High-altitude controllable launching device of multi-rotor unmanned aerial vehicle

Abstract

The high-altitude controllable launching device comprises a supporting frame, a launching tube is fixed to the front end of the supporting frame, a first cylinder body is fixed to the rear end of the launching tube, a second cylinder body is arranged at the rear end of the first cylinder body in a sliding mode, a bullet inlet is formed in the launching tube, and a bullet outlet is formed in the rear end of the second cylinder body. A bullet bin is arranged above the bullet inlet, a sealing piece is arranged between the launching tube and the bullet bin in a sliding mode, the sealing piece is fixedly connected with a second cylinder body, a reset spring is arranged between the second cylinder body and the supporting frame, and the second cylinder body is connected with a driving mechanism driving the second cylinder body to move backwards. Compared with the prior art, the bullet is launched through compressed air, the bullet cannot be cracked up, the bullet inlet is sealed during launching, and the launching effect is guaranteed. And secondly, linkage is achieved between the second cylinder body and the sealing piece, filling of the projectile and sealing of the projectile inlet are synchronously completed when energy storage and energy release of the spring are completed, and the overall structure becomes simpler.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle (UAV) material launching, in particular to a high-altitude controllable launching device for a multi-rotor UAV. Background Art

[0002] In recent years, with the advancement of drone technology, multi-rotor drones have become increasingly important across various industries. Their advantages, such as compact size, excellent controllability, large payload capacity, low takeoff and landing requirements, and high cost-effectiveness, have led to a growing number of applications and significant progress. Currently, multi-rotor drones are widely used in low- and medium-altitude areas, such as emergency rescue, firefighting, and medical services. Performing specialized operations from the air can complement ground-based operations in complex terrain, hazardous environments, and unpredictable environments. Remote aerial delivery, launch, or replenishment can maximize the safety of equipment in these specialized operations, minimize secondary hazards, improve operational efficiency, increase equipment's effective airborne time and delivery density, enhance operational capabilities, rapidly respond to diverse application scenarios, and enhance drones' ability to adapt to diverse missions. Therefore, the emergence of high-altitude controllable launch systems for multi-rotor drones, capable of rapid delivery, continuous launch, and instant replenishment, can effectively enhance and expand the application and efficiency of drones in specialized operations, effectively ensuring equipment safety and reducing personnel exposure to unknown risks. Patent application publication number CN114408180A discloses a fire extinguishing bomb storage device for firefighting drones. The device includes a drone body, a magazine located below the drone body, and a connecting assembly that securely connects the magazine to the bottom of the drone body. The magazine has partitions fixedly installed at equal intervals within the magazine cavity. The space formed between the partitions and the magazine's inner wall stores the fire extinguishing bomb body. An ejection assembly is fixedly installed at the bottom of the magazine. This solution uses a compressed spring to drive a push block, thereby ejecting the fire extinguishing bomb body from the ejection slot. However, the push block is in hard contact with the fire extinguishing bomb body, which could damage the material (fire extinguishing bomb body). Utility Model Content

[0003] The utility model provides a high-altitude controllable launching device for a multi-rotor UAV, which is used to solve the problem that materials may be damaged when materials are launched by a conventional UAV through a compression spring-driven push block.

[0004] The utility model provides a high-altitude controllable launching device for a multi-rotor unmanned aerial vehicle, comprising a supporting frame, a launching tube being fixed at the front end of the supporting frame, a first cylinder being fixed at the rear end of the launching tube, a second cylinder being slidably arranged at the rear end of the first cylinder, a bullet feed port being provided on the launching tube, a bullet magazine being provided above the bullet feed port, a sealing member being slidably arranged between the launching tube and the bullet magazine, the sealing member being fixedly connected to the second cylinder, a reset spring being provided between the second cylinder and the supporting frame, and the second cylinder being connected to a driving mechanism for driving the second cylinder to move backward.

[0005] Preferably, the driving mechanism includes: a rack, a sector gear and a driving motor, the rack is fixed on the second cylinder body, the output shaft of the driving motor is fixed to the sector gear, and the sector gear cooperates with the rack.

[0006] Preferably, the sealing member is provided with a feeding hole cooperating with the bullet feed port and the bullet magazine.

[0007] Preferably, a plurality of sliding rods are fixed on the support frame, the second cylinder body is slidably connected to the sliding rods, and the return spring is arranged on the sliding rods between the second cylinder body and the support frame.

[0008] Preferably, a first transmission shaft is rotatably provided on the support frame, the two sector gears are respectively fixed at both ends of the first transmission shaft, and the distance between the slide rod and the second cylinder body is smaller than the distance between the rack and the second cylinder body.

[0009] Preferably, a second transmission shaft is further included, and a first bevel gear and a second bevel gear are fixed on the first transmission shaft and the second transmission shaft respectively, the first bevel gear and the second bevel gear are meshed with each other, and the output shaft of the drive motor is fixed to the second transmission shaft.

[0010] Preferably, a motor seat is fixed on the support frame, and the driving motor and the sliding rod are both fixed on the motor seat.

[0011] Preferably, the first cylinder is fixed to the support frame via a first support, and the sliding rod is fixed to the first support.

[0012] Preferably, the sealing member is fixed to the second cylinder body via a connecting plate, and the connecting plate passes through the first support.

[0013] Preferably, a slide groove is provided on the launch tube, and the sealing member is provided with a slider that cooperates with the slide groove, and the slider slides along the slide groove.

[0014] Compared to existing technologies, the present invention uses compressed gas to launch the projectile, preventing damage to the projectile. The feed port is sealed during launch, ensuring effective launch. Furthermore, the second cylinder and seal are linked, allowing for simultaneous loading of the projectile and sealing of the feed port during spring energy storage and release, simplifying the overall structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0016] Figure 1 It is a structural diagram of the utility model;

[0017] Figure 2 It is a partial structural diagram of the utility model;

[0018] Figure 3 for Figure 2 Schematic diagram of the structure after removing the support frame;

[0019] Figure 4 This is a structural diagram of the sealing element of the present invention;

[0020] Figure 5 This is a schematic structural diagram of the launch tube of the present invention.

[0021] Reference numerals:

[0022] 1. Support frame, 2. Launch tube, 021. Bullet feed port, 022. Slide, 3. First cylinder, 4. Second cylinder, 5. Magazine, 6. Seal, 061. Feed hole, 7. Slide, 8. Rack, 9. Sector gear, 10. Drive motor, 11. Slide rod, 12. First transmission shaft, 13. Second transmission shaft, 14. First bevel gear, 15. Second bevel gear, 16. Motor base, 17. First support, 18. Connecting rod, 100. Drive mechanism. DETAILED DESCRIPTION

[0023] To make the purpose, technical solutions, and advantages of the present invention more clear, the following will be combined with the accompanying drawings to clearly and completely describe the technical solutions of the present invention. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0024] Refer to the attached Figure 1 and attached Figure 3This embodiment provides a high-altitude controllable launch device for a multi-rotor unmanned aerial vehicle, comprising a support frame 1, a launch tube 2 fixed at the front end of the support frame 1, a first cylinder 3 fixed at the rear end of the launch tube 2, a second cylinder 4 slidably mounted at the rear end of the first cylinder 3, the first cylinder 3 and the second cylinder 4 forming an air chamber, the air intake duct of which is provided with a one-way valve; a bullet feed port 021 is provided on the launch tube 2, a magazine 5 is provided above the bullet feed port 021, the magazine 5 is fixed to the support frame 1, a seal 6 is slidably mounted between the launch tube 2 and the magazine 5, the bullet feed port 021 is opened by sliding the seal 6 to allow the materials (e.g., bullets) in the magazine 5 to fall into the launch tube 2; or the bullet feed port 021 is sealed during launch to prevent leakage of compressed gas. The seal 6 is fixedly connected to the second cylinder 4, a return spring (not shown) is provided between the second cylinder 4 and the support frame 1, and the second cylinder 4 is connected to a drive mechanism 100 for driving it backward. In the present invention, the driving mechanism 100 drives the second cylinder 4 to move backward, driving the sealing member 6 to move backward. While the sealing member 6 seals the bullet inlet 021, the second cylinder 4 compresses the return spring. During firing, the driving mechanism 100 no longer drives the second cylinder 4. The elastic force of the return spring drives the second cylinder 4 to slide forward, and the air in the air chamber is compressed and then ejected toward the launch tube 2, launching the projectile in the launch tube 2. During this process, the second cylinder 4 drives the sealing member 6 to slide forward. After the projectile is launched, the sealing member 6 continues to slide forward until the bullet inlet 021 is exposed. The projectile in the magazine 5 falls into the launch tube 2, ready for the next launch. Compared to existing hard contact launch methods, the present invention launches the projectile through compressed gas, which will not damage the projectile. The bullet inlet 021 is sealed during launch, ensuring the launch effect. Secondly, the second cylinder body 4 and the sealing member 6 are linked to simultaneously complete the loading of the projectile and the sealing of the feed port 021 when completing the spring energy storage and energy release, making the overall structure simpler.

[0025] An embodiment of the driving mechanism 100: Figure 2 The drive mechanism 100 includes a rack 8, a sector gear 9 (some of the gear teeth are not removed in the figure), and a drive motor 10. The rack 8 is fixed to the second cylinder 4. The output shaft of the drive motor 10 is fixed to the sector gear 9, and the sector gear 9 cooperates with the rack 8. The drive motor 10 drives the sector gear 9 to rotate. When the sector gear 9 contacts and meshes with the rack 8, the sector gear 9 continues to rotate, driving the rack 8 to move backward. The movement of the rack 8 drives the second cylinder 4 to slide backward, and the backward sliding of the second cylinder 4 compresses the return spring. During launch, the sector gear 9 rotates, and the sector gear 9 and rack 8 transition from an engaged state to a disengaged state. The elastic force of the return spring drives the second cylinder 4 forward, and then the projectile in the launch tube 2 is launched by compressed air. The rack 8 returns to its initial position, waiting for the next engagement of the sector gear 9.

[0026] As another embodiment of the present invention, a sealing member 6 is provided with a feed hole 061 that cooperates with the bullet feed port 021 and the magazine 5. The sealing member 6 includes a tubular sliding portion, on which the feed hole 061 is disposed. When the sealing member 6 slides and the feed hole 061 is directly above the bullet feed port 021, the discharge port of the magazine 5 communicates with the bullet feed port 021 through the feed hole 061. When the feed hole 061 is not above the bullet feed port 021, the sealing member 6 seals the bullet feed port 021.

[0027] In another embodiment of the present invention, multiple slide rods 11 are fixed to the support frame 1, the second cylinder 4 is slidably connected to the slide rods 11, and a return spring is provided on the slide rods 11 between the second cylinder 4 and the support frame 1. This structural design allows for the installation of multiple return springs, thereby achieving a greater elastic force. Specifically, the sliding sleeve 7 is fixed to the second cylinder 4, and the return spring is provided between the sliding sleeve 7 and the support frame 1. When the sliding sleeve 7 slides backward along the slide rod 11, it compresses the return spring.

[0028] Specifically, there are three sliding bars 11 , and the three sliding bars 11 are distributed in an inverted T shape.

[0029] As another embodiment of the present utility model: a first transmission shaft 12 is rotatably provided on the support frame 1, two sector gears 9 are respectively fixed at both ends of the first transmission shaft 12, the distance between the slide rod 11 and the second cylinder body 4 is smaller than the distance between the rack 8 and the second cylinder body 4, and the two racks 8 are fixed on both sides of the second cylinder body 4 through support arms.

[0030] As another embodiment of the present invention, this embodiment further includes a second transmission shaft 13. A first bevel gear 14 and a second bevel gear 15 are respectively fixed to the first transmission shaft 12 and the second transmission shaft 13. The first bevel gear 14 and the second bevel gear 15 are meshed with each other. The output shaft of the drive motor 10 is fixed to the second transmission shaft 13 via a reduction mechanism. With this structural design, the drive motor 10 is located at the rear end of the support frame 1, the magazine 5 is located at the front end, and the first cylinder 3 and the second cylinder 4 are located in the middle. The entire structure is rationally distributed, avoiding a top-heavy phenomenon.

[0031] As another embodiment of the present invention: a motor base 16 is fixed on the support frame 1, and the drive motor 10 and the slide rod 11 are both fixed on the motor base 16. Specifically, the motor base 16 is fixed to the support frame 1 through a second support, and the rear end of the slide rod 11 is fixed to the second support.

[0032] As another embodiment of the present invention: the first cylinder body 3 is slidably disposed in the second cylinder body 4 .

[0033] As another embodiment of the present invention, the first cylinder body 3 is fixed to the support frame 1 through the first support 17 , and the front end of the slide rod 11 is fixed to the first support 17 .

[0034] In another embodiment of the present invention, the seal 6 is secured to the second cylinder 4 via a connecting rod 18, which passes through a first support 17. The first support 17 has a clearance hole through which the connecting rod 18 passes. The second cylinder 4 is arranged in three layers from the inside out: the connecting rod 18 is located in the inner layer, the slide rod 11 is located in the middle layer, and the rack 8 is located in the outer layer.

[0035] As another embodiment of the present invention: Figure 5 The launch tube 2 is provided with a slide groove 022, the seal 6 is provided with a slider that cooperates with the slide groove 022, the slider slides along the slide groove 022, the slider is fixed on the sliding part, and the connecting rod 18 is fixed on the sliding part.

[0036] As another embodiment of the present invention: Figure 4 The rear end of feed hole 061 is notched, and a guide plate is located within feed hole 061. As the slider slides forward, the pellets land on the guide plate. As the slider continues to slide forward, the guide plate clears feed port 021, allowing the pellets to fall into launch tube 2. When launch tube 2 is fully loaded with pellets, the slider moves backward, inserting the guide plate between the upper and lower pellets, lifting the upper pellet and preventing the pellets at the bottom of magazine 5 from being damaged by the slider's backward movement.

[0037] As another embodiment of the present invention: a protective shell is fixed on the support frame 1, and the drive motor 10, the second transmission shaft 13, the first bevel gear 14, the second bevel gear 15 and the slide rod 11 are all located below the protective shell.

[0038] In the present invention, the drive motor 10 drives the sector gear 9 to rotate via the first bevel gear 14 and the second bevel gear 15. In the first stage, the sector gear 9 rotates more than half a circle (assuming two-thirds of a circle) before contacting the rack 8. In the second stage, the sector gear 9 continues to rotate, meshing with the rack 8, driving the rack 8 backward, thereby driving the second cylinder 4 backward. The sliding sleeve 7 of the second cylinder 4 compresses the return spring. At the same time, the air chamber formed by the second cylinder 4 and the first cylinder 3 begins to inhale air, and the seal 6 connected to the second cylinder 4 also slides backward to seal the bullet inlet 021. When the sector gear 9 is about to rotate the remaining one-third of a circle, the second cylinder 4 has reached its maximum backward travel, the inhaled air has reached its maximum volume, and the return spring has completed the energy storage and compression and is ready for release. When it is necessary to launch, the drive motor 10 drives the sector gear 9 to rotate. The rotation of the sector gear 9 re-enters the first stage. The sector gear 9 loses the meshing effect with the gear. The return spring begins to release the compression force, driving the second cylinder body 4 to slide forward. The second cylinder body 4 compresses the gas in the air chamber. The compressed gas pushes the projectile out when passing through the narrow space in the launch tube 2, completing the launch. In the second stage, the second cylinder body 4 drives the seal 6 to slide forward. When it slides to half the stroke, the projectile has completely left the launch tube 2. The subsequent pressure relief stage will be entered. When the seal 6 runs to the two-thirds stroke position, the bullet feed port 021 will be gradually opened, and the internal gas pressure will be released. After the seal 6 has completed all the movements, the bullet feed port 021 is fully opened, and the projectile in the magazine 5 falls into the launch tube 2 by gravity to complete the loading and start the next launch.

[0039] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A high-altitude controllable launch device for a multi-rotor UAV, characterized in that: It includes a support frame, a launch tube is fixed to the front end of the support frame, a first cylinder is fixed to the rear end of the launch tube, a second cylinder is slidably provided on the rear end of the first cylinder, a bullet feed port is provided on the launch tube, a magazine is provided above the bullet feed port, a seal is slidably provided between the launch tube and the magazine, the seal is fixedly connected to the second cylinder, a return spring is provided between the second cylinder and the support frame, and the second cylinder is connected to a driving mechanism that drives it to move backward.

2. The multi-rotor UAV high-altitude controllable launch device according to claim 1, characterized in that: The driving mechanism includes: a rack, a sector gear and a driving motor. The rack is fixed on the second cylinder body. The output shaft of the driving motor is fixed to the sector gear. The sector gear cooperates with the rack.

3. The high-altitude controllable launch device for a multi-rotor UAV according to claim 1, characterized in that: The sealing member is provided with a feeding hole which cooperates with the bullet feed port and the bullet magazine.

4. The high-altitude controllable launch device for a multi-rotor UAV according to claim 2, characterized in that: A plurality of sliding rods are fixed on the support frame, the second cylinder body is slidably connected to the sliding rods, and the return spring is arranged on the sliding rods between the second cylinder body and the support frame.

5. The multi-rotor UAV high-altitude controllable launch device according to claim 4, characterized in that: A first transmission shaft is rotatably provided on the support frame, and the two sector gears are respectively fixed at both ends of the first transmission shaft. The distance between the slide rod and the second cylinder body is smaller than the distance between the rack and the second cylinder body.

6. The multi-rotor UAV high altitude controllable launch device according to claim 5, characterized in that: It also includes a second transmission shaft, on which a first bevel gear and a second bevel gear are fixed respectively, the first bevel gear and the second bevel gear are meshed with each other, and the output shaft of the drive motor is fixed to the second transmission shaft.

7. The multi-rotor UAV high altitude controllable launch device according to claim 6, characterized in that: A motor seat is fixed on the support frame, and the driving motor and the sliding rod are both fixed on the motor seat.

8. The high-altitude controllable launch device for a multi-rotor UAV according to claim 7, characterized in that: The first cylinder is fixed on the support frame through a first support, and the sliding rod is fixed on the first support.

9. The high-altitude controllable launch device for a multi-rotor UAV according to claim 8, characterized in that: The sealing member is fixed to the second cylinder body via a connecting plate, and the connecting plate passes through the first support.

10. The high-altitude controllable launch device for a multi-rotor UAV according to claim 1, characterized in that: The launch tube is provided with a slide groove, and the sealing member is provided with a slider matched with the slide groove, and the slider slides along the slide groove.

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