Pneumatic launching system of folding wing unmanned aerial vehicle

Abstract

The utility model discloses a folding wing unmanned aerial vehicle pneumatic launching system which comprises a launching cylinder, an electromagnetic valve and an air storage tank, a supporting rod assembly is arranged at the front end of the launching cylinder, a supporting seat is arranged at the rear end of the launching cylinder, a rear supporting assembly used for pushing a folding wing unmanned aerial vehicle is movably arranged in the launching cylinder, and the rear end of the launching cylinder is connected with the electromagnetic valve through an elbow. The other end of the air storage tank is connected with an air compressor through a quick connector. The launching cylinder type design is adopted, energy is released instantly through compressed air, more reliable and stable launching power is provided for launching of the unmanned aerial vehicle, the problems that the flight attitude of the unmanned aerial vehicle is out of control and the like due to the fact that the launching mode of the unmanned aerial vehicle is unstable and launching power is insufficient are greatly solved, and the success rate of launching of the unmanned aerial vehicle is increased; meanwhile, the closed launching cylinder is adopted as a launching track, safety is higher, reliability is good, and the situation that operators are injured can be effectively prevented.

Description

Technical Field

[0001] This utility model relates to the field of pneumatic catapult technology, and in particular to a pneumatic launch system specifically for folding-wing drones. Background Technology

[0002] In recent years, with the continuous expansion of the drone market, the drone industry has developed rapidly, and its application scope has become increasingly wide, being used in many fields such as emergency rescue, aerial photography, security monitoring, environmental monitoring, and power line inspection. Different types and purposes of drones have different launch methods, commonly including hand-launching, airborne delivery, vehicle-mounted launch, catapult launch, and rocket booster. In recent years, aerodynamic catapult technology has received widespread attention and application in drone takeoff and the launch of other equipment. This launch method is suitable for launching folding-wing drones, using compressed air to instantly release energy to power the drone's launch, offering advantages such as good safety and stealth, good economy, and good adaptability. However, existing aerodynamic catapult systems or devices used for folding-wing drones suffer from low launch accuracy, poor directionality, low efficiency, and significant susceptibility to environmental influences.

[0003] For example, patent document CN107352041A discloses a pneumatic launch device for unmanned aerial vehicles (UAVs), including a base, a launch carriage, a launch tube, an air tank, and a solenoid valve. The front end of the launch tube is connected to the launch carriage via a piston rod. The launch carriage is mounted in a groove on the base via pulleys. A buffer device is provided at the front end of the upper surface of the base, and a tripod with a lifting rod is provided at the front end of the base. The tripod is used to adjust the launch angle of the UAV. The control system controls the air tank to inflate the launch tube. During launch, the launch carriage moves along the base, propelling the UAV into the air. The buffer device stops the launch carriage. In this launch device, the groove on the base serves as the launch track for the UAV. Both the launch carriage and the base are exposed to the outside, making the launch of the UAV susceptible to interference from the external environment. Furthermore, the launch accuracy is low, the directionality is poor, and the launch power cannot be adjusted. Therefore, it is necessary to optimize the structure of existing pneumatic launch devices for UAVs to increase launch stability and make the launch power adjustable to suit different types of folding-wing UAVs. Utility Model Content

[0004] The purpose of this invention is to provide a pneumatic launch system for unmanned aerial vehicles (UAVs) to solve the problems and defects existing in the background technology.

[0005] To achieve the above objectives, the following technical solution is provided:

[0006] A pneumatic launch system for a folding-wing drone includes a launch tube, a solenoid valve, and an air tank. A support rod assembly is provided at the front end of the launch tube, and a support base is provided at the rear end of the launch tube. A rear support assembly for pushing the folding-wing drone is movably disposed inside the launch tube. The rear end of the launch tube is connected to the solenoid valve via an elbow. The other end of the solenoid valve is connected to the air tank, and the other end of the air tank is connected to an air compressor via a quick connector.

[0007] Preferably, a reinforcing ring is provided at the rear end of the launch tube. The reinforcing ring is connected to the solenoid valve via a flange and an elbow, and the support base is rotatably connected to the side wall of the flange via bolts. The reinforcing ring can be used to increase the strength of the launch tube.

[0008] Preferably, the rear support assembly includes a circular support plate, the sidewall of which is tightly fitted to the inner wall of the launch tube. Four limiting grooves are provided on the top surface of the circular support plate, and push rods are inserted into the limiting grooves. The front parts of the four push rods are fixed together by a connecting assembly. A first bracket is fixedly connected to the front end of each push rod, and a first socket is installed on the first bracket. The first socket is used to connect to a first plug on the fuselage of the folding wing UAV.

[0009] The circular support plate is equivalent to a piston cylinder and fits tightly against the inner wall of the launch tube. A sealed cavity is formed between the circular support plate, the launch tube, and the flange. Injecting compressed air into the cavity can push the rear support assembly to move along the axis of the launch tube, thereby propelling the UAV to launch.

[0010] Preferably, a second bracket is fixedly connected to the bottom surface of the circular support plate, a second socket is installed on the second bracket, and a second plug is correspondingly provided on the flange. The second socket is used to connect with the second plug. By providing a socket on the circular support plate and a plug on the flange, the rear support assembly is connected to the flange for guidance during installation.

[0011] Preferably, the rear end of the push rod is fixed in the limiting groove by screws. Fixing the push rod in the limiting groove with screws prevents the push rod from loosening and flying out with the drone.

[0012] Preferably, the rear support assembly is connected to the flange via a connecting rope. The purpose of this structural design is to prevent the rear support assembly from detaching from the launch tube after the UAV exits the launch tube.

[0013] Preferably, the support rod assembly includes a fixing clamp and two support rods. The fixing clamp is fixed to the outer wall of the launch tube by fasteners. Two connecting seats are symmetrically arranged on the fixing clamp. The support rods are rotatably connected to the connecting seats by bolts. Ground nails are provided at the ends of the support rods. The angle between the launch tube and the ground can be adjusted by rotating the support rods.

[0014] Preferably, the solenoid valve is connected to the gas storage tank via a flexible hose. Designing a flexible connection between the solenoid valve and the gas storage tank facilitates system installation and transportation.

[0015] Preferably, a silencing hole is provided at the front end of the launch tube. Providing a silencing hole on the launch tube can reduce the noise generated during the launch of the UAV.

[0016] Compared with the prior art, the present invention has the following advantages:

[0017] 1) This utility model adopts a launch tube design, which releases energy instantly through compressed air, providing a more reliable and stable launch power for the launch of the UAV, greatly reducing the problems of UAV flight attitude loss of control caused by unstable launch method and insufficient launch power, and further improving the success rate of UAV launch;

[0018] 2) This utility model uses a closed launching tube as the launching track, which is safer, more reliable, and can effectively prevent injury to operators;

[0019] 3) The support for the launch tube in this utility model is designed to be foldable. The support rod assembly can not only adjust the launch angle, but also be folded to be parallel to the launch tube, overcoming the shortcomings of traditional launch systems that are not convenient to carry and transport.

[0020] 4) This utility model has a silencing hole at the front end of the launch tube, which can reduce the noise generated by the drone at the moment of launch. Attached Figure Description

[0021] Figure 1 This is a front view of the overall structure of an embodiment of the present utility model;

[0022] Figure 2 This is a top view of the overall structure of an embodiment of the present utility model;

[0023] Figure 3 This is a three-view structural diagram of the rear support assembly in an embodiment of this utility model;

[0024] Figure 4 for Figure 1 Enlarged view of section C;

[0025] Figure 5 These are front and side view structural diagrams of the fixing clip in the embodiments of this utility model;

[0026] Reference numerals: 1. Launch tube; 2. Solenoid valve; 3. Gas tank; 4. Support rod assembly; 41. Fixing clamp; 411. Connecting seat; 42. Support rod; 5. Support seat; 6. Rear support assembly; 60. Circular support plate; 601. Limiting groove; 61. First push rod; 62. Second push rod; 63. Third push rod; 64. Fourth push rod; 65. Connecting assembly; 66. First bracket; 67. First socket; 68. Second bracket; 69. Second socket; 7. Air compressor; 8. Reinforcing ring; 9. Flange; 91. Second plug; 10. Elbow; 11. Hose; 12. Silencing hole. Detailed Implementation

[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the protection scope of the present utility model.

[0028] like Figures 1 to 5 As shown, a pneumatic launch system for a folding-wing drone includes a launch tube 1, a solenoid valve 2, and an air tank 3. A support rod assembly 4 is provided at the front end of the launch tube 1, and a support base 5 is provided at the rear end of the launch tube 1. A rear support assembly 6 for pushing the folding-wing drone is movably disposed inside the launch tube 1. The rear end of the launch tube 1 is connected to the solenoid valve 2, and the other end of the solenoid valve 2 is connected to the air tank 3. The other end of the air tank 3 is connected to an air compressor 7 through a quick connector.

[0029] The rear end of the launching tube 1 is provided with a reinforcing ring 8, which is used to increase the strength of the launching tube 1. The right end of the reinforcing ring 8 is connected to a flange 9, and the right end of the flange 9 is provided with an elbow 10. One end of the elbow 10 is connected to the flange 9 by a thread, and the other end is connected to the solenoid valve 2 by a thread.

[0030] The support base 5 has ground nails machined at its bottom. The support base 5 is rotatably connected to the side wall of the flange 9 by bolts. The support base 5 can rotate relative to the flange 9, which makes it convenient to adjust the angle of the launch tube 1. At the same time, it is convenient to transport and carry after being folded.

[0031] The rear support assembly 6 includes a circular support plate 60, the sidewall of which is tightly fitted to the inner wall of the launch tube 1. Four limiting grooves 601 are provided on the top surface of the circular support plate 60, and four push rods are inserted into these grooves: a first push rod 61, a second push rod 62, a third push rod 63, and a fourth push rod 64. The front ends of the four push rods are fixed together by a connecting assembly 65 to prevent the push rods from swinging and affecting launch accuracy. The front ends of the first push rod 61 and the second push rod 62 are fixedly connected to a first bracket 66 by fasteners. A first socket 67 is installed on the first bracket 66, and a first plug is correspondingly installed at the tail of the drone fuselage. The first socket 67 is used to connect to the first plug on the folding-wing drone fuselage.

[0032] Among them, a second bracket 68 is fixedly connected to the bottom surface of the circular tray 60 by fasteners. A second socket 69 is installed on the second bracket 68, and a second plug 91 is installed on the flange. Before the drone is launched, the second socket 69 and the second plug 91 are connected.

[0033] The rear ends of the four push rods are fixed in the limiting grooves 601 with screws to prevent the push rods from loosening and flying out with the drone.

[0034] The rear support assembly 6 is connected to the flange 9 via a connecting rope to prevent the rear support assembly 6 from detaching from the launch tube 1 after the UAV leaves the launch tube 1.

[0035] The support rod assembly 4 includes a fixing clip 41 and two support rods 42. The fixing clip 41 is fixed to the outer wall of the launch tube 1 by bolts. Two connecting seats 411 are symmetrically arranged on the fixing clip 41, and the included angle between the two connecting seats 411 is set to 60°. The support rods 42 are rotatably connected to the connecting seats 411 by bolts. The end of the support rod 42 is provided with a ground nail for easy insertion into the ground. The angle between the launch tube 1 and the ground can be adjusted by rotating the support rod 42.

[0036] The solenoid valve 2 is connected to the gas storage tank 3 via a hose 11, which facilitates the installation and transportation of the launch system.

[0037] The launch tube 1 has a silencing hole 12 at the front end, which can reduce the noise generated by the drone at the moment of launch.

[0038] This utility model is used as follows: First, open the support rod assembly 4. Adjust the angle between the launch tube 1 and the ground by rotating the support rod 42 (adjusting the launch angle). Then, insert the ground stakes on the support rod 42 and the bottom of the support base 5 into the ground (if used on a hard surface, this is not necessary). Quickly connect the air tank 3 and the air compressor 7 via a quick connector. Connect the rear support assembly 6 to the flange 9. Then, connect the folding-wing drone to the first socket 67 on the rear support assembly via the first plug. Then, control the solenoid valve 2 to quickly release compressed air. The compressed air pushes the rear support assembly 6 along the axis of the launch tube 1, thereby propelling the drone to launch. After use, separate the air tank 3 from the air compressor 7. Then, pull the support rod assembly 4 and the support base 5 from the ground. Fold the support rod assembly 4 parallel to the launch tube 1. Then, store or transport the various parts of the launch system.

[0039] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A pneumatic launch system for a folding-wing unmanned aerial vehicle (UAV), comprising a launch tube, a solenoid valve, and an air tank, characterized in that, The launch tube has a support rod assembly at its front end and a support base at its rear end. A rear support assembly for pushing the folding-wing UAV is movably installed inside the launch tube. The rear end of the launch tube is connected to the solenoid valve via an elbow. The other end of the solenoid valve is connected to the air tank. The other end of the air tank is connected to an air compressor via a quick connector.

2. The aerodynamic launch system for a folding-wing unmanned aerial vehicle according to claim 1, characterized in that, A reinforcing ring is provided at the rear end of the launch tube. The reinforcing ring is connected to the solenoid valve through a flange and an elbow. The support base is rotatably connected to the side wall of the flange by bolts.

3. The aerodynamic launch system for a folding-wing unmanned aerial vehicle according to claim 2, characterized in that, The rear support assembly includes a circular support plate. The side wall of the circular support plate is tightly fitted to the inner wall of the launch tube. Four limiting grooves are provided on the top surface of the circular support plate. Push rods are inserted into the limiting grooves. The front parts of the four push rods are fixed together by a connecting assembly. A first bracket is fixedly connected to the front end of the push rod. A first socket is installed on the first bracket. The first socket is used to connect to a first plug on the fuselage of the folding wing UAV.

4. The aerodynamic launch system for a folding-wing unmanned aerial vehicle according to claim 3, characterized in that, A second bracket is fixedly connected to the bottom surface of the circular tray, a second socket is installed on the second bracket, and a second plug is correspondingly provided on the flange. The second socket is used to connect to the second plug.

5. The aerodynamic launch system for a folding-wing unmanned aerial vehicle according to claim 4, characterized in that, The rear end of the push rod is fixed in the limiting groove by screws.

6. The aerodynamic launch system for a folding-wing unmanned aerial vehicle according to claim 5, characterized in that, The rear support assembly is connected to the flange via a connecting rope.

7. The aerodynamic launch system for a folding-wing unmanned aerial vehicle according to claim 1, characterized in that, The support rod assembly includes a fixing clamp and two support rods. The fixing clamp is fixed to the outer wall of the launch tube by fasteners. Two connecting seats are symmetrically arranged on the fixing clamp. The support rods are rotatably connected to the connecting seats by bolts. Ground nails are provided at the ends of the support rods.

8. The aerodynamic launch system for a folding-wing unmanned aerial vehicle according to claim 1, characterized in that, The solenoid valve is connected to the gas storage tank via a hose.

9. The aerodynamic launch system for a folding-wing unmanned aerial vehicle according to claim 1, characterized in that, The front end of the launch tube is provided with a silencing hole.

Images