Unmanned aerial vehicle (UAV) launcher

Abstract

This invention relates to the field of flight equipment technology, and more particularly to a drone launching device, comprising: a handheld launching structure, which includes a launch chamber assembly, a power assembly, and a trigger assembly; the launch chamber assembly includes a launch chamber having multiple launch ports for loading drones; the power assembly includes a hammer and a drive unit; the drive unit is used to rotate the launch chamber to switch the launch port facing the hammer, and the drive unit also drives the hammer to move away from the launch chamber until the hammer reaches the charging position; the trigger assembly includes a locking block and a trigger connected to each other, the locking block limiting the hammer in the charging position, and after the trigger is pulled, the locking block releases the hammer, which propels the drone out of the launch port facing the hammer; and an automatic wing-spreading structure installed on the drone fuselage. This invention at least improves the convenience of launching multiple drones.

Description

Technical Field

[0001] This invention belongs to the field of flight equipment technology, and in particular relates to a drone launch device. Background Technology

[0002] The proposal of drone launchers aims to improve the flexibility, regional adaptability, and survivability of drone systems. Currently, drones have advantages such as compact size, flexible maneuverability, vertical take-off and landing, low noise, long endurance, and strong environmental adaptability, making them very suitable for use in scenarios requiring rapid deployment and covert operations when combined with drone launchers.

[0003] Patent application CN113044233A discloses a drone launch device. Specifically, the drone is fixed inside a launch tube, and high-pressure gas stored in an air tank is delivered to the launch tube through a connecting pipe. A solenoid valve controls the release of gas. When the solenoid valve opens, the high-pressure gas propels the drone out of the launch tube rapidly. Structurally, this device only supports the fixing and launch of a single drone. If multiple drones are launched consecutively, reloading and setting are required, increasing the complexity and time of operation. If the gas in the air tank is not replenished in time, it may not provide sufficient thrust to launch the drone stably. Especially in the case of launching multiple drones consecutively, subsequent drones may fail to achieve the expected launch effect due to insufficient gas pressure, increasing safety risks during the launch process and affecting the success rate and flight stability of the drone.

[0004] Patent application CN109436364A discloses a device for continuous launch of unmanned aerial vehicles (UAVs). A storage device stores the UAVs, a conveyor transports them from the storage device to a trolley, and an automatic mounting device transfers the UAVs onto the trolleys. The rotary multi-track UAV launcher has at least three launchers, each docking with a trolley and providing the trolley with the driving force for launch. During launch, a conveyor chain and hooks work together to dock and separate the UAVs. The automatic mounting device transports and docks the UAVs onto the trolley support structure by rotation. After launching the UAVs, the launchers automatically reset to prepare for the next launch. While this device improves UAV launch efficiency, its structure is relatively complex, involving multiple precisely coordinated components, resulting in a large system size, reducing portability, and requiring complex connection and debugging processes, increasing the risk of malfunctions in actual operation. Furthermore, the complex structure requires more time and resources to train operators to ensure correct loading, launching, and resetting of the UAVs. Summary of the Invention

[0005] In view of this, the present invention aims to provide a drone launching device that at least improves the convenience of launching multiple drones.

[0006] To achieve the above objectives, the technical solution created by this invention is implemented as follows:

[0007] This invention provides a drone launching device, comprising: a handheld launching structure, which includes a launch chamber assembly, a power assembly, and a trigger assembly; the launch chamber assembly includes a launch chamber having multiple launch ports for loading drones; the power assembly includes a hammer and a drive unit connected to each other; the drive unit is used to rotate the launch chamber to switch the launch port facing the hammer, and while rotating the launch chamber, the drive unit also moves the hammer away from the launch chamber until the hammer reaches the charging position; the trigger assembly includes a locking block and a trigger connected to each other, the locking block limiting the hammer to the charging position, and after the trigger is pulled, the locking block releases the hammer, which propels the drone out of the launch port facing the hammer; and an automatic wing-spreading structure mounted on the drone body, which includes a rotor mounting frame and a rotor, the rotor mounting frame being mounted on the drone body via a first rotation axis, and the rotor being mounted on the rotor mounting frame. When the drone is in the launch port, the rotor mounting frame drives the rotor to fit against the side of the drone body; after the drone is launched, the rotor mounting frame drives the rotor to unfold.

[0008] In some embodiments, the automatic wing deployment structure further includes a torsion spring, a magnet, and an iron core with a coil wound around it. The torsion spring cooperates with the first rotating shaft and is connected to the rotor mounting frame and the drone body. The iron core is fixed to the drone body, and the magnet is fixed to the rotor mounting frame. When the drone is located in the launch port, the coil is energized, and the magnet, under the magnetic force of the iron core, causes the rotor to adhere to the side of the drone body through the rotor mounting frame. After the drone is launched, the coil is de-energized to allow the rotor to deploy.

[0009] In some embodiments, the launch chamber is cylindrical, with launch holes penetrating the launch chamber along its axial direction, and multiple launch holes are spaced apart around the axis of the launch chamber. The launch chamber has a central shaft hole penetrating the launch chamber along its axis. The launch chamber assembly also includes a central shaft, a launch chamber shell, and a launch chamber rear cover. The central shaft is disposed within the central shaft hole, and the launch chamber is fitted within the launch chamber shell. The launch chamber is rotatable relative to the launch chamber shell around the central shaft. One end of the central shaft is connected to the first end of the launch chamber shell, and the first end of the launch chamber shell has a launch port. The launch hole facing the hammer is also facing the launch port. The launch chamber rear cover is disposed at the second end of the launch chamber shell via a second rotating shaft. The launch chamber rear cover has a second through hole and a first through hole facing the hammer. The power assembly and trigger assembly are disposed on the side of the launch chamber rear cover away from the launch chamber shell. The drive unit is connected to the launch chamber via a connector disposed within the second through hole to drive the launch chamber to rotate along its axis.

[0010] In some embodiments, the connector includes a grooved wheel, a dial, and a connecting rod. The grooved wheel is fixed to one end of the launch chamber facing the rear cover of the launch chamber and is directly opposite the central shaft. The side of the dial contacts the side of the grooved wheel and is fixed to the first end of the connecting rod. The connecting rod passes through a second through hole and is connected to a drive unit. The drive unit includes a motor, a first gear, a second gear, and a gear chain. The motor shaft is driven by the first gear, and the first gear is driven by the second gear through the gear chain. The second end of the connecting rod is connected to the second gear. The motor drives the first gear to rotate, the first gear drives the second gear to rotate through the gear chain, and the second gear drives the dial to rotate through the connecting rod, so that the dial actuates the grooved wheel, thereby causing the launch chamber to rotate to switch the launch port facing the hammer.

[0011] In some embodiments, the surface of the launch chamber rear cover facing the launch chamber has a shaped groove, and the groove wheel and dial are both disposed in the shaped groove.

[0012] In some embodiments, the drive unit further includes: a spiral slide, a launch spring, and a fixed baffle. The fixed baffle, spiral slide, launch spring, and hammer are located on the side of the first gear away from the motor, and the fixed baffle, launch spring, and hammer are connected in sequence and arranged in a direction away from the first gear. The spiral slide is located in the inner ring of the hammer and the inner ring of the launch spring. The first end of the spiral slide is connected to the hammer, and the other end of the spiral slide passes through the fixed baffle and is connected to the motor shaft of the motor. The motor drives the spiral slide to rotate, and the spiral slide drives the hammer to move towards the fixed baffle through the pin in the inner ring of the hammer. The launch spring is compressed until the hammer reaches the charging position, and the pin is disconnected from the thread of the spiral slide, completing the charging operation. After the trigger is pulled, the locking block releases the hammer, the launch spring pushes the hammer, and the hammer pushes the UAV in the launch hole to be launched.

[0013] In some embodiments, the drive unit further includes a power housing, and the motor, the first gear, a portion of the gear chain, the fixed baffle, the spiral slide, the launching spring, and the hammer are all disposed within the power housing.

[0014] In some embodiments, the trigger assembly further includes a trigger housing disposed on the side of the power housing, a locking iron and a second gear disposed within the trigger housing, a gear chain extending from the power housing into the trigger housing, and a trigger extending from the trigger housing through a through hole in the trigger housing.

[0015] In some embodiments, the parameters of the launching spring satisfy the following formula:

[0016]

[0017] Where H0 is the original length of the launching spring, and the unit of H0 is mm; f n f is the maximum deformation of the launching spring. nThe unit is mm; F ′ F is the spring constant of the launching spring. ′ The unit is N / mm; m w For the mass of the drone, m w The unit is kg; m j For the mass of the hammer, m j The unit is kg; V w V is the launch speed of the drone. w The unit is m / s; H s H represents the vertical height of the handheld launcher. s The unit is mm.

[0018] In some embodiments, the trigger assembly further includes a catch spring and a trigger inner housing. The trigger inner housing is disposed on the side of the launch chamber rear cover away from the launch chamber, and when the hammer is in the charging position, the trigger inner housing is disposed below the hammer. One end of the catch extends from the side of the trigger inner housing away from the hammer to the front end of the hammer, and the other end of the catch is disposed on the trigger inner housing by the catch spring.

[0019] Compared with the prior art, the present invention can achieve the following beneficial effects: The drone launching device provided by the embodiments of the present invention includes a handheld launching structure, which allows the drone to be stored in a folded state during transportation and storage. Multiple drones can be launched continuously with one loading. After launch, the drone automatically unfolds its rotors for flight through an automatic wing-spreading structure. The handheld launching structure, through the cooperation of the power component and the trigger component, enables the hammer to quickly accumulate power, achieving the purpose of rapid take-off of the drone after launch. The handheld launching structure, through the cooperation of the grooved wheel and the dial, enables the launch chamber to automatically rotate after each launch, thereby providing drones for the next launch. The buckle provided on the launch chamber shell and the slot provided on the launch chamber rear cover cooperate to realize the rapid loading of drones.

[0020] In summary, the UAV launching device provided by the embodiments of the present invention is not limited by the launch site, facilitates the storage and transportation of UAVs, and has a rapid launch process. When the UAV is launched, it can quickly take off and automatically deploy its wings. Moreover, it can launch multiple UAVs continuously to achieve the effect of swarm intelligence and collaboration. Attached Figure Description

[0021] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments and descriptions of the invention are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0022] Figure 1 A schematic diagram of the structure of the UAV described in the embodiment of the present invention;

[0023] Figure 2 A schematic diagram of the automatic wing-spreading structure described in the embodiment of the present invention;

[0024] Figure 3 A schematic diagram of the handheld launching structure described in an embodiment of the present invention;

[0025] Figure 4 A schematic diagram of the launch chamber and connector described in an embodiment of the present invention;

[0026] Figure 5 A schematic diagram of the filling state of the handheld launching structure described in the embodiment of the present invention;

[0027] Figure 6 A detailed structural diagram of the handheld launching structure described in an embodiment of the present invention;

[0028] Figure 7 A schematic diagram of the power assembly and trigger assembly of the handheld launching structure described in the embodiment of the present invention;

[0029] Figure 8 A side view of a portion of the handheld launching structure described in an embodiment of the present invention;

[0030] Figure 9 A schematic diagram of the hammer, spiral slide, launching spring, and fixed baffle of the handheld launching structure described in the embodiment of the present invention;

[0031] Figure 10 A tabular schematic diagram of the launching spring parameters described in the embodiments of the present invention;

[0032] Figure 11 This is a flowchart illustrating the launching of a drone by a drone launcher according to an embodiment of the present invention.

[0033] Explanation of reference numerals in the attached drawings: 1. Unmanned aerial vehicle (UAV); 111. Iron core; 112. Magnet; 113. Rotor; 114. Rotor mounting bracket; 21. Launch chamber shell; 211. Launch port; 212. Buckle; 213. Auxiliary handheld structure; 22. Launch chamber; 23. Launch chamber rear cover; 231. First through hole; 232. Slot; 24. Central shaft; 301. Power housing; 302. Hammer; 303. Spiral slide; 304 305. Launch spring; 306. Fixed baffle; 307. Motor; 308. First gear; 309. Second gear; 3000. Gear chain; 310. Grooved wheel; 311. Dial; 401. Locking iron; 402. Trigger inner housing; 403. Locking iron spring; 404. Trigger; 405. Trigger outer housing; 313. Pin; 312. Connecting rod; 221. Launch hole; 233. Irregular groove; 411. Locking iron extension groove. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not constitute a limitation thereof.

[0035] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other.

[0036] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this invention. Furthermore, the terms "first," "second," etc., 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, features defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0037] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; 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; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0038] The invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0039] refer to Figures 1 to 9This invention provides a drone launching device, comprising: a handheld launching structure for storing, transporting, and launching multiple drones 1 with automatic wing extension structures; the handheld launching structure includes a launch chamber assembly, a power assembly, and a trigger assembly; the launch chamber assembly includes a launch chamber 22, which has multiple launch ports 221 for loading the drones 1; the launch chamber 22 is used to store and transport multiple drones 1 with automatic wing extension structures; the power assembly includes a hammer 302 and a drive unit connected to each other; the drive unit is used to rotate the launch chamber 22 to switch the launch ports 221 facing the hammer 302; while rotating the launch chamber 22, the drive unit also moves the hammer 302 in a direction away from the launch chamber 22 until the hammer 302 reaches the charging position; the trigger assembly includes a... The device includes a locking iron 401 and a trigger 404. The locking iron 401 limits the hammer 302 to the charging position. After the trigger 404 is pulled, the locking iron 401 releases the hammer 302, which propels the drone 1 out of the launch port 221 directly opposite the hammer 302. An automatic wing-spreading structure is installed on the body of the drone 1. The automatic wing-spreading structure allows the drone 1 to automatically unfold its rotor 113 after taking off. The automatic wing-spreading structure includes a rotor mounting frame 114 and a rotor 113. The rotor mounting frame 114 is installed on the body of the drone 1 via a first rotation axis. The rotor 113 is installed on the rotor mounting frame 114. When the drone 1 is inside the launch port 221, the rotor mounting frame 114 drives the rotor 113 to fit against the side of the drone 1 body. After the drone 1 is launched, the rotor mounting frame 114 drives the rotor 113 to unfold.

[0040] In some embodiments, reference Figure 1 Drone 1 can be a micro coaxial dual-rotor drone. This type of drone technology is already mature and will not be described in detail here.

[0041] The power assembly provided in this embodiment of the invention can synchronize the automatic switching of the launch port 221 and the rapid power accumulation process, which helps to reduce the size of the entire UAV launch device and facilitates handheld launch; the trigger assembly can instantly release the hammer 302, so that the UAV 1 in the launch port 221 directly opposite the hammer 302 can obtain a large thrust to achieve rapid take-off.

[0042] In some embodiments, reference Figure 2The automatic wing deployment structure also includes a torsion spring, a magnet 112, and an iron core 111 with a coil wound on it (not shown). The torsion spring cooperates with the first rotating shaft and is connected to the rotor mounting bracket 114 and the body of the UAV 1. The iron core 111 is fixed to the body of the UAV 1, and the magnet 112 is fixed to the rotor mounting bracket 114. When the UAV 1 is located in the launch port 221, the coil is energized, and the magnet 112 is subjected to the magnetic force of the iron core 111, which causes the rotor 113 to adhere to the side of the UAV 1 body through the rotor mounting bracket 114. After the UAV 1 is launched, the coil is de-energized to allow the rotor 113 to deploy.

[0043] Specifically, the rotor mounting bracket 114 has a slot coaxial with the first rotation axis, a torsion spring is fixed in the slot, and an iron core 111 is located in the fuselage part where the rotor 113 can completely overlap with the magnet 112 when folded. The coil wound on the iron core 111 is connected to the circuit. When the torsion spring is not under force, it drives the rotor mounting bracket 114 to support the rotor 113 to open. When the drone 1 is in the handheld launch structure, the coil on the iron core 111 is energized, making it magnetic and attracting the magnet 112. At this time, the torsion spring is compressed, and the rotor 113 folds. When the drone 1 is launched into the air and the acceleration drops to zero, the circuit connected to the iron core 111 de-energizes the coil, the magnetism of the iron core 111 disappears, and it can no longer attract the magnet 112. The torsion spring returns to its original state, and the rotor 113 unfolds.

[0044] In some embodiments, reference Figure 3 and Figure 4 The launch chamber 22 is cylindrical, with launch holes 221 penetrating it along its axial direction. Multiple launch holes 221 are arranged at intervals around the axis of the launch chamber 22. The launch chamber 22 has a central shaft hole penetrating it along its axis. The launch chamber assembly also includes a central shaft 24, a launch chamber shell 21, and a launch chamber rear cover 23. The central shaft 24 is disposed within the central shaft hole, and the launch chamber 22 is fitted within the launch chamber shell 21. The launch chamber 22 is rotatable relative to the launch chamber shell 21 around the central shaft 24. One end of the central shaft 24 is connected to the first end of the launch chamber shell 21. The launch chamber shell 21 is connected to the launch chamber shell 21, and the first end of the launch chamber shell 21 has a launch port 211, and the launch hole 221, which is directly opposite to the hammer 302, is also directly opposite to the launch port 211. The launch chamber rear cover 23 is set at the second end of the launch chamber shell 21 through the second rotating shaft. The launch chamber rear cover 23 has a second through hole and a first through hole 231, which is directly opposite to the hammer 302. The power assembly and the trigger assembly are set on the side of the launch chamber rear cover 23 away from the launch chamber shell 21. The drive unit is connected to the launch chamber 22 through the connector set in the second through hole so as to drive the launch chamber 22 to rotate along its axis.

[0045] For details, please refer to Figure 5The front cover of the launch chamber shell 21 has a circular launch port 211, the diameter of which is the same as the diameter of the launch hole 221 of the launch chamber 22. There is an auxiliary hand-held structure 213 at the bottom front end of the launch chamber shell 21. The two buckles 212 at the rear end of the launch chamber shell 21 are engaged with the slots 232 on the rear cover 23 of the launch chamber. The launch chamber 22 is inside the launch chamber shell 21 and the launch chamber 22 and the launch chamber shell 21 are coaxial. The rear cover 23 of the launch chamber is engaged with the launch chamber shell 21. When the buckles 212 of the launch chamber shell 21 are opened, the rear cover 23 of the launch chamber can be opened along the second rotation axis. At this time, multiple UAVs 1 can be loaded into the launch chamber 22 at one time. Then the rear cover 23 of the launch chamber is closed, and the buckles 212 of the launch chamber shell 21 are engaged with the slots 232 of the rear cover 23 of the launch chamber, completing the loading process of the UAVs 1.

[0046] In some embodiments, the launch chamber 22 has three launch holes 221, which are arranged in a 120° circular array.

[0047] In some embodiments, reference Figure 4 , Figure 6 , Figure 7 as well as Figure 8 The connecting components include a grooved wheel 310, a dial 311, and a connecting rod 312. The grooved wheel 310 is fixed to one end of the launch chamber 22 facing the rear cover 23 of the launch chamber, and the grooved wheel 310 is directly opposite the central shaft 24. The side of the dial 311 contacts the side of the grooved wheel 310, and the dial 311 is fixed to the first end of the connecting rod 312. The connecting rod 312 passes through the second through hole, and the second end of the connecting rod 312 is connected to the drive unit. The drive unit includes a motor 306, a first gear 307, a second gear 308, and a gear chain 309. The motor 306... The shaft is connected to the first gear 307, which is connected to the second gear 308 via a gear chain 309. The second end of the connecting rod 312 is connected to the second gear 308. The motor 306 drives the first gear 307 to rotate, which in turn drives the second gear 308 to rotate via the gear chain 309. The second gear 308 drives the dial 311 to rotate via the connecting rod 312, so that the dial 311 actuates the slotted wheel 310, thereby causing the firing chamber 22 to rotate to switch the firing port 221 facing the hammer 302.

[0048] For details, please refer to Figures 4 to 8The dial 311 is connected to the hub of the second gear 308. The grooved wheel 310 is fixed to the center of the rear end of the launch chamber 22. The rear cover 23 of the launch chamber has a circular power port, namely the first through hole 231. The diameter of the first through hole 231 is the same as the diameter of the launch hole 221 of the launch chamber 22, and it is coaxial with the launch port 211 opposite to the hammer 302. The grooved wheel 310 has three grooves arranged in a 120° circumferential array and three concave arcs arranged in a 120° circumferential array. The grooves and concave arcs are staggered. One side of the grooved wheel 310 is fixed to the launch chamber 22, and the grooves correspond to the launch hole 221 of the launch chamber 22.

[0049] In some embodiments, the dial 311 consists of a pin and a convex arc. The concave arc of the grooved wheel 310 and the convex arc of the dial 311 have the same radius. The dial 311 is placed on one side of the grooved wheel 310, and the convex arc of the dial 311 is completely in contact with a concave arc of the grooved wheel 310. The center of the convex arc is connected to the hub of the second gear 308.

[0050] When the dial 311 rotates, if the concave arc of the grooved wheel 310 contacts the convex arc of the dial 311, the grooved wheel 310 cannot rotate, and the launch chamber 22 fixed to the grooved wheel 310 also cannot rotate. At this time, one of the launch holes 221 of the launch chamber 22 is directly opposite the launch port 211 of the launch chamber shell 21. The UAV 1 in the launch hole 221 directly opposite the launch port 211 is waiting to be launched. When the pin of the dial 311 contacts the groove of the grooved wheel 310, the grooved wheel 310 is rotated by force and rotates 120° each time. The launch chamber 22 fixed to the grooved wheel 310 is driven by the grooved wheel 310 to rotate 120° around the central axis 24. At this time, the next launch hole 221 of the launch chamber 22 is directly opposite the launch port 211 of the launch chamber shell 21. The UAV 1 in the launch hole 221 directly opposite the launch port 211 is waiting to be launched.

[0051] In some embodiments, the surface of the launch chamber rear cover 23 facing the launch chamber 22 has a shaped groove 233, and the groove wheel 310 and the dial 311 are both disposed in the shaped groove.

[0052] In some embodiments, reference Figure 8 and Figure 9The drive unit also includes a spiral slide 303, a launching spring 304, and a fixed baffle 305. The fixed baffle 305, spiral slide 303, launching spring 304, and hammer 302 are located on the side of the first gear 307 away from the motor 306. The fixed baffle 305, launching spring 304, and hammer 302 are connected in sequence and arranged in a direction away from the first gear 307. The spiral slide 303 is located on the inner ring of the hammer 302 and the inner ring of the launching spring 304. The first end of the spiral slide 303 is connected to the hammer 302, and the other end of the spiral slide 303 passes through the fixed baffle 305. The fixed baffle 305 is connected to the motor shaft of the motor 306; the motor 306 drives the spiral slide 303 to rotate, and the spiral slide 303 drives the hammer 302 to move towards the fixed baffle 305 through the pin 313 on the inner ring of the hammer 302. The launching spring 304 is compressed until the hammer 302 reaches the charging position. The pin 313 is disconnected from the thread of the spiral slide 303, and the charging operation is completed. After the trigger 404 is pulled, the locking block 401 releases the hammer 302, the launching spring 304 pushes the hammer 302, and the hammer 302 pushes the drone 1 in the launching hole 221 to be launched.

[0053] It should be noted that the hammer 302 is a column with an open rear end, a hollow middle section, and a closed front end. The cross-sectional diameter of the hammer 302 can be slightly smaller than the diameter of the first through hole 231 of the launch chamber rear cover 23, and the hammer 302 is coaxial with the first through hole 231 of the launch chamber rear cover 23. The inner ring of the hammer 302 has two symmetrical pins 313, which contact the spiral slide 303. The spiral slide 303 is a column with a spiral groove on the outside. The spiral slide 303 is placed inside the hammer 302 and the launch spring 304, and the tail of the spiral slide 303 is connected to the motor shaft of the motor 306. The motor 306 controls the rotation of the motor shaft through a circuit. The motor shaft drives the first gear 307 and the spiral slide 303 to rotate, thereby realizing the automatic switching of the launch port 221 and the synchronous charging.

[0054] The process of automatically switching the emission port 221 is as follows: the motor 306 drives the first gear 307 to rotate through the motor shaft, the first gear 307 drives the second gear 308 to rotate through the gear chain 309, and the second gear 308 drives the dial 311 to rotate through the hub, thereby controlling the rotation of the emission chamber 22 to switch the emission port 221.

[0055] The power storage process is as follows: When the spiral slide 303 rotates, it presses the pin 313 on the hammer 302 backward, thus moving the hammer 302 backward. Since the hammer 302 is connected to the launching spring 304, the launching spring 304 will be compressed. When the spiral slide 303 rotates to the power storage position, the spring is compressed to its tightest position, the hammer 302 is locked on the locking iron 401 and the pin 313 is disengaged from the thread of the spiral slide 303 and is no longer under force. At this time, the motor 306 stops rotating, completing the power storage process.

[0056] In some embodiments, the drive unit further includes a power housing 301, and a motor 306, a first gear 307, a partial gear chain 309, a fixed baffle 305, a spiral slide 303, a launching spring 304 and a hammer 302 are all disposed inside the power housing 301.

[0057] Specifically, the first through hole 231 is connected to the power housing 301 on the side facing the power assembly. Below the first through hole 231 of the launch chamber rear cover 23, on the side facing the trigger assembly, there is a locking extension groove 411, with part of the front of the locking iron 401 placed in the locking extension groove 411. The receiving cavity inside the power housing 301 can be divided into a front cavity and a rear cavity. The front cavity is used to house the fixing baffle 305, the spiral slide 303, the launch spring 304, and the hammer 302. The rear cavity is used to house the motor 306, the first gear 307, and part of the gear chain 309. The diameter of the front opening is slightly larger than the diameter of the first through hole 231 of the launch chamber rear cover 23, and the front opening is coaxial with the first through hole 231 of the launch chamber rear cover 23. In the rear cavity, there is a strip-shaped through hole at the bottom corresponding to the first gear 307, allowing the gear chain 309 to pass through and connect with the second gear 308. The rear end has a mounting groove that allows the rear end of the motor 306 to be embedded to fix the motor 306.

[0058] In some embodiments, the trigger assembly further includes a trigger housing 405 disposed on the side of the power housing 301, a locking block 401 and a second gear 308 disposed within the trigger housing 405, a gear chain 309 extending from the power housing 301 into the trigger housing 405, and a trigger 404 extending from a through hole in the trigger housing 405. The power housing 301 may be fixed above the trigger housing 405, and a motor 306 connected to a motor circuit to control its rotation may be located inside the trigger housing 405.

[0059] In some embodiments, the parameters of the launching spring 304 satisfy the following formula:

[0060]

[0061] Where H0 is the original length of the launching spring 304, and the unit of H0 is mm; f n f is the maximum deformation of the launching spring 304. n The unit is mm; F ′ F is the spring constant of the launching spring 304. ′ The unit is N / mm; m w For the mass of UAV 1, m w The unit is kg; m j For the mass of hammer 302, m j The unit is kg; V wV is the launch velocity of UAV 1. w The unit is m / s; H s H represents the vertical height of the handheld launcher. s The unit is mm.

[0062] In some embodiments, the detailed parameters of the selected launch spring 304 can be as follows: Figure 10 As shown in the table below. (Reference) Figure 10 Assuming V is launched w Reaching a maximum speed of approximately 30 m / s instantaneously, we can calculate:

[0063]

[0064] Obviously The launch spring 304 meets the launch requirements.

[0065] In some embodiments, the trigger assembly further includes a catch spring 403 and a trigger inner shell 402. The trigger inner shell 402 is disposed on the side of the launch chamber rear cover 23 away from the launch chamber 22. When the hammer 302 is in the charging position, the trigger inner shell 402 is disposed below the hammer 302. One end of the catch 401 extends from the side of the trigger inner shell 402 away from the hammer 302 to the front end of the hammer 302. The other end of the catch 401 is disposed on the trigger inner shell 402 through the catch spring 403.

[0066] Specifically, the upper side of the tail of the locking bar 401 is connected to the locking bar spring 403, and the lower side is fixed to the trigger 404. The upper end of the locking bar spring 403 is fixed to the inner shell of the trigger 402, and the lower end is fixed to the tail of the locking bar 401. The locking bar 401 is located directly below the front cavity of the power housing 301. The top of the front end of the locking bar 401 is slightly higher than the edge of the hammer 302, so that the locking bar 401 can prevent the hammer 302 from being ejected. The middle part of the locking bar 401 has a pivot connecting to the inner shell of the trigger 402, so that the locking bar 401 can rotate up and down along the pivot. The trigger 404 is fixed to the lower side of the tail of the locking bar 401, and the locking bar spring 403 is fixed to the upper side. With the launch port 211 of the handheld launcher facing the air, when the trigger 404 is pulled, the rear end of the catch 401 rises and the front end lowers, thereby releasing the hammer 302. Under the action of the launch spring 304, the hammer 302 pushes the UAV 1 upward through the first through hole 231 of the launch chamber rear cover 23, thus completing one launch process.

[0067] Specifically, when launching, one hand holds the trigger housing 405, and the other hand supports the auxiliary hand-held structure 213 on the launch chamber housing 21, placing the entire hand-held launch structure vertically with the launch port 211 facing upward. Pulling the trigger 404 causes the rear end of the catch 401 to rise and the front end to fall, thereby releasing the hammer 302. Under the action of the launch spring 304, the hammer 302 pushes the UAV 1 forward through the first through hole 231 of the launch chamber rear cover 23, completing one launch process.

[0068] refer to Figure 11 After motor 306 is energized and completes one automatic switching of launch port 221 and power accumulation, pulling trigger 404 launches drone 1. Then motor 306 is energized again to automatically switch launch port 221 and power accumulation, waiting to pull trigger 404 again to launch drone 1. This process continues, meaning that every time trigger 404 is pulled to launch drone 1, motor 306 is energized to automatically switch launch port 221 and power accumulation in preparation for another launch. Furthermore, since three drones 1 can be loaded into the handheld launcher at a time, one to three drones 1 can be launched into the air consecutively. Drones 1 can fly individually or form a small swarm in the air, achieving collective intelligence and collaborative effects.

[0069] It should be understood that the various forms of processes shown above can be used to reorder, add, or delete steps. For example, the steps described in this invention disclosure can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution disclosed in this invention can be achieved, and this is not limited herein.

[0070] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A drone launching device, characterized in that, include: A handheld launching structure, comprising a launching chamber assembly, a power assembly, and a trigger assembly; The launch chamber assembly includes a launch chamber having multiple launch ports for mounting drones. The power assembly includes a hammer and a drive unit connected to each other. The drive unit rotates the launch chamber to switch the launch port facing the hammer. While rotating the launch chamber, the drive unit also moves the hammer away from the launch chamber until the hammer reaches the charging position. The trigger assembly includes a locking block and a trigger connected to each other. The locking block holds the hammer in the charging position. When the trigger is pulled, the locking block releases the hammer, and the hammer propels the drone out of the launch port facing the hammer. An automatic wing-deploying structure is installed on the body of a drone. The automatic wing-deploying structure includes a rotor mounting frame and a rotor. The rotor mounting frame is installed on the drone body via a first rotation axis. The rotor is installed on the rotor mounting frame. When the drone is located in the launch port, the rotor mounting frame drives the rotor to fit against the side of the drone body. After the drone is launched, the rotor mounting frame drives the rotor to deploy.

2. The UAV launching device according to claim 1, characterized in that, The automatic wing deployment structure also includes a torsion spring, a magnet, and an iron core with a coil wound around it. The torsion spring cooperates with the first rotating shaft and is connected to the rotor mounting frame and the UAV body. The iron core is fixed to the UAV body, and the magnet is fixed to the rotor mounting frame. When the UAV is located in the launch port, the coil is energized, and the magnet, under the magnetic force of the iron core, causes the rotor to adhere to the side of the UAV body through the rotor mounting frame. After the UAV is launched, the coil is de-energized to allow the rotor to deploy.

3. The UAV launching device according to claim 1, characterized in that, The launch chamber is cylindrical, the launch holes penetrate the launch chamber along the axial direction, and a plurality of the launch holes are arranged at intervals around the axis of the launch chamber. The launch chamber has a central hole that penetrates the launch chamber along its axis. The launch chamber assembly also includes a central shaft, a launch chamber shell, and a launch chamber rear cover; The central axis is disposed in the central axis hole, the launch chamber is sleeved in the launch chamber shell, the launch chamber is rotatable relative to the launch chamber shell around the central axis, one end of the central axis is connected to the first end of the launch chamber shell, and the first end of the launch chamber shell has a launch port, and the launch hole facing the hammer is also facing the launch port. The launch chamber rear cover is disposed at the second end of the launch chamber shell via a second rotating shaft. The launch chamber rear cover has a second through hole and a first through hole opposite to the hammer. The power assembly and the trigger assembly are disposed on the side of the launch chamber rear cover away from the launch chamber shell. The drive unit is connected to the launch chamber via a connector disposed in the second through hole to drive the launch chamber to rotate along its axis.

4. The UAV launching device according to claim 3, characterized in that, The connector includes a grooved wheel, a dial, and a connecting rod. The grooved wheel is fixed to one end of the launch chamber facing the rear cover of the launch chamber and is directly opposite the central shaft. The side of the dial contacts the side of the grooved wheel and is fixed to the first end of the connecting rod. The connecting rod passes through the second through hole and the second end of the connecting rod is connected to the drive unit. The drive unit includes a motor, a first gear, a second gear, and a gear chain. The motor shaft of the motor is connected to the first gear, the first gear is connected to the second gear via the gear chain, and the second end of the connecting rod is connected to the second gear. The motor drives the first gear to rotate, the first gear drives the second gear to rotate through the gear chain, and the second gear drives the dial to rotate through the connecting rod, so that the dial moves the slotted wheel, thereby causing the firing chamber to rotate to switch the firing port facing the hammer.

5. The UAV launching device according to claim 4, characterized in that, The surface of the launch chamber rear cover facing the launch chamber has an irregular groove, and the grooved wheel and the dial are both disposed in the irregular groove.

6. The UAV launching device according to claim 4, characterized in that, The drive unit further includes a spiral slide, a launching spring, and a fixed baffle. The fixed baffle, the spiral slide, the launching spring, and the hammer are located on the side of the first gear away from the motor. The fixed baffle, the launching spring, and the hammer are connected in sequence and arranged in a direction away from the first gear. The spiral slide is located on the inner ring of the hammer and the inner ring of the launching spring. The first end of the spiral slide is connected to the hammer, and the other end of the spiral slide passes through the fixed baffle and is connected to the motor shaft of the motor. The motor drives the spiral slide to rotate, and the spiral slide drives the hammer to move towards the fixed baffle through the pin in the inner ring of the hammer. The launching spring is compressed until the hammer reaches the power storage position, and the pin is disconnected from the thread of the spiral slide, thus completing the power storage operation. After the trigger is pulled, the locking block releases the hammer, the launch spring pushes the hammer, and the hammer propels the drone out of the launch port.

7. The UAV launching device according to claim 6, characterized in that, The drive unit also includes a power housing, and the motor, the first gear, part of the gear chain, the fixed baffle, the spiral slide, the launching spring and the hammer are all disposed inside the power housing.

8. The UAV launching device according to claim 7, characterized in that, The trigger assembly further includes a trigger housing disposed on the side of the power housing, the locking block and the second gear are disposed inside the trigger housing, the gear chain extends from the power housing into the trigger housing, and the trigger extends out of the trigger housing from a through hole on the trigger housing.

9. The UAV launching device according to claim 6, characterized in that, The parameters of the launching spring satisfy the following formula: Wherein, H0 is the original length of the launching spring, and the unit of H0 is mm; f n f is the maximum deformation of the launching spring. n The unit is mm; F ′ F is the spring constant of the launching spring. ′ The unit is N / mm; m w Let m be the mass of the drone. w The unit is kg; m j Let m be the mass of the hammer. j The unit is kg; V w V is the launch speed of the UAV. w The unit is m / s; H s H is the vertical height of the handheld launching structure. s The unit is mm.

10. The UAV launching device according to claim 3, characterized in that, The trigger assembly also includes a catch spring and a trigger inner shell. The trigger inner shell is located on the side of the launch chamber rear cover away from the launch chamber. When the hammer is in the charging position, the trigger inner shell is located below the hammer. One end of the catch extends from the side of the trigger inner shell away from the hammer to the front end of the hammer, and the other end of the catch is mounted on the trigger inner shell by the catch spring.

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