Unmanned aerial vehicle launching device

Abstract

The invention relates to the technical field of flight equipment, in particular to an unmanned aerial vehicle launching device which comprises a handheld launching structure which comprises a launching bin assembly, a power assembly and a trigger assembly. The launching bin assembly comprises a launching bin, the launching bin is provided with a plurality of launching holes used for loading the unmanned aerial vehicle, and the power assembly comprises a driving hammer and a driving unit; the driving unit is used for driving the launching bin to rotate so as to switch the launching holes right opposite to the driving hammer, and the driving unit further drives the driving hammer to move in the direction away from the launching bin till the driving hammer reaches the force storage position. The trigger assembly comprises a clamping iron and a trigger which are connected with each other, the clamping iron limits the driving hammer at the force storage position, after the trigger is pulled, the clamping iron releases the driving hammer, and the driving hammer pushes the unmanned aerial vehicle in the launching hole right opposite to the driving hammer to be launched; and the automatic wing unfolding structure is arranged on the unmanned aerial vehicle body. The method is at least beneficial to improving the convenience of launching the multiple unmanned aerial vehicles.

Description

Technical Field

[0001] The invention belongs to the technical field of flight equipment, and in particular relates to a UAV launching device. Background Art

[0002] The proposal of the drone launch device is aimed at improving the flexibility, regional adaptability and survivability of the drone system. At present, drones have the advantages of compact size, flexible maneuverability, vertical take-off and landing, low noise, long endurance and strong environmental adaptability. They are very suitable for combination with drone launch devices for use in scenarios that require rapid deployment and covert operations.

[0003] The patent with application publication number CN113044233A provides a UAV launching device. Specifically, the UAV is fixed in a launching tube, and the high-pressure gas stored in the gas cylinder is transported to the launching tube through a connecting pipe. The solenoid valve controls the release of the gas. When the solenoid valve is opened, the high-pressure gas pushes the UAV to be quickly launched from the launching tube. The device structurally only supports the fixing and launching of a single UAV. If multiple UAVs are launched continuously, repeated loading and setting are required, which increases the complexity and time of the operation. If the gas in the gas cylinder is not replenished in time, it may not provide sufficient thrust to stably launch the UAV. Especially in the case of launching multiple UAVs continuously, the subsequently launched UAVs may fail to achieve the expected launching effect due to insufficient gas pressure, increasing the safety risk during the launching process and affecting the success rate of the launching and the flight stability of the UAV.

[0004] The patent with application publication number CN109436364A provides a device for continuous launch of UAVs, wherein a storage device is used to store UAVs, a conveying device is used to transport UAVs from the storage device to a pulley, and an automatic loading device is responsible for transferring the UAV to the pulley. There are at least three catapults on the rotating tube multi-track UAV catapult, each of which is docked with a pulley to provide the pulley with driving force during ejection. During launch, the conveying chain and the hook cooperate to achieve the docking and separation of the UAV. The automatic loading device transports and docks the UAV to the pulley bracket structure by rotation. After the catapult ejects the UAV, it automatically resets to prepare for the next launch. Although the device improves the launch efficiency of the UAV, its structure is relatively complex and involves multiple precisely matched components, which makes the entire system bulky, reduces the portability of the device, and requires complex connection and debugging processes, increasing the risk of failure in actual operation. In addition, the complex structure requires more time and resources to train operators to ensure that the loading, launching and resetting operations of the UAV can be performed correctly. Summary of the invention

[0005] In view of this, the present invention aims to provide a UAV launching device, which is at least helpful in improving the convenience of launching multiple UAVs.

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

[0007] The invention provides a UAV launching device, comprising: a handheld launching structure, the handheld launching structure comprising a launching chamber assembly, a power assembly and a trigger assembly; the launching chamber assembly comprises a launching chamber, the launching chamber has a plurality of launching holes for loading UAVs, the power assembly comprises a connected hammer and a driving unit; the driving unit is used to drive the launching chamber to rotate so as to switch the launching holes directly facing the hammer, and while the driving unit drives the launching chamber to rotate, it also drives the hammer to move in a direction away from the launching chamber until the hammer reaches a power storage position; the trigger assembly comprises a connected clamp and a trigger, the clamp limits the hammer at the power storage position, after the trigger is pulled, the clamp releases the hammer, and the hammer pushes the UAV in the launching hole directly facing the hammer to be launched; an automatic wing spreading structure arranged on the UAV body, the automatic wing spreading structure comprises a rotor fixing frame and a rotor, the rotor fixing frame is arranged on the UAV body through a first rotating shaft, the rotor is arranged on the rotor fixing frame, when the UAV is located in the launching hole, the rotor fixing frame drives the rotor to fit on the side of the UAV body, and after the UAV is launched, the rotor fixing frame drives the rotor to spread out.

[0008] In some embodiments, the automatic wing-spreading structure also includes a torsion spring, a magnet, and an iron core wound with a coil. The torsion spring cooperates with the first rotating shaft, and the torsion spring is connected to the rotor fixing frame and the UAV body. The iron core is fixed on the UAV body, and the magnet is fixed on the rotor fixing frame. When the UAV is located in the launch hole, the coil is energized, and the magnet is acted upon by the magnetic force of the iron core to make the rotor fit to the side of the UAV body through the rotor fixing frame. After the UAV is launched, the coil is de-energized to allow the rotor to unfold.

[0009] In some embodiments, the launch chamber is cylindrical, the launch hole passes through the launch chamber along the axial direction of the launch chamber, and the multiple launch holes are arranged at intervals around the axis of the launch chamber, and the launch chamber has a central axis hole passing through the launch chamber along its axis; the launch chamber assembly also includes a central axis, a launch chamber shell and a launch chamber back cover; wherein, the central axis is arranged 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 opposite to the hammer is also opposite to the launch port; the launch chamber back cover is arranged at the second end of the launch chamber shell through a second rotating axis, the launch chamber back cover has a second through hole and a first through hole opposite to the hammer, the power assembly and the trigger assembly are arranged on the side of the launch chamber back cover away from the launch chamber shell, and the driving unit is connected to the launch chamber through a connecting piece arranged in the second through hole to drive the launch chamber to rotate along its axis.

[0010] In some embodiments, the connecting member includes a groove wheel, a dial and a connecting rod, the groove wheel is fixed at one end of the launching chamber facing the rear cover of the launching chamber, and the groove wheel is opposite to the central axis, the side of the dial is in contact with the side of the groove wheel, and the dial is fixed to the first end of the connecting rod, the connecting rod is penetrated in the second through hole, and the second end of the connecting rod is connected to the driving unit; the driving 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 through the gear chain, and the second end of the connecting rod is connected to the second gear; wherein, 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 drives the groove wheel, and then the launching chamber rotates to switch the launching hole opposite to the hammer.

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

[0012] In some embodiments, the drive unit also 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, and 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 on 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 toward the fixed baffle through the pin on 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 to complete the power storage operation; after pulling the trigger, the latch releases the hammer, the launching spring pushes the hammer, and the hammer pushes the drone in the launching hole to shoot out.

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

[0014] In some embodiments, the trigger assembly also includes a trigger housing disposed on the side of the power housing, a latch and a second gear are disposed in the trigger housing, the gear chain automatically extends from the power housing into the trigger housing, and the trigger extends from the trigger housing through a through hole on the trigger housing.

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

[0016]

[0017] Among them, H 0 is the original length of the launching spring, H 0 The unit is mm; f nis the maximum deformation of the launching spring, f n The unit is mm; F ′ is the stiffness constant of the launching spring, F ′ The unit is N / mm; m w is the mass of the drone, m w The unit is kg; m j is the mass of the hammer, m j The unit is kg; V w is the launch speed of the drone, V w The unit of H is m / s; s is the vertical height of the handheld launch structure, H s The unit is mm.

[0018] In some embodiments, the trigger assembly also includes a latch spring and a trigger inner shell. The trigger inner shell is arranged on the side of the rear cover of the launching chamber away from the launching chamber, and when the hammer is in the power storage position, the trigger inner shell is arranged below the hammer. One end of the latch 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 latch is arranged on the trigger inner shell through the latch spring.

[0019] Compared with the prior art, the invention can achieve the following beneficial effects: the UAV launch device provided by the embodiment of the invention includes a handheld launch structure, which can store the UAV in a folded state in the handheld launch structure during transportation and storage, and multiple UAVs can be launched continuously after one loading, and after the UAV is launched, the automatic wing-spreading structure can automatically unfold the rotor of the UAV for flight; the handheld launch structure can realize rapid power accumulation of the hammer through the cooperation of the power component and the trigger component, so as to achieve the purpose of rapid launch of the UAV after launch; the handheld launch structure can realize automatic rotation of the launch chamber after each launch through the cooperation of the groove wheel and the dial, so as to provide the UAV for another launch; the buckle provided on the launch chamber shell and the slot provided on the rear cover of the launch chamber cooperate to realize rapid loading of the UAV.

[0020] In summary, the drone launch device provided in the embodiment of the present invention is not restricted by the launch site, is convenient for the storage and transportation of drones, and has a rapid launch process. When the drone is launched, it can quickly take off and automatically spread its wings, and multiple drones can be launched continuously to achieve group intelligence and coordination effects. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The drawings constituting part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments and descriptions of the present invention are used to explain the present invention and do not constitute an improper limitation on the present invention. In the drawings:

[0022] Figure 1 A schematic diagram of the structure of the drone according to an embodiment of the present invention;

[0023] Figure 2 A schematic diagram of the structure of the automatic wing spreading structure according to an embodiment of the present invention;

[0024] Figure 3 A structural schematic diagram of a handheld transmitting structure according to an embodiment of the present invention;

[0025] Figure 4 A schematic diagram of the structure of the launch chamber and the connecting member according to an embodiment of the present invention;

[0026] Figure 5 A structural schematic diagram of a filling state of a handheld launching structure according to an embodiment of the present invention;

[0027] Figure 6 A detailed structural diagram of a handheld transmitting structure according to an embodiment of the present invention;

[0028] Figure 7 A schematic diagram of the structure of a power assembly and a trigger assembly of a handheld launch structure according to an embodiment of the present invention;

[0029] Figure 8 A side view of a partial structure of a handheld launch structure according to an embodiment of the present invention;

[0030] Fig. 9 A schematic diagram of the structure of the hammer, spiral slide, launch spring and fixed baffle of the handheld launch structure according to the embodiment of the present invention;

[0031] Fig.10 A table diagram of the parameters of the launch spring described in the embodiment of the present invention;

[0032] Fig.11 The present invention is a flowchart of launching a drone using the drone launching device according to an embodiment of the present invention.

[0033] Description of reference numerals: 1, UAV; 111, iron core; 112, magnet; 113, rotor; 114, rotor fixing frame; 21, launch chamber shell; 211, launch port; 212, buckle; 213, auxiliary hand-held structure; 22, launch chamber; 23, launch chamber rear cover; 231, first through hole; 232, slot; 24, central axis; 301, power housing; 302, hammer; 303, spiral slide; 304 , launching spring; 305, fixed baffle; 306, motor; 307, first gear; 308, second gear; 309, gear chain; 310, groove wheel; 311, dial; 401, latch; 402, trigger inner shell; 403, latch spring; 404, trigger; 405, trigger outer shell; 313, pin; 312, connecting rod; 221, launching hole; 233, special-shaped groove; 411, latch extension groove. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solution and advantages of the invention more clear, the invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described here are only used to explain the invention and do not constitute a limitation of the invention.

[0035] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0036] In the description of the invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the invention, unless otherwise specified, the meaning of "multiple" is two or more.

[0037] In the description of the invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the invention can be understood according to specific circumstances.

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

[0039] refer to Figures 1 to 9 The present invention provides a UAV launch device, comprising: a handheld launch structure, the handheld launch structure is used for storing, transporting and launching a plurality of UAVs 1 with automatic wing-spreading structures, the handheld launch structure comprises a launch chamber assembly, a power assembly and a trigger assembly; the launch chamber assembly comprises a launch chamber 22, the launch chamber 22 has a plurality of launch holes 221 for loading the UAVs 1, the launch chamber 22 is used for storing and transporting a plurality of UAVs 1 with automatic wing-spreading structures, the power assembly comprises a connected hammer 302 and a drive unit; the drive unit is used for driving the launch chamber 22 to rotate so as to switch the launch holes 221 facing the hammer 302, and while the drive unit drives the launch chamber 22 to rotate, it also drives the hammer 302 to move in a direction away from the launch chamber 22 until the hammer 302 reaches the power storage position; the trigger assembly comprises a connected The latch 401 and the trigger 404, the latch 401 limits the hammer 302 in the power storage position, after the trigger 404 is pulled, the latch 401 releases the hammer 302, and the hammer 302 pushes the UAV 1 in the launching hole 221 opposite to the hammer 302 to be launched; an automatic wing-spreading structure is arranged on the body of the UAV 1, and the automatic wing-spreading structure can make the UAV 1 automatically unfold the rotor 113 after it is lifted into the air. The automatic wing-spreading structure includes a rotor fixing frame 114 and rotor 113, the rotor fixing frame 114 is arranged on the body of the UAV 1 through a first rotating axis, and the rotor 113 is arranged on the rotor fixing frame 114. When the UAV 1 is located in the launching hole 221, the rotor fixing frame 114 drives the rotor 113 to fit against the side of the UAV 1 body. After the UAV 1 is launched, the rotor fixing frame 114 drives the rotor 113 to unfold.

[0040] In some embodiments, reference Figure 1 The UAV 1 can be a micro coaxial twin-rotor UAV. The technology of this type of UAV is currently mature and will not be described in detail here.

[0041] The power assembly provided in the embodiment of the present invention can synchronize the automatic switching of the launch hole 221 and the rapid power accumulation process, which is beneficial to reducing the volume of the entire UAV launch device and facilitating handheld launch; the trigger assembly can instantly release the hammer 302, so that the UAV 1 in the launch hole 221 facing the hammer 302 obtains a larger thrust to achieve rapid lift-off.

[0042] In some embodiments, reference Figure 2 The automatic wing-spreading structure also includes a torsion spring, a magnet 112, and an iron core 111 wound with a coil (not shown). The torsion spring cooperates with the first rotating shaft, and the torsion spring is connected to the rotor fixing frame 114 and the UAV 1 body. The iron core 111 is fixed to the UAV 1 body, and the magnet 112 is fixed to the rotor fixing frame 114. When the UAV 1 is located in the launching hole 221, the coil is energized, and the magnet 112 is acted upon by the magnetic force of the iron core 111 to make the rotor 113 fit to the side of the UAV 1 body through the rotor fixing frame 114. After the UAV 1 is launched, the coil is de-energized to allow the rotor 113 to unfold.

[0043] Specifically, the rotor fixing frame 114 has a notch coaxial with the first rotation axis, the torsion spring is fixed in the notch, the iron core 111 is located at the fuselage part that can completely overlap with the magnet 112 when the rotor 113 is folded, and the coil wound on the iron core 111 is connected to the circuit, and the torsion spring will drive the rotor fixing frame 114 to support the rotor 113 to open when it is not under force. When the drone 1 is in the handheld launch structure, the coil on the iron core 111 is energized to make it magnetic and attract the magnet 112. At this time, the torsion spring is compressed by force, and the rotor 113 is folded. When the drone 1 is launched into the air and the acceleration drops to zero, the circuit connected to the iron core 111 disconnects the coil, the iron core 111 loses its magnetism and can no longer attract the magnet 112. The torsion spring returns to its original state, and the rotor 113 is unfolded.

[0044] In some embodiments, reference Figure 3 and Figure 4The launch chamber 22 is cylindrical, the launch hole 221 penetrates the launch chamber 22 along the axial direction of the launch chamber 22, and the plurality of launch holes 221 are arranged at intervals around the axis of the launch chamber 22, and the launch chamber 22 has a central axis hole penetrating the launch chamber 22 along its axis; the launch chamber assembly further includes a central axis 24, a launch chamber shell 21 and a launch chamber back cover 23; wherein the central axis 24 is arranged in the central axis hole, the launch chamber 22 is sleeved in the launch chamber shell 21, the launch chamber 22 is rotatable relative to the launch chamber shell 21 around the central axis 24, and one end of the central axis 24 is connected to the first end of the launch chamber shell 21 The launch chamber shell 21 is connected, and the first end of the launch chamber shell 21 has a launch port 211, and the launch hole 221 opposite to the hammer 302 is also opposite to the launch port 211; the launch chamber rear cover 23 is arranged at the second end of the launch chamber shell 21 through a second rotating axis, the launch chamber rear cover 23 has a second through hole and a first through hole 231 opposite to the hammer 302, the power assembly and the trigger assembly are arranged on the side of the launch chamber rear cover 23 away from the launch chamber shell 21, and the driving unit is connected to the launch chamber 22 through a connecting piece arranged in the second through hole to drive the launch chamber 22 to rotate along its axis.

[0045] Specifically, refer to Figure 5 The front cover of the launch chamber shell 21 has a circular launch port 211, and the diameter of the launch port 211 is the same as the diameter of the launch hole 221 of the launch chamber 22. An auxiliary hand-held structure 213 is provided at the bottom of the front end of the launch chamber shell 21. Two buckles 212 at the rear end of the launch chamber shell 21 are buckled with the slots 232 on the launch chamber back cover 23. The launch chamber 22 is in the launch chamber shell 21, and the launch chamber 22 is coaxial with the launch chamber shell 21. The launch chamber back cover 23 is buckled with the launch chamber shell 21. When the buckle 212 of the launch chamber shell 21 is opened, the launch chamber back cover 23 can be opened along the second rotation axis. At this time, multiple drones 1 can be loaded into the launch chamber 22 at one time, and then the launch chamber back cover 23 is closed, and the buckle 212 of the launch chamber shell 21 is buckled with the slot 232 of the launch chamber back cover 23 again to complete the loading process of the drone 1.

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

[0047] In some embodiments, reference Figure 4 , Figure 6 , Figure 7 as well as Figure 8The connecting member includes a groove wheel 310, a dial 311 and a connecting rod 312. The groove wheel 310 is fixed to one end of the launch chamber 22 facing the launch chamber rear cover 23, and the groove wheel 310 is directly opposite to the middle axis 24. The side of the dial 311 contacts the side of the groove wheel 310, and the dial 311 is fixed to the first end of the connecting rod 312. The connecting rod 312 is arranged in the second through hole, and the second end of the connecting rod 312 is connected to the driving unit; the driving unit includes a motor 306, a first gear 307, a second gear 308 and a gear chain 309. The motor 306 is electrically connected to the drive unit 306. The machine shaft is connected to the first gear 307 in transmission connection, the first gear 307 is connected to the second gear 308 through the gear chain 309, and the second end of the connecting rod 312 is connected to the second gear 308; wherein, the motor 306 drives the first gear 307 to rotate, 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 connecting rod 312, so that the dial 311 drives the groove wheel 310, and then the launching chamber 22 rotates to switch the launching hole 221 opposite to the hammer 302.

[0048] Specifically, refer to Figures 4 to 8 , the dial 311 is connected to the hub of the second gear 308, the groove wheel 310 is fixed to the rear center of the launch chamber 22, and the launch chamber rear cover 23 has a circular power port, namely the first through hole 231. The diameter of the first through hole 231 is equal to the diameter of the launch hole 221 of the launch chamber 22, and is coaxial with the launch hole 211 directly facing the hammer 302. The groove 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 groove wheel 310 is fixed to the launch chamber 22, and the groove corresponds to the launch hole 221 of the launch chamber 22.

[0049] In some embodiments, the dial 311 is composed of a dial pin and a convex arc, the radius of the concave arc of the groove wheel 310 and the convex arc of the dial 311 are equal, the dial 311 is placed on one side of the groove wheel 310, and the convex arc of the dial 311 is completely fitted with a concave arc of the groove wheel 310, and 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 groove wheel 310 contacts the convex arc of the dial 311, the groove wheel 310 cannot rotate, and the launch chamber 22 fixed to the groove wheel 310 cannot rotate either. At this time, a certain launch hole 221 of the launch chamber 22 is opposite to the launch port 211 of the launch chamber shell 21, and the UAV 1 in the launch hole 221 opposite to the launch port 211 is waiting for launch. When the pin of the dial 311 contacts the groove of the groove wheel 310, the groove wheel 310 is forced to rotate and rotates 120° each time. The launch chamber 22 fixed to the groove wheel 310 is driven by the groove wheel 310 to rotate 120° around the central axis 24. At this time, the next launch hole 221 of the launch chamber 22 is opposite to the launch port 211 of the launch chamber shell 21, and the UAV 1 in the launch hole 221 opposite to the launch port 211 is waiting for launch.

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

[0052] In some embodiments, reference Figure 8 and Fig. 9 The driving unit further includes: a spiral slide 303, a launching spring 304 and a fixed baffle 305. The fixed baffle 305, the spiral slide 303, the launching spring 304 and the hammer 302 are located on the side of the first gear 307 away from the motor 306, and the fixed baffle 305, the launching spring 304 and the hammer 302 are sequentially connected 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 penetrates 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 toward the fixed baffle 305 through the pin 313 on the inner ring of the hammer 302, and the launching spring 304 is compressed until the hammer 302 reaches the power storage position, and the pin 313 is disconnected from the thread of the spiral slide 303, completing the power storage operation; after pulling the trigger 404, the latch 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 shoot out.

[0053] It should be noted that the hammer 302 is a column with an opening at the rear end, a hollow structure in the middle part and a closed front end. The cross-sectional diameter of the hammer 302 may 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 circle of the hammer 302 has two symmetrical pins 313, and the pins 313 are in contact with the spiral slide 303. The spiral slide 303 is a column with a spiral slide groove wound around 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 the circuit, and the motor shaft drives the first gear 307 and the spiral slide 303 to rotate, thereby realizing the automatic switching of the launch hole 221 and the synchronous accumulation of power.

[0054] The process of automatically switching the launch hole 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 to control the launch chamber 22 to rotate and switch the launch hole 221.

[0055] The power storage process is specifically as follows: when the spiral slide 303 rotates, it will press the pin 313 on the hammer 302 to move backward, thereby moving the hammer 302 backward. Since the hammer 302 is connected to the firing spring 304, the firing spring 304 will be compressed. When the spiral slide 303 rotates to the power storage position, the spring is compressed to the tightest, the hammer 302 is stuck on the clamp 401, and the pin 313 is separated from the thread of the spiral slide 303 and is no longer subjected to force. At this time, the motor 306 stops rotating, and the power storage process is completed.

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

[0057] Specifically, the first through hole 231 is connected to the power housing 301 on the side facing the power assembly, and a clamp extension groove 411 is provided on the side facing the trigger assembly below the first through hole 231 of the launch chamber rear cover 23, and a part of the front part of the clamp 401 is placed in the clamp extension groove 411. The accommodating chamber in the power housing 301 can be divided into a front chamber and a rear chamber, the front chamber is used to set the fixed baffle 305, the spiral slide 303, the launch spring 304 and the hammer 302, and the rear chamber is used to set the motor 306, the first gear 307 and part of the gear chain 309, the front opening diameter of the front chamber is slightly larger than the diameter of the first through hole 231 of the launch chamber rear cover 23, and the front opening of the front chamber is coaxial with the first through hole 231 of the launch chamber rear cover 23, and the bottom of the rear chamber corresponding to the first gear 307 has a strip through hole so that the gear chain 309 can pass through and connect with the second gear 308, and the rear end has a mounting groove inside so that the rear end of the motor 306 can 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, the latch 401 and the second gear 308 are disposed in the trigger housing 405, the gear chain 309 extends from the power housing 301 to the trigger housing 405, and the trigger 404 extends from the trigger housing 405 through a through hole on the trigger housing 405. The power housing 301 can be fixed above the trigger housing 405, and the motor 306 is connected to a motor circuit to control its rotation, and the motor circuit can be placed inside the trigger housing 405.

[0059] In some embodiments, the parameters of the launch spring 304 satisfy the following equation:

[0060]

[0061] Among them, H 0 is the original length of the launching spring 304, H 0 The unit is mm; f n is the maximum deformation of the launching spring 304, f n The unit is mm; F ′ is the stiffness constant of the launch spring 304, F ′ The unit is N / mm; m w is the mass of UAV 1, m w The unit is kg; m j is the mass of hammer 302, m j The unit is kg; V w is the launch speed of UAV 1, V w The unit of H is m / s; s is the vertical height of the handheld launch structure, H s The unit is mm.

[0062] In some embodiments, the detailed parameters of the selected launch spring 304 can be as follows: Fig.10 Reference Fig.10 , assuming that V w The maximum speed reaches about 30m / s in an instant, which can be calculated as follows:

[0063]

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

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

[0066] Specifically, the upper side of the tail of the latch 401 is connected to the latch spring 403, and the lower side is fixed on the trigger 404. The upper end of the latch spring 403 is fixed on the trigger inner shell 402, and the lower end is fixed to the tail of the latch 401. The latch 401 is located directly below the front cavity of the power housing 301. The top of the front end of the latch 401 is slightly higher than the edge of the hammer 302, so that the latch 401 can prevent the hammer 302 from popping out. The middle part of the latch 401 has a rotating shaft connected to the trigger inner shell 402 so that the latch 401 can rotate up and down along the rotating shaft. The trigger 404 is fixed on the lower side of the tail of the latch 401, and the latch spring 403 is fixed on the upper side. The launching port 211 of the handheld launching structure is pointed toward the air. When the trigger 404 is pulled, the rear end of the latch 401 rises and the front end lowers, thereby releasing the hammer 302. The hammer 302, under the action of the launching spring 304, pushes the drone 1 upward through the first through hole 231 of the launch chamber rear cover 23 to complete a launching process.

[0067] Specifically, when launching, one hand holds the trigger housing 405, and the other hand supports the auxiliary hand-held structure 213 of the launch chamber shell 21, and the entire hand-held launch structure is placed vertically with the launch port 211 facing upwards. The trigger 404 is pulled, and the rear end of the latch 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 drone 1 forward through the first through hole 231 of the launch chamber rear cover 23 to complete a launch process.

[0068] refer to Fig.11After the motor 306 is powered on to automatically switch the launch hole 221 and store power once, the trigger 404 is pulled to launch the drone 1 once, and then the motor 306 is powered on again to automatically switch the launch hole 221 and store power, waiting for the trigger 404 to be pulled again to launch the drone 1, and so on, that is, every time the trigger 404 is pulled to launch the drone 1, the motor 306 will be powered on to automatically switch the launch hole 221 and store power to wait for another launch. In addition, since three drones 1 can be loaded into the handheld launch structure at one time, one to three drones 1 can be launched into the air continuously, and the drone 1 can either fly alone or form a small drone 1 group in the air to achieve group intelligence and coordination 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 the disclosure of the present invention can be performed in parallel, sequentially or in different orders, as long as the desired results of the technical solution disclosed in the present invention can be achieved, and this document does not limit this.

[0070] The above specific implementations do not constitute a limitation on the protection scope of the present invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A UAV launching device, characterized in that: include: A handheld launching structure, comprising a launching chamber assembly, a power assembly and a trigger assembly; The launch bin assembly includes a launch bin, and the launch bin has a plurality of launch holes for loading drones. The power assembly includes a connected hammer and a drive unit; the drive unit is used to drive the launch bin to rotate so as to switch the launch hole directly opposite to the hammer. While the drive unit drives the launch bin to rotate, it also drives the hammer to move in a direction away from the launch bin until the hammer reaches a power storage position; the trigger assembly includes a connected latch and a trigger, the latch limits the hammer at the power storage position, and after the trigger is pulled, the latch releases the hammer, and the hammer pushes the drone in the launch hole directly opposite to the hammer to be ejected; An automatic wing-spreading structure is arranged on a UAV body, the automatic wing-spreading structure comprises a rotor fixing frame and a rotor, the rotor fixing frame is arranged on the UAV body through a first rotating shaft, the rotor is arranged on the rotor fixing frame, when the UAV is located in the launching hole, the rotor fixing frame drives the rotor to fit into the side of the UAV body, after the UAV is launched, the rotor fixing frame drives the rotor to spread out.

2. The UAV launch device according to claim 1, characterized in that: The automatic wing-spreading structure also includes a torsion spring, a magnet, and an iron core wound with a coil. The torsion spring cooperates with the first rotating shaft, and the torsion spring is connected to the rotor fixing frame and the UAV body. The iron core is fixed to the UAV body, and the magnet is fixed to the rotor fixing frame. When the UAV is located in the launching hole, the coil is energized, and the magnet is acted upon by the magnetic force of the iron core to make the rotor fit to the side of the UAV body through the rotor fixing frame. After the UAV is launched, the coil is de-energized to allow the rotor to spread out.

3. The UAV launching device according to claim 1, characterized in that: The launch chamber is cylindrical, the launch hole penetrates the launch chamber along the axial direction of the launch chamber, and a plurality of the launch holes are arranged at intervals around the axis of the launch chamber, and the launch chamber has a central axis hole that penetrates the launch chamber along its axis; The launch chamber assembly also includes a central axis, a launch chamber shell and a launch chamber rear cover; Wherein, the central axis is arranged in the central axis hole, the launch chamber is sleeved in the launch chamber shell, the launch chamber is rotatable around the central axis relative to the launch chamber shell, 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 arranged at the second end of the launch chamber shell through a second rotating axis, 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 arranged on the side of the launch chamber rear cover away from the launch chamber shell, and the driving unit is connected to the launch chamber through a connecting piece arranged in the second through hole to drive the launch chamber to rotate along its axis.

4. The UAV launch device according to claim 3, characterized in that: The connecting member comprises a groove wheel, a dial and a connecting rod, wherein the groove wheel is fixed at one end of the launch chamber facing the rear cover of the launch chamber, and the groove wheel is directly opposite to the central axis, the side surface of the dial is in contact with the side surface of the groove wheel, and the dial is fixed to the first end of the connecting rod, the connecting rod is penetrated in the second through hole, and the second end of the connecting rod is connected to the driving unit; The driving unit comprises a motor, a first gear, a second gear and a gear chain, the motor shaft of the motor is transmission-connected to the first gear, the first gear is transmission-connected to the second gear through the gear chain, and the second end of the connecting rod is connected to the second gear; Among them, 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 toggles the groove wheel, and then the launching chamber rotates to switch the launching hole 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 a special-shaped groove, and the groove wheel and the dial are both arranged in the special-shaped groove.

6. The UAV launch device according to claim 4, characterized in that: The driving unit further comprises: a spiral slide, a firing spring and a fixed baffle, wherein the fixed baffle, the spiral slide, the firing spring and the hammer are located on a side of the first gear away from the motor, and the fixed baffle, the firing spring and the hammer are sequentially connected and arranged in a direction away from the first gear, the spiral slide is located on the inner circle of the hammer and on the inner circle of the firing spring, a 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 toward the fixed baffle through the pin on the inner ring of the hammer, and the firing spring is compressed until the hammer reaches the power storage position, and the pin is disconnected from the thread of the spiral slide, completing the power storage operation; After the trigger is pulled, the latch releases the hammer, the launching spring pushes the hammer, and the hammer pushes the drone in the launching hole to be launched.

7. The UAV launch device according to claim 6, characterized in that: The drive unit further comprises a power housing, wherein the motor, the first gear, a portion of the gear chain, the fixed baffle, the spiral slide, the firing spring and the hammer are all arranged in the power housing.

8. The UAV launching device according to claim 7, characterized in that: The trigger assembly also includes a trigger housing arranged on the side of the power housing, the latch and the second gear are arranged in the trigger housing, the gear chain extends from the power housing to the trigger housing, and the trigger extends from the trigger housing through 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 is the maximum deformation of the launching spring, f n The unit is mm; F ′ is the stiffness coefficient of the launching spring, F ′ The unit is N / mm; m w is the mass of the UAV, m w The unit is kg; m j is the mass of the hammer, m j The unit is kg; V w is the launch speed of the UAV, V w The unit of H is m / s; s is the vertical height of the handheld launch structure, H s The unit is mm.

10. The UAV launching device according to claim 3, characterized in that: The trigger assembly also includes a latch spring and a trigger inner shell. The trigger inner shell is arranged on a side of the launch chamber rear cover away from the launch chamber, and when the hammer is in the power storage position, the trigger inner shell is arranged below the hammer. One end of the latch extends from a side of the trigger inner shell away from the hammer to the front end of the hammer, and the other end of the latch is arranged on the trigger inner shell through the latch spring.

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