Pneumatic launcher mounted on unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicle load equipment, and provides an unmanned aerial vehicle mounted pneumatic launcher which comprises a box body connected with an unmanned aerial vehicle through a support, an air compression device and a launching device are arranged in the box body, the air compression device comprises an air cylinder and a first motor, and the launching device comprises an air storage tank. The air cylinder is connected with an air inlet pipe with one-way air inlet, the air outlet end of the air cylinder is communicated with the air storage tank through an air guide pipe, the air outlet end of the air storage tank is sequentially connected with an electromagnetic valve and a launching pipe extending out of the box body, and the first motor is connected with a piston arranged in the air cylinder through a gear set and used for driving the piston to reciprocate so as to inject air into the air storage tank in a one-way mode. The piston is driven by the first motor to do reciprocating motion, air is continuously injected into the air storage tank, the air pressure needed by launching is guaranteed, after the air pressure in the air storage tank reaches a preset value, the electromagnetic valve is opened, high-pressure air is ejected out of the launching pipe, a launched object is rapidly pushed to be delivered to a target position, and the delivery precision and reliability are improved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) payload equipment technology, and more specifically, to a pneumatic launcher mounted on a UAV. Background Technology

[0002] Drone technology has developed rapidly in recent years and is widely used in military, civilian, and commercial fields. In scenarios such as logistics, emergency rescue, agricultural plant protection, and military reconnaissance, drone delivery has become an efficient and flexible technological means. However, current drone delivery methods mainly rely on multi-rotor drones flying to the delivery area for vertical drop. In actual use, multi-rotor drones can only release their payload above the target, allowing the object to fall vertically solely due to gravity. This has many limitations. For example, delivery can be hindered when there are obstructions directly above the target; furthermore, the acceleration of the dropped object is only affected by gravity, resulting in a long descent time and susceptibility to airflow, causing deviations from the intended trajectory and leading to poor delivery accuracy and even inaccurate delivery, thus affecting the precision and reliability of the delivery. Utility Model Content

[0003] The purpose of this invention is to provide a pneumatic launcher for drones, which solves the problems of poor delivery accuracy and reliability of existing drones.

[0004] This utility model is achieved through the following technical solution: a pneumatic launcher mounted on a drone, comprising a box connected to the drone via a bracket, a compressor and a launcher inside the box, the compressor comprising a cylinder and a first motor, the launcher comprising an air tank, the cylinder being connected to a one-way air inlet pipe, the cylinder outlet being connected to the air tank via an air guide pipe, the air tank outlet being sequentially connected to a solenoid valve and a launcher extending out of the box, the first motor being connected to a piston inside the cylinder via a gear set, for driving the piston to reciprocate to inject air one-way into the air tank.

[0005] Furthermore, the gear set includes a driving gear, a reduction gear, and a cam shaft gear. The driving gear is coaxially connected to the output shaft of the first motor. The reduction gear includes a large-diameter gear and a small-diameter gear arranged coaxially. The large-diameter gear meshes with the driving gear, the small-diameter gear meshes with the cam shaft gear, and the piston end is eccentrically connected to the cam shaft gear.

[0006] Furthermore, the bracket includes a connecting frame that snaps onto the drone and a frame that connects to both sides of the box.

[0007] Furthermore, a second motor for driving the box to rotate is provided on the connecting frame, and a third motor for driving the box to pitch is provided on the frame.

[0008] Furthermore, a cooling fan is connected to the output shaft of the first motor, and the housing has ventilation holes directly opposite the air outlet of the cooling fan.

[0009] Furthermore, the gas storage tank is connected to a pressure relief pipe, and a pressure valve is installed on the pressure relief pipe.

[0010] Furthermore, the gas storage tank is connected to a pressure sensor, and the box contains a laser rangefinder and an optical camera.

[0011] Furthermore, one-way valves are installed on the intake pipe and the duct pipe respectively.

[0012] This utility model has at least the following advantages and beneficial effects: the piston is driven by the first motor to reciprocate and continuously inject air into the gas tank to ensure the air pressure required for launch. After the air pressure in the gas tank reaches the predetermined value, the solenoid valve is opened to eject high-pressure air from the launch tube, which quickly pushes the launch object to the target position, thus improving the launch accuracy and reliability. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the structure of a pneumatic launcher mounted on a drone, which is provided by this utility model.

[0014] Figure 2 A side view of a pneumatic launcher mounted on a drone, provided by this utility model.

[0015] Figure 3 This utility model provides a schematic diagram of the internal structure of the housing of a pneumatic launcher mounted on a drone.

[0016] Figure 4 This utility model provides a top view of the internal structure of the housing of a pneumatic launcher mounted on a drone.

[0017] Figure 5 This utility model provides a schematic diagram of the launching device in a pneumatic launcher mounted on a drone.

[0018] Figure 6 A side view of the compressed air device in a pneumatic launcher mounted on a drone, provided by this utility model.

[0019] Figure 7 An exploded view of the compressed air device in a pneumatic launcher mounted on a drone, provided by this utility model.

[0020] Figure 8 This utility model provides a structural schematic diagram of the support structure in a pneumatic launcher mounted on a drone.

[0021] Reference numerals: 1-Bracket, 11-Connecting frame, 12-Frame, 13-Second motor, 14-Third motor, 2-Box, 20-Heat dissipation hole, 21-Partition plate, 22-Laser rangefinder sensor, 23-Optical camera, 24-Main control circuit board, 25-Display screen, 26-Regulator, 3-Compressor, 31-Cylinder, 311-Piston, 32-First motor, 33-Inlet pipe, 34-Cooling fan, 4-Emitting device, 41-Air tank, 42-Solenoid valve, 43-Emitting tube, 44-Pressure relief pipe, 45-Pressure valve, 46-Pressure sensor, 5-Air guide pipe, 6-Gear set, 61-Driving gear, 62-Reduction gear, 621-Large diameter gear, 622-Small diameter gear, 63-Cam shaft gear. Detailed Implementation

[0022] The specific implementation method is described below with reference to the accompanying drawings.

[0023] Example

[0024] like Figures 1 to 8 As shown, this embodiment mainly discloses a pneumatic launcher mounted on a drone, including a housing 2 connected to the drone via a bracket 1. The housing 2 contains a compressor 3 and a launcher 4. The compressor 3 includes a cylinder 31 and a first motor 32, and the launcher 4 includes an air tank 41. The cylinder 31 is connected to a one-way air inlet pipe 33, and the outlet of the cylinder 31 is connected to the air tank 41 via an air guide pipe 5. The outlet of the air tank 41 is sequentially connected to a solenoid valve 42 and a launch pipe 43 extending outside the housing 2. The first motor 32 is connected to a piston 311 inside the cylinder 31 via a gear set 6, driving the piston 311 to reciprocate and inject air unidirectionally into the air tank 41. Specifically, integrating the compressor 3 and the launcher 4 within the housing 2 results in a compact structure and reduces the need for external piping. The piston 311 is driven by the first motor 32 to reciprocate. Air is drawn into the cylinder 31 from the air inlet pipe 33 and then pressed into the air storage tank 41 by the piston 311. This process is repeated to continuously inject air into the air storage tank 41 to ensure the air pressure required for launch. When the air pressure in the air storage tank 41 reaches the predetermined value, the solenoid valve 42 is opened, and high-pressure air is ejected from the launch pipe 43, which quickly propels the launch object to the target position, improving the launch accuracy and reliability.

[0025] Furthermore, in specific implementation, such as Figure 4 , Figure 6 and Figure 7As shown, the gear set 6 provided in this embodiment of the present invention includes a driving gear 61, a reduction gear 62, and a cam shaft gear 63. The driving gear 61 is coaxially connected to the output shaft of the first motor 32. The reduction gear 62 includes a large-diameter gear 621 and a small-diameter gear 622 arranged coaxially. The large-diameter gear 621 meshes with the driving gear 61, and the small-diameter gear 622 meshes with the cam shaft gear 63. The end of the piston 311 is eccentrically connected to the cam shaft gear 63. Specifically, the reduction gear 62 and the cam shaft gear 63 are rotatably connected to the partition 21 provided in the housing. Through the cooperation of the driving gear 61, the reduction gear 62, and the cam shaft gear 63, the high-speed rotation of the first motor 32 is converted into the reciprocating motion of the piston 311, while increasing the torque, which is suitable for the generation of high-pressure gas.

[0026] Furthermore, in specific implementation, such as Figure 1 , Figure 2 and Figure 8 As shown, the bracket 1 provided in this embodiment of the present invention includes a connecting frame 11 that snaps onto the drone and a frame 12 that connects to both sides of the housing 2. The bracket 1 connects the housing 2 to the drone, achieving a modular design that facilitates installation, disassembly, and maintenance. Specifically, the connecting frame 11 extends upwards from the middle of the frame 12 to the center of the housing, ensuring the stability of the pneumatic launcher. The connecting frame 11 uses a snap-on connection method, facilitating quick installation and disassembly and improving the drone's mounting efficiency. The frame 12 is semi-frame-shaped and connects to both sides of the housing 2, increasing the overall structural stability and reducing vibration and shaking during launch.

[0027] Preferably, a second motor 13 for driving the rotation of the housing 2 is provided on the connecting frame 11, and a third motor 14 for driving the pitch of the housing 2 is provided on the frame 12. Specifically, the main body of the second motor 13 is fixed to the connecting frame, and its output shaft is connected to the UAV; the main body of the third motor 14 is fixed to the frame 12, and its output shaft is connected to the housing 2. By driving the rotation of the housing 2 with the second motor 13 and driving the pitch of the housing 2 with the third motor 14, multi-degree-of-freedom adjustment of the launch angle is achieved, improving launch accuracy and adaptability.

[0028] Furthermore, in specific implementation, such as Figure 6 and Figure 7 As shown, a cooling fan 34 is connected to the output shaft of the first motor 32 provided in this embodiment of the invention, and a heat dissipation hole 20 is provided in the housing 2 directly opposite the air outlet of the cooling fan 34. The cooling fan 34 can effectively reduce the working temperature inside the housing 2, preventing overheating due to prolonged operation and improving the reliability and service life of the system. In addition, the cooling fan 34 is directly driven by the output shaft of the first motor 32 while driving the piston 311, eliminating the need for an additional power source and achieving energy saving and high efficiency.

[0029] Furthermore, in specific implementation, such as Figure 5 As shown, the gas storage tank 41 provided in this embodiment of the present invention is connected to a pressure relief pipe 44, and a pressure valve 45 is provided on the pressure relief pipe 44. The pressure relief pipe 44 and the pressure valve 45 can automatically relieve pressure when the pressure inside the gas storage tank 41 is too high, preventing damage to the gas storage tank 41 due to overpressure and improving the safety of the system. At the same time, by adjusting the setting value of the pressure valve 45, the maximum pressure inside the gas storage tank 41 can be controlled to adapt to different launch requirements.

[0030] Furthermore, in specific implementation, such as Figure 5 As shown, the air tank 41 provided in this embodiment of the present invention is connected to a pressure sensor 46, and the housing 2 is equipped with a laser rangefinder 22 and an optical camera 23. Specifically, the housing 2 is equipped with a main control circuit board 24, a display screen 25, and an regulator 26. The pressure sensor 46 is electrically connected to the display screen 25 to display the air pressure in the air tank 41 in real time, so that the operator can easily grasp the system status. At the same time, the pressure sensor 46 is electrically connected to the pressure valve 45 through the main control circuit board 24. When the air pressure exceeds the set threshold, the pressure valve 45 is controlled to release air through the pressure relief pipe 44. In addition, the regulator 26 can set the air pressure intensity of the air tank 41 through the main control circuit board 24. Different air pressure intensities correspond to different launch distances. Combined with the ranging information of the laser rangefinder 22, the purpose of precise launch can be achieved. In use, after the transmitter is mounted on the drone and powered on, the air pressure intensity is set through the regulator 26. The first motor 32 drives the piston 311 to move back and forth to inject air into the air tank 41. After the set air pressure is reached, the first motor 32 is turned off. Once the drone reaches the designated location, it transmits images back via the optical camera 23, controls the second motor 13 and the third motor 14 to adjust the rotation and pitch of the housing 2, so that the launch tube 43 is facing the target position. Based on the ranging information of the laser rangefinder 22, it adjusts the air pressure of the air tank 41 appropriately, and then activates the solenoid valve 42 to launch the object.

[0031] Furthermore, in specific implementations, one-way valves are respectively provided on the air inlet pipe 33 and the air guide pipe 5 provided in this embodiment of the present invention. The one-way valves prevent gas backflow during the compression process, thereby improving compression efficiency. Through the control of the one-way valves, the unidirectionality of gas flow is ensured, avoiding the impact of pressure fluctuations on system stability.

Claims

1. A pneumatic launcher mounted on a drone, characterized in that, The device includes a box (2) connected to the drone via a bracket (1), and the box (2) is equipped with a compressor (3) and a launcher (4). The compressor (3) includes a cylinder (31) and a first motor (32), and the launcher (4) includes an air tank (41). The cylinder (31) is connected to a one-way air intake pipe (33). The air outlet of the cylinder (31) is connected to the air storage tank (41) through an air guide pipe (5). The air outlet of the air storage tank (41) is connected in sequence to a solenoid valve (42) and a launching pipe (43) extending out of the box body (2). The first motor (32) is connected to the piston (311) set in the cylinder (31) through a gear set (6) to drive the piston (311) to reciprocate to inject air into the air storage tank (41) in one direction.

2. The pneumatic launcher mounted on a UAV according to claim 1, characterized in that, The gear set (6) includes a drive gear (61), a reduction gear (62), and a cam shaft gear (63). The drive gear (61) is coaxially connected to the output shaft of the first motor (32). The reduction gear (62) includes a large diameter gear (621) and a small diameter gear (622) arranged coaxially. The large diameter gear (621) meshes with the drive gear (61), and the small diameter gear (622) meshes with the cam shaft gear (63). The end of the piston (311) is eccentrically connected to the cam shaft gear (63).

3. The pneumatic launcher mounted on a UAV according to claim 1, characterized in that, The bracket (1) includes a connecting frame (11) that is fastened to the drone and a frame (12) that is fastened to both sides of the box (2).

4. A pneumatic launcher mounted on a UAV according to claim 3, characterized in that, The connecting frame (11) is provided with a second motor (13) for driving the box (2) to rotate, and the frame (12) is provided with a third motor (14) for driving the box (2) to pitch.

5. A pneumatic launcher mounted on a UAV according to claim 1, characterized in that, A cooling fan (34) is connected to the output shaft of the first motor (32), and the housing (2) has a heat dissipation hole (20) at the air outlet position of the cooling fan (34).

6. A pneumatic launcher mounted on a UAV according to claim 1, characterized in that, The gas storage tank (41) is connected to a pressure relief pipe (44), and a pressure valve (45) is installed on the pressure relief pipe (44).

7. A pneumatic launcher mounted on a UAV according to claim 1, characterized in that, The gas storage tank (41) is connected to a pressure sensor (46), and the box (2) is equipped with a laser rangefinder (22) and an optical camera (23).

8. A pneumatic launcher mounted on a UAV according to claim 1, characterized in that, One-way valves are respectively provided on the air inlet pipe (33) and the air guide pipe (5).

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