinder 20, resulting in a more stable structure.
[0044] In some embodiments, the upper end of the second plate 42 is provided with a limiting groove 421, and the drone is provided with a limiting protrusion that matches the shape of the limiting groove 421. Specifically, when the drone is inside the cylinder 20, the limiting groove 421 limits the limiting protrusion, preventing the drone from rotating relative to the second plate 42 when the second plate 42 pushes the drone, making the drone more stable during launch.
[0045] In some embodiments, the locking pin 70 is connected to a driving member, which drives the locking pin 70 to be spaced apart from the cylinder cover 50. The driving member and the gas generator 30 are both connected to an electronic control device. In this way, the electronic control device controls the gas generator 30 to spray high-pressure gas, and at the same time, the electronic control device controls the driving member to drive the locking pin 70 to be spaced apart from the cylinder cover 50, so that the torsion spring 60 drives the cylinder cover 50 to the open position. In this way, compared with manual operation, the drone launcher can launch the drone more quickly and smoothly.
[0046] In some embodiments, the base 10 is provided with a quick-connect plug 13, which connects to an external electronic control device or charging circuit. Both the first plate 41 and the second plate 42 are provided with wire holes. This allows one end of an electrical connection cable to be connected to the quick-connect plug 13, and the other end to be connected to the drone inside the cylinder 20 through the wire holes of the first plate 41 and the second plate 42, enabling communication or power supply to the drone.
[0047] The above description is only a preferred embodiment of the present utility model and does not limit the patent scope of the present utility model. All equivalent structural transformations made under the inventive concept of the present utility model using the contents of the present utility model specification and drawings, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present utility model.
Claims
1. A drone launch tube for launching drones, characterized in that, include: Base; The cylindrical body is located on the base; A gas generator is disposed on the base and located inside the cylinder. The gas generator contains a gas generating agent and an igniter. as well as A sabot is movably disposed within the cylinder. The sabot includes a first plate and a second plate. The first plate is located above the gas generator, and its shape matches the structure of the inner wall of the cylinder. The second plate is fixed to the first plate and located above it. The second plate is used to abut against the lower end of the UAV.
2. The UAV launch tube as described in claim 1, characterized in that, The ejector device also includes a plurality of connecting rods extending axially along the cylinder body, with one end of each connecting rod fixed to the first plate body and the other end fixed to the first plate body.
3. The UAV launch tube as described in claim 1, characterized in that, The drone launch tube also includes a cover, which is movably mounted on the top of the tube body. The cover has a closed position and an open position. In the closed position, the cover is closed to the launch port of the tube body. In the open position, the cover is spaced apart from the launch port of the tube body.
4. The UAV launch tube as described in claim 3, characterized in that, The cylinder cover is provided with a limiting member, the shape of which matches the structure of the top of the drone. When the cylinder cover is in the closed position, the limiting member abuts against the top of the drone.
5. The UAV launch tube as described in claim 3, characterized in that, A torsion spring is provided between the cap and the body, the torsion spring having elastic deformation to return the cap from the closed position to the open position, and the body is provided with a movable locking pin, which is inserted into the cap to limit the cap when in the closed position.
6. The UAV launch tube as described in claim 1, characterized in that, The base is provided with multiple support rods that extend along the extension direction of the cylinder, and the first plate is placed on the upper end of the multiple support rods.
7. The UAV launch tube as described in claim 6, characterized in that, The lower end of the first plate is provided with multiple positioning grooves corresponding to the multiple support rods.
8. The UAV launch tube as described in claim 1, characterized in that, The drone launch tube includes a limiting rope, the lower end of which is fixed to the base, and the upper end of which is connected to the lower end of the first plate.
9. The UAV launch tube as described in claim 8, characterized in that, The base is provided with a mounting seat, which is detachably mounted on the base from the bottom end of the base. The gas generator is mounted on the mounting seat, and the lower end of the limiting rope is fixed to the mounting seat.
10. The UAV launch tube as described in claim 1, characterized in that, The upper end of the second plate is provided with a limiting groove, and the UAV is provided with a limiting protrusion that matches the shape of the limiting groove.