A folding wing uav cluster launcher

Abstract

The application provides a kind of folding wing unmanned aerial vehicle cluster launching device, comprising: mounting body and multiple unmanned aerial vehicle launching components, the unmanned aerial vehicle launching components are evenly installed on the mounting body;The unmanned aerial vehicle launching component includes a launching barrel, a gas generator and a piston, the launching barrel is installed on the mounting body, the gas generator is arranged at the tail end of the launching barrel, the piston is movably arranged in the launching barrel, and a sealed cavity is formed around the inner wall of the launching barrel and the gas generator, the side of the piston away from the sealed cavity is formed with a positioning part for positioning with the unmanned aerial vehicle.Relative to the prior art, the folding wing unmanned aerial vehicle cluster launching device of the application realizes flexible ejection by compressed air of the gas generator, the device is light in weight, low in failure rate, low in use cost, high in practicality and maneuverability, can meet the unmanned aerial vehicle launching requirements under different harsh conditions, is convenient and fast to load and launch, and has wide application range.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically to a folding-wing UAV swarm launcher. Background Technology

[0002] With the development of information technology, warfare is increasingly moving towards unmanned and information-based operations. Drones, which have functions such as reconnaissance and strike, are widely used in modern warfare. Due to their small size, swarm operations enable close cooperation between individual drones to carry out tactical deception, conduct multi-domain strikes, and exert suppressive strikes on the enemy.

[0003] Currently, most existing folding-wing drones use a parallel connection method. This method limits the number of drones that can be loaded and requires a matching launch device. The entire launch device is bulky, requires multiple reloading, is costly, and inconvenient. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings and deficiencies of the prior art and provide a folding-wing drone swarm launch device.

[0005] One embodiment of the present invention provides a folding-wing unmanned aerial vehicle (UAV) swarm launch device, comprising: a mounting body and a plurality of UAV launch components, wherein the UAV launch components are uniformly mounted on the mounting body;

[0006] The UAV launch assembly includes a launch tube, a gas generator, and a piston. The launch tube is mounted on the mounting body, the gas generator is located at the tail end of the launch tube, and the piston is movably disposed within the launch tube, forming a sealed cavity with the inner wall of the launch tube and the gas generator. A positioning part is formed on the side of the piston away from the sealed cavity, which is used for positioning and cooperating with the UAV. After the gas generator fills the sealed cavity with gas, the piston moves along the launch tube under the drive of the air pressure in the sealed cavity, and pushes the UAV out from the head end of the launch tube. Compared with the prior art, the folding-wing UAV swarm launch device of the present invention achieves flexible ejection by compressing air through a gas generator. The device is lightweight, has a low failure rate, low operating cost, strong practicality and mobility, can meet the UAV launch requirements under different harsh conditions, is convenient for rapid loading and launching, and has a wide range of applications.

[0007] In some alternative implementations, the piston is connected to the gas generator via a flexible draw rope.

[0008] In some alternative embodiments, the UAV launch assembly further includes a mounting base disposed at the tail end of the gas generator, the mounting base having a positioning groove, the gas generator being disposed on the mounting base and positioned in conjunction with the positioning groove.

[0009] In some alternative embodiments, the gas generator is detachably mounted on the mounting base via a plurality of first threaded locking elements.

[0010] In some optional embodiments, the tail end of the launch tube is provided with a bottom cover and a bottom sleeve. The bottom cover is provided with a boss and a fixing channel. The mounting base is inserted into the fixing channel, the boss is inserted into the bottom sleeve, and the bottom sleeve is inserted into the launch tube. The bottom cover and the mounting base together close the opening at the tail end of the launch tube.

[0011] In some alternative embodiments, a quick-connect plug is provided on the side of the mounting base away from the gas generator, and the quick-connect plug is electrically connected to the gas generator.

[0012] In some alternative implementations, the quick-connect plug is detachably mounted on the mounting base via a plurality of second threaded locking elements.

[0013] In some alternative embodiments, the launch tube arrays of the various UAV launch assemblies are arranged on the mounting body.

[0014] In some alternative embodiments, a plurality of angle iron reinforcements are provided on the outer side of the launch tube, and the plurality of angle iron reinforcements are arranged around the launch tube.

[0015] In some alternative embodiments, a pressure stabilizing groove is provided on the side of the piston facing the sealing cavity, the pressure stabilizing groove is arranged in the middle of the piston, and the flexible pull rope is connected to the middle of the pressure stabilizing groove.

[0016] Compared with existing technologies, the folding-wing UAV swarm launcher of the present invention achieves flexible ejection by compressing air through a gas generator. The device is lightweight, has a low failure rate, low operating costs, and is highly practical and mobile. It can meet the launch requirements of UAVs under various harsh conditions, is easy to load and launch quickly, and has a wide range of applications.

[0017] To provide a clearer understanding of the present invention, the specific embodiments of the present invention will be described below in conjunction with the accompanying drawings. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of a folding-wing UAV swarm launcher according to an embodiment of the present invention;

[0019] Figure 2 This is a schematic diagram of the structure of a drone launch assembly according to an embodiment of the present invention;

[0020] Figure 3 This is an exploded view of a drone launch assembly according to an embodiment of the present invention;

[0021] Figure 4 This is a partial cross-sectional view of a drone launch assembly according to an embodiment of the present invention;

[0022] Figure 5 for Figure 3 The enlarged view of point A shown.

[0023] Explanation of reference numerals in the attached figures:

[0024] 10. Mounting body; 20. UAV launch assembly; 21. Launch tube; 211. Bottom cover; 212. Bottom sleeve; 213. Boss; 214. Fixing channel; 215. Angle iron reinforcement; 22. Gas generator; 23. Piston; 231. Positioning part; 232. Flexible pull rope; 233. Pressure stabilizing groove; 24. Mounting base; 241. Positioning groove; 242. First threaded locking element; 25. Quick connector; 251. Second threaded locking element; 30. Sealing cavity; 40. Top cover; 50. Base; 60. Support base; 70. Disc; 80. Hydraulic lifting system; 90. Steering rocker arm. Detailed Implementation

[0025] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention. The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of the present invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified, and "several" means one or more.

[0026] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0027] Please see Figure 1One embodiment of the present invention provides a folding-wing drone swarm launch device, including: a mounting body 10 and a plurality of drone launch components 20, wherein the drone launch components 20 are uniformly mounted on the mounting body 10.

[0028] Please see Figures 2 to 4 The drone launch assembly 20 includes a launch tube 21, a gas generator 22, and a piston 23. The launch tube 21 is mounted on the mounting body 10 and is used to hold the drone and guide it during launch. The gas generator 22 is located at the tail end of the launch tube 21 and is used to provide high-pressure gas. The piston 23 is movably disposed inside the launch tube 21 and forms a sealed cavity 30 with the inner wall of the launch tube 21 and the gas generator 22. A positioning part 231 is formed on the side of the piston 23 away from the sealed cavity 30. The positioning part 231 is used to position and cooperate with the drone, so that the drone is less likely to rotate circumferentially or deviate radially relative to the piston 23 when it moves along the launch tube 21. After the gas generator 22 fills the sealed cavity 30 with high-pressure gas, the gas pressure inside the sealed cavity 30 increases and expands, causing the piston 23 to move along the launch tube 21 under the drive of the gas pressure inside the sealed cavity 30. This causes the piston 23 to push the drone along the launch tube 21 and eject the drone from the head end of the launch tube 21.

[0029] Piston 23 is made entirely of ABS resin 3D printing technology. The resin itself is not easily corroded, and it is resistant to acids and alkalis, anti-aging, lightweight and quick to form.

[0030] In some alternative implementations, the piston 23 is connected to the gas generator 22 via a flexible pull rope 232. When the piston 23 moves to the head end of the launch tube 21, the flexible pull rope 232 becomes taut and does not detach from the launch tube 21, and the drone is ejected. This avoids the piston 23 being launched along with the drone and affecting or colliding with other drones ejected from the launch tube 21, and also avoids the trouble of needing to retrieve the piston 23 after it detaches from the launch tube 21.

[0031] Please see Figure 5 In some alternative embodiments, the UAV launch assembly 20 also includes a mounting base 24, which is disposed at the tail end of the gas generator 22. The mounting base 24 is provided with a positioning groove 241, and the gas generator 22 is disposed on the mounting base 24 and positioned and engaged with the positioning groove 241.

[0032] The installation method of the gas generator 22 can be selected according to actual needs. In some optional embodiments, the gas generator 22 is detachably mounted on the mounting base 24 by a plurality of first threaded locking elements 242. Of course, the installation method of the gas generator 22 is not limited to this. Those skilled in the art can also select other suitable structures according to the teachings of the present invention. For example, the gas generator 22 can also be directly threaded into the mounting base 24, or it can be snapped into the mounting base 24 by a snap-fit ​​structure.

[0033] The fixing method of the mounting base 24 can be selected according to the actual needs. In order to facilitate the quick installation of the gas generator 22, in some optional embodiments, the tail end of the launch tube 21 is provided with a bottom cover 211 and a bottom sleeve 212. The bottom cover 211 is provided with a boss 213 and a fixing channel 214. The mounting base 24 is inserted into the fixing channel 214, the boss 213 is inserted into the bottom sleeve 212, and the bottom sleeve 212 is inserted into the launch tube 21. The bottom cover 211 and the mounting base 24 together close the opening at the tail end of the launch tube 21.

[0034] In some alternative embodiments, a quick-connect plug 25 is provided on the side of the mounting base 24 away from the gas generator 22. The quick-connect plug 25 is electrically connected to the gas generator 22, which facilitates the gas generator 22 located in the launch tube 21 to be quickly connected to an external power source.

[0035] The quick-connect plug 25 can be fixed in a suitable way according to actual needs. In some optional embodiments, the quick-connect plug 25 is detachably mounted on the mounting base 24 by a plurality of second threaded locking elements 251.

[0036] In some alternative embodiments, the launch tubes 21 of each UAV launch assembly 20 are arranged in an array on the mounting body 10. In this embodiment, the mounting body 10 is provided with 30 UAV launch assemblies 20, and the maximum number of UAVs launched at one time is 30.

[0037] When the cross-section of the launch tube 21 is rectangular, the stress concentration at the inner corner of the launch tube 21 leads to structural instability. In some optional embodiments, multiple angle iron reinforcements 215 are provided on the outer side of the launch tube 21. The multiple angle iron reinforcements 215 are arranged around the launch tube 21 to strengthen the corner strength of the launch tube 21 and resist the stress concentration effect of the inner chamfer of the launch tube 21.

[0038] In some alternative embodiments, a pressure-stabilizing groove 233 is provided on the side of the piston 23 facing the sealing cavity 30. The pressure-stabilizing groove 233 is arranged in the middle of the piston 23, and a flexible pull rope 232 is connected to the middle of the pressure-stabilizing groove 233. When gas rushes into the pressure-stabilizing groove 233, the gas pressure acts on the side wall of the pressure-stabilizing groove 233, and the direction of the gas pressure is perpendicular to the guiding direction of the launching tube 21. This allows the piston 23 to be stably attached to the inner wall of the launching tube 21 and is not easy to shake. This ensures that the middle of the piston 23 is stably subjected to gas pressure. Moreover, the pressure-stabilizing groove 233 also helps to reduce the weight of the piston 23.

[0039] The launch tube 21 is detachably mounted on the mounting body 10 by multiple screws, which facilitates quick replacement of the launch tube 21.

[0040] A cavity is formed inside the mounting body 10, and the launching tube 21 is arranged inside the cavity. An opening is provided at the top of the cavity, and a top cover 40 is hinged to the top of the mounting body 10. The top cover 40 is used to close the opening.

[0041] The bottom of the mounting body 10 is also connected to a base 50. The base 50 and the support 60 are rotatably engaged. A hydraulic lifting system 80 is provided between the base 50 and the support 60. The hydraulic lifting system 80 lifts the base 50, causing the base 50 and the mounting body 10 to swing up and down, thereby adjusting the vertical angle of the launch tube 21. A disc 70 is provided at the bottom of the support 60. The disc 70 is fixed to the accompanying launch vehicle, facilitating the movement of the folding-wing UAV swarm launch device. The support 60 and the disc 70 are rotatably engaged, allowing the support 60 to adjust its horizontal angle relative to the disc 70.

[0042] The drive mechanism that drives the support base 60 to rotate relative to the disk 70 can be selected according to actual needs. In this embodiment, the drive mechanism includes a steering rocker arm 90 and a transmission gear set. The steering rocker arm 90 is rotatably mounted on the support base 60 and is driven to the disk 70 through the transmission gear set. By rocking the steering rocker arm 90, the support base 60 and the disk 70 can rotate relative to each other. Of course, the structure of the drive mechanism is not limited to this. Those skilled in the art can also select other suitable structures according to the teachings of this invention. For example, the support base 60 and the disk 70 can be driven to rotate relative to each other by a drive motor. This example is not limited to this one.

[0043] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A folding-wing unmanned aerial vehicle (UAV) swarm launcher, characterized in that, include: The mounting body and multiple drone launch assemblies are uniformly mounted on the mounting body; The drone launch assembly includes a launch tube, a gas generator, and a piston. The launch tube is mounted on the mounting body. The gas generator is located at the tail end of the launch tube. The piston is movably disposed inside the launch tube and forms a sealed cavity with the inner wall of the launch tube and the gas generator. A positioning part is formed on the side of the piston away from the sealed cavity. The positioning part is used to position and cooperate with the drone. After the gas generator fills the sealed cavity with gas, the piston moves along the launch tube under the drive of the gas pressure in the sealed cavity and pushes the drone out from the head end of the launch tube. The piston is connected to the gas generator via a flexible draw rope; The UAV launch assembly also includes a mounting base, which is disposed at the tail end of the gas generator. The mounting base is provided with a positioning groove, and the gas generator is disposed on the mounting base and positioned and engaged with the positioning groove. The tail end of the launch tube is provided with a bottom cover and a bottom sleeve. The bottom cover is provided with a boss and a fixing channel. The mounting base is inserted into the fixing channel, the boss is inserted into the bottom sleeve, and the bottom sleeve is inserted into the launch tube. The bottom cover and the mounting base together close the opening at the tail end of the launch tube. A pressure-stabilizing groove is provided on the side of the piston facing the sealing cavity. The pressure-stabilizing groove is located in the middle of the piston, and the flexible pull rope is connected to the middle of the pressure-stabilizing groove.

2. The folding-wing UAV swarm launcher according to claim 1, characterized in that: The gas generator is detachably mounted on the mounting base via a plurality of first threaded locking elements.

3. The folding-wing UAV swarm launcher according to claim 1, characterized in that: A quick-connect plug is provided on the side of the mounting base away from the gas generator, and the quick-connect plug is electrically connected to the gas generator.

4. The folding-wing UAV swarm launcher according to claim 3, characterized in that: The quick-connect plug is detachably mounted on the mounting base via multiple second threaded locking elements.

5. A folding-wing unmanned aerial vehicle (UAV) swarm launcher according to any one of claims 1 to 4, characterized in that: The launch tube arrays of each of the aforementioned UAV launch components are arranged on the mounting body.

6. A folding-wing unmanned aerial vehicle (UAV) swarm launcher according to any one of claims 1 to 4, characterized in that: The outer side of the launch tube is provided with multiple angle iron reinforcements, which are arranged around the launch tube.

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