A wing-mounted folding-wing UAV cluster launching mechanism

Abstract

The present invention discloses a wing-mounted folding-wing UAV cluster launch mechanism, belonging to the field of UAV launch. The mechanism comprises a transport carrier, a launch tube, an elastic member, and a locking mechanism. The launch tube is detachably connected to the transport carrier. A launch chamber with an open lower end for loading UAVs is provided within the launch tube. An opening is provided on the side wall of the launch tube, and the elastic member is installed in the launch chamber. The locking mechanism includes a locking member that is rotatably arranged relative to the launch tube. When the launch tube is loaded with UAVs, the locking member is in a locked position, extends through the opening into the launch chamber, abuts against the UAVs to prevent them from escaping from the launch chamber, and the UAVs squeeze the elastic member. When the launch tube launches a UAV, the locking member is in an unlocked position, moves out of the launch chamber, and the elastic member ejects the UAVs from the launch chamber. In the present invention, the UAV launch operation is simple, flexible, and convenient to use, and a large number of UAVs can be launched simultaneously.

Description

Technical Field

[0001] The present invention relates to the technical field of UAV launch, and in particular to a wing-mounted folding-wing UAV cluster launch mechanism. Background Art

[0002] With the rapid development of networking and data link technology, folding-wing drones (rovers) have achieved information sharing and networked collaborative operations, enabling them to simultaneously engage multiple targets across a large area, fully realizing their combat effectiveness. The US military previously proposed deploying large numbers of folding-wing drones (rovers) over a specific area. These drones would automatically form a combat network, thereby achieving long-term, sustained control of a specific area. The emergence of folding-wing drones allows troops to pre-position weapons in the airspace near potential targets, making them a useful reconnaissance or indirect launch weapon. Currently, there are three common methods for launching folding-wing drones: using a grenade launcher, hand-throwing, and launching from fixed or mobile platforms, such as main battle tanks and infantry fighting vehicles. Due to the limited range of these folding-wing drones, these methods require vehicles to transport them to a certain range within the target area before they can be launched. This carries the risk of personnel exposure and casualties. Therefore, launching folding-wing drones from a swarm of mother aircraft has become a more suitable option in this new era.

[0003] A related art discloses an air-based launch device for unmanned aerial vehicles (UAVs). The device includes a slide rail, a launch bracket, and a launcher. Each launcher has multiple launch tubes, and the launch tubes include an ejection device. The ejection device includes a single-double ear structure, a spring device, and a steel cable, which can accommodate multiple swarm UAVs. Before launching, the UAV is first placed in the launch tube, and then the launcher is released through the launch bracket. During launch, the steel cable of the locked spring device is pulled out, the spring device is unlocked, and the thrust generated by the spring device in the ejection device is used to push the UAV out of the launch tube without damaging the UAV structure and equipment, thereby completing the launch of the UAV. In the launch method of this UAV launch device, it is necessary to pull out the steel cable of the locked spring device and unlock the spring device. It is difficult to pull out the steel cable horizontally, which increases the instability of the UAV launch. Summary of the Invention

[0004] The present invention aims to address at least one of the technical problems existing in the prior art. To this end, the present invention proposes a wing-mounted, folding-wing drone cluster launch mechanism. The drones can be launched simply by switching a locking member from the locked position to the unlocked position. The drone launch operation is simple and difficult to detect. The device is inexpensive, requires no complex preparation, and is flexible and convenient to use, allowing for the simultaneous launch of large numbers of drones.

[0005] A wing-mounted folding-wing UAV cluster launch mechanism according to an embodiment of the present invention includes:

[0006] transport carrier;

[0007] a launch tube, detachably connected to the transport carrier, wherein a launch cavity with an open lower end for loading the drone is provided in the launch tube, and an opening communicating with the launch cavity is provided on a side wall of the launch tube;

[0008] an elastic member, installed in the firing chamber;

[0009] The locking mechanism includes a locking member, the locking member being rotatably arranged relative to the launching tube, the locking member having a locked position and an unlocked position, wherein when the locking member is in the locked position, the locking member extends through the opening into the launching chamber; when the locking member is in the unlocked position, the locking member is removed from the launching chamber;

[0010] When the launch tube is loaded with a drone, the locking piece is in a locked position, the locking piece abuts against the drone to restrict the drone from escaping from the launch chamber, and the drone squeezes the elastic piece; when the launch tube launches the drone, the locking piece is in an unlocked position, and the elastic piece pops the drone out of the launch chamber.

[0011] A wing-mounted folding-wing UAV cluster launching mechanism according to an embodiment of the present invention has at least the following beneficial effects:

[0012] The drone is loaded into the launch chamber of the launch tube with the locking member in the locked position, securing it within the chamber. The launch tube is then mounted on a transport carrier, enabling cluster storage and launch of drones. To launch a drone, the locking member switches to the unlocked position, and an elastic member ejects the drone from the chamber. This makes launching a drone simple and difficult to detect. The device is inexpensive, requires no complex preparation, and is flexible and convenient, allowing for the simultaneous launch of large numbers of drones.

[0013] According to some embodiments of the present invention, the locking mechanism further includes a drive assembly, the drive assembly having a drive shaft, the drive assembly being mounted on the launching tube, the drive shaft being connected to the locking member, the drive assembly having a free state and a working state, and when the drive assembly is in the free state, the locking member is operable to rotate around the drive shaft to switch the locking member between the locked position and the unlocked position; when the drive assembly is in the working state, the drive assembly drives the locking member to rotate to switch the locking member between the locked position and the unlocked position.

[0014] According to some embodiments of the present invention, the locking mechanism further comprises a torsion spring, which is sleeved on the drive shaft and connects the locking member and the launching tube. When the drive assembly is in a free state, the torsion spring limits the locking member to a locked position.

[0015] According to some embodiments of the present invention, a thrust piece is further included, which is slidably connected in the launch tube and connected to the elastic piece. When the launch tube is loaded with a drone, the drone abuts against the thrust piece, and the thrust piece squeezes the elastic piece. When the launch tube launches the drone, the elastic piece ejects the drone from the launch chamber through the thrust piece.

[0016] According to some embodiments of the present invention, it further includes a fixing frame and a carrier bracket, wherein the carrier bracket is installed on the transport carrier, the carrier bracket is detachably connected to the fixing frame, a plurality of the launching tubes are provided, the fixing frame is connected to the plurality of the launching tubes, and the open ends of the plurality of the launching tubes face downward.

[0017] According to some embodiments of the present invention, the fixing frame includes a connecting plate and a reinforcement plate, the upper ends of the plurality of launching tubes are hinged to the connecting plate, the reinforcement plate is connected to the lower ends of the plurality of launching tubes, and the reinforcement plate is provided with a plurality of first connecting holes and a plurality of second connecting holes, one launching tube corresponds to one first connecting hole and one second connecting hole, a screw passes through the first connecting hole to connect to the launching tube, and a screw passes through the second connecting hole to connect to the launching tube.

[0018] According to some embodiments of the present invention, the launch tubes are arranged in pairs to form a launch tube assembly, and a plurality of launch tube assemblies are provided. A first mounting member, a second mounting member and a third mounting member are connected to the launch tube assembly, the first mounting member is connected to the upper end of the launch tube assembly, the second mounting member is connected to the middle part of the launch tube assembly, the third mounting member is connected to the lower end of the launch tube assembly, the first mounting member is hinged to the connecting plate, the locking mechanism is installed on the second mounting member, and the third mounting member is connected to the reinforcement plate.

[0019] According to some embodiments of the present invention, the fixing frame is provided with a plug-in protrusion and a first connecting protrusion, the first connecting protrusion is provided with a third connecting hole for a fastener to pass through, the carrier hanger is provided with a second connecting protrusion, the second connecting protrusion is provided with a fourth connecting hole for the fastener to pass through, and the carrier hanger is provided with a slot for the plug-in protrusion to extend into and for limiting the axial rotation of the plug-in protrusion around the third connecting hole.

[0020] According to some embodiments of the present invention, a limiting pad is provided on the inner wall of the slot, and when the plug-in protrusion is inserted into the slot, the limiting pad abuts against the plug-in protrusion;

[0021] The fastener includes a latch and an R-shaped pin. The latch is provided with a fastening hole. The latch is passed through the third connecting hole and the fourth connecting hole, and the R-shaped pin is passed through the fastening hole.

[0022] According to some embodiments of the present invention, a fairing is further included, which is detachably mounted on the fixing frame. A receiving cavity is provided in the fairing, and a launch port connected to the receiving cavity is provided at the lower end of the fairing. The launch tube is installed in the receiving cavity, and the open end of the launch tube faces the launch port. The fairing can be detachably arranged.

[0023] Additional aspects and advantages of the present invention will be set forth in part in the description which follows. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The present invention will be further described below with reference to the accompanying drawings and embodiments, in which:

[0025] Figure 1 This is a structural diagram of a wing-mounted folding-wing UAV cluster launch mechanism according to an embodiment of the present invention;

[0026] Figure 2 A cross-sectional view of a launch tube of a wing-mounted folding-wing UAV cluster launch mechanism according to an embodiment of the present invention;

[0027] Figure 3 This is a structural diagram of the launch tube, locking mechanism, and drones of a wing-mounted folding-wing drone cluster launch mechanism according to an embodiment of the present invention;

[0028] Figure 4 for Figure 3 A magnified view of middle A;

[0029] Figure 5 This is a schematic diagram of the structure of the launch tube, locking mechanism, fixing frame and carrier bracket of the wing-mounted folding-wing UAV cluster launch mechanism according to an embodiment of the present invention;

[0030] Figure 6 for Figure 5 Enlarged view of middle B;

[0031] Figure 7 This is a schematic structural diagram of a carrier rack for a wing-mounted folding-wing UAV cluster launch mechanism according to an embodiment of the present invention;

[0032] Figure 8 This is a structural diagram of the connecting plate of the wing-mounted folding-wing UAV cluster launch mechanism according to an embodiment of the present invention;

[0033] Figure 9 This is a schematic structural diagram of a reinforcement plate for a wing-mounted folding-wing UAV cluster launch mechanism according to an embodiment of the present invention;

[0034] Figure 10 This is a schematic structural diagram of a fairing for a wing-mounted folding-wing UAV cluster launch mechanism according to an embodiment of the present invention;

[0035] Figure 11 This is a structural diagram of a folding rotor UAV;

[0036] Figure 12 This is a structural diagram of a foldable fixed-wing UAV.

[0037] Figure Number:

[0038] 100. Transport carrier;

[0039] 200, launching tube; 210, launching chamber; 220, opening; 230, elastic member; 240, thrust member; 250, first mounting member; 260, second mounting member; 270, third mounting member;

[0040] 300, locking mechanism; 310, locking member; 320, driving assembly; 321, driving shaft; 330, torsion spring;

[0041] 400, fixing frame; 410, connecting plate; 411, plug-in protrusion; 412, first connecting protrusion; 4121, third connecting hole; 413, fastener; 4131, latch; 4132, R-shaped pin; 420, reinforcing plate; 421, first connecting hole; 422, second connecting hole;

[0042] 500, carrier rack; 510, second connecting protrusion; 511, fourth connecting hole; 520, slot; 521, limiting pad;

[0043] 600, fairing; 610, launch port;

[0044] 700, drone; 710, notch slot. DETAILED DESCRIPTION

[0045] The following describes embodiments of the present invention in detail. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended only to explain the present invention and are not to be construed as limiting the present invention.

[0046] In the description of the present 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", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present 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 limiting the present invention. In addition, features defined as "first" or "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0047] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0048] See also Figure 1 、 Figure 2 and Figure 3 According to an embodiment of the present invention, a wing-mounted folding-wing UAV cluster launch mechanism includes a transport carrier 100, a launch tube 200, an elastic member 230, and a locking mechanism 300. The launch tube 200 is detachably connected to the transport carrier 100. A launch chamber 210 is provided in the launch tube 200. The lower end of the launch chamber 210 is open and is used to load the UAV 700. Figure 4 , an opening 220 is provided on the side wall of the launch tube 200, and the opening 220 is connected to the launch chamber 210, and the elastic member 230 is installed in the launch chamber 210. The locking mechanism 300 includes a locking member 310, and the locking member 310 is rotatable relative to the launch tube 200. The locking member 310 has a locking position and an unlocking position. When the locking member 310 is in the locking position, the locking member 310 passes through the opening 220 and extends into the launch chamber 210; when the locking member 310 is in the unlocking position, the locking member 310 moves out of the launch chamber 210. When the launch tube 200 is loaded with the drone 700, the locking member 310 is in the locking position, and the locking member 310 abuts against the drone 700 (see Figure 11 , a folding rotor drone 700, having a notch groove 710, the groove wall of the notch groove 710 can be defined by a locking member 310; see Figure 12A foldable fixed-wing UAV 700 has a notch 710, the groove wall of the notch 710 can be limited by a locking piece 310), thereby restricting the UAV 700 from escaping from the launch chamber 210, and the UAV 700 squeezes the elastic piece 230; when the launch tube 200 launches the UAV 700, the locking piece 310 is in the unlocked position, and the elastic piece 230 pops the UAV 700 out of the launch chamber 210.

[0049] The transport carrier 100 is a mother aircraft, which can be a large UAV. Using the mother aircraft to mount the small folding-wing UAV 700 can effectively solve the problems of the folding-wing UAV 700's short range and limited number of launches per time, meeting the needs of the UAV 700 for long-distance cluster coordinated combat, reconnaissance or attacking ground targets, thereby achieving long-term control of a specific area. The mother aircraft is used to carry the launch mechanism and transport the folding-wing UAV 700 it carries to the target mission area in the pre-set airspace for launch; the launch tube 200 is used for loading, storing energy and launching the folding-wing UAV 700; after the folding-wing UAV 700 is launched from the launch tube 200 under the wing of the mother aircraft, the rotor quickly recovers from the folded state to the flight state. The folding-wing UAV 700 uses the mother aircraft as a communication relay station in the air, interacting with the ground station through line-of-sight communication, satellite communication, etc., thereby realizing the folding-wing UAV 700 cluster formation combat.

[0050] The wing-mounted folding-wing UAV cluster launching mechanism can meet the needs of launching folding rotor UAV 700 and folding fixed-wing UAV 700.

[0051] The drone 700 is loaded into the launch chamber 210 of the launch tube 200, with the locking member 310 in the locked position. The locking member 310 secures the drone 700 within the launch chamber 210. The launch tube 200 is mounted on the transport carrier 100, enabling cluster storage and launch of drones 700. To launch a drone 700, the locking member 310 switches to the unlocked position, and the elastic member 230 ejects the drone 700 from the launch chamber 210. This simple launch operation makes detection difficult. The launch tube 200 is inexpensive, requires no complex preparation, and is flexible and convenient, allowing for the simultaneous launch of large numbers of drones 700.

[0052] In some embodiments, see Figure 1 、 Figure 3 and Figure 4The locking mechanism 300 further includes a drive assembly 320 having a drive shaft 321. The drive assembly 320 is mounted on the launch tube 200, and the drive shaft 321 is connected to the locking member 310. The drive assembly 320 has a free state and an operating state. When the drive assembly 320 is in the free state, the locking member 310 is operable to rotate about the drive shaft 321, thereby switching the locking member 310 between a locked position and an unlocked position. When the drive assembly 320 is in the operating state, the drive assembly 320 drives the locking member 310 to rotate, thereby switching the locking member 310 between a locked position and an unlocked position.

[0053] The drive assembly 320 can be a servo or a motor. When the servo is powered, it is in an operating state, driving the locking member 310 to rotate. When the servo is powered off, it is in a free state, allowing the drive shaft 321 to rotate freely. The locking member 310 can be manually moved to switch between a locked and unlocked position.

[0054] In some embodiments, see Figure 1 、 Figure 3 and Figure 4 The locking mechanism 300 also includes a torsion spring 330, which is sleeved on the drive shaft 321 and connects the locking member 310 to the launch tube 200. When the drive assembly 320 is in a free state, the torsion spring 330 confines the locking member 310 to the locked position. By using the servo, torsion spring 330, and other parts in combination, when the rotary-wing drone 700 is installed, after one end surface of the rotary-wing drone 700 (the wall of the notch 710) passes over the locking member 310, the locking member 310 automatically rebounds to its original position (the locked position) under the force of the torsion spring 330. When the rotary-wing drone 700 is released, it is automatically locked in the tube. When the rotary-wing drone 700 is unlocked, the servo only needs to overcome the torsion of the torsion spring 330 and the friction between the locking member 310 and the end surface of the drone 700 (the wall of the notch 710), saving effort during unlocking, and a low-torque servo can be used.

[0055] In some embodiments, see Figure 1 and Figure 2A thrust piece 240 is also provided in the launch chamber 210. The thrust piece 240 is slidably connected in the launch tube 200 and is connected to the elastic piece 230. When the launch tube 200 is loaded with the drone 700, the drone 700 abuts against the thrust piece 240, and the thrust piece 240 squeezes the elastic piece 230. When the launch tube 200 launches the drone 700, the elastic piece 230 ejects the drone 700 from the launch chamber 210 through the thrust piece 240. The elastic piece 230 can be a spring, and a positioning groove is provided on the thrust piece 240, and one end of the spring extends into the positioning groove. The provision of the thrust piece 240 can prevent the spring from directly contacting the drone 700 and scratching the drone 700. It can also increase the force-bearing area of ​​the drone 700 and ensure that the tail end of the drone 700 is evenly stressed.

[0056] In some embodiments, see Figure 1 and Figure 5 The wing-mounted folding-wing drone cluster launch mechanism also includes a mounting bracket 400 and a carrier bracket 500. The carrier bracket 500 is mounted on the transport vehicle 100, mounted under the wing of the transport vehicle 100. The carrier bracket 500 is detachably connected to the mounting bracket 400. Multiple launch tubes 200 are provided, and the mounting bracket 400 connects to multiple launch tubes 200, with the open ends of the multiple launch tubes 200 facing downward. The mounting bracket 400 and carrier bracket 500 enable the detachable attachment of multiple launch tubes 200 to the transport vehicle 100.

[0057] In some embodiments, see Figure 5 、 Figure 8 and Figure 9 The mounting frame 400 includes a connecting plate 410 and a reinforcement plate 420. The upper ends of the multiple launch tubes 200 are hingedly connected to the connecting plate 410, while the reinforcement plate 420 connects to the lower ends of the multiple launch tubes 200. The reinforcement plate 420 is provided with multiple first connection holes 421 and multiple second connection holes 422, with one first connection hole 421 and one second connection hole 422 corresponding to each launch tube 200. Screws pass through the first connection holes 421 to connect to the launch tube 200, and screws pass through the second connection holes 422 to connect to the launch tube 200. The lower end of the launch tube 200 is connected to the reinforcement plate 420 via two screws, preventing the launch tube 200 from rotating around the upper end relative to the connecting plate 410. The multiple launch tubes 200 are hingedly connected to the connecting plate 410 at their upper ends and connected to the reinforcement plate 420 at their lower ends via two screws, allowing the multiple launch tubes 200 to be assembled into a single, stable structure.

[0058] In some embodiments, see Figure 2 and Figure 5The launch tubes 200 are arranged in pairs to form a launch tube assembly. Multiple launch tube assemblies are provided, and a first mounting member 250, a second mounting member 260, and a third mounting member 270 are connected to the launch tube assembly. The first mounting member 250 is connected to the upper end of the launch tube assembly, the second mounting member 260 is connected to the middle of the launch tube assembly, and the third mounting member 270 is connected to the lower end of the launch tube assembly. The first mounting member 250 is hingedly connected to the connecting plate 410. The locking mechanism 300 is mounted on the second mounting member 260, and the third mounting member 270 is connected to the reinforcement plate 420. The second mounting member 260 has two first mounting holes, through which the two launch tubes 200 are respectively inserted. The third mounting member 270 has two second mounting holes, through which the two launch tubes 200 are respectively inserted. The two launch tubes 200 are installed together through the first mounting member 250, the second mounting member 260 and the third mounting member 270. The locking mechanisms 300 on the two launch tubes 200 are located on both sides, which can improve space utilization and avoid interference when multiple drones 700 are combined.

[0059] In some embodiments, see Figure 5 、 Figure 6 and Figure 7 The fixing frame 400 is provided with an inserting protrusion 411 and a first connecting protrusion 412. The first connecting protrusion 412 is provided with a third connecting hole 4121 for the fastener 413 to pass through. The carrier hanger 500 is provided with a second connecting protrusion 510. The second connecting protrusion 510 is provided with a fourth connecting hole 511 for the fastener 413 to pass through. The carrier hanger 500 is provided with a slot 520 for the inserting protrusion 411 to extend into and for limiting the axial rotation of the inserting protrusion 411 about the third connecting hole 4121. A limiting pad 521 is provided on the inner wall of the slot 520. When the inserting protrusion 411 is inserted into the slot 520, the limiting pad 521 abuts against the inserting protrusion 411. The fastener 413 includes a latch pin 4131 and an R-shaped pin 4132 . A fastening hole is provided on the latch pin 4131 . The latch pin 4131 passes through the third connection hole 4121 and the fourth connection hole 511 , and the R-shaped pin 4132 passes through the fastening hole.

[0060] The right side of the connecting plate 410 is connected to the carrier bracket 500 through a cylindrical pin and an R-shaped pin 4132, and the left side is inserted into the slot 520 through the plug-in protrusion 411, and the connecting plate 410 is tightly fixed under the pressure of the limit pad 521, so that the connecting plate 410 and the carrier bracket 500 can be quickly disassembled and assembled, and the processing accuracy requirements of the parts are relatively low.

[0061] In some embodiments, see Figure 1 and Figure 10The wing-mounted folding-wing UAV cluster launch mechanism also includes a fairing 600, which is detachably mounted on the fixing frame 400. A receiving cavity is provided in the fairing 600. A launching port 610 is provided at the lower end of the fairing 600. The launching port 610 is connected to the receiving cavity. The launching tube 200 is installed in the receiving cavity. The open end of the launching tube 200 faces the launching port 610. The fairing 600 is detachable. The setting of the fairing 600 can reduce the wind resistance of the mother aircraft during flight, ensure the flight time of the mother aircraft, and reduce the difficulty of flight control. The detachable fairing 600 can also reduce the difficulty of installation and is convenient for disassembly.

[0062] The launch process of the wing-mounted folding-wing UAV cluster launch mechanism:

[0063] 1. Install multiple launch tubes 200 on a fixing frame 400, and install the fixing frame 400 under the wing of the mother aircraft (transport carrier 100).

[0064] 2. Manually change the Folding Wing Drone 700 from the flying state to the folded state.

[0065] 3. Manually move the locking member 310 to move it out of the launch chamber 210 . When the locking member 310 is in the unlocked position, insert the folded rotor drone 700 into the launch chamber 210 .

[0066] 4. After the rotary-wing drone 700 moves to the designated position, the locking member 310 is released. Under the action of the torsion spring 330, the locking member 310 extends into the launch chamber 210 and abuts against the wall of the notch 710 of the drone 700. At this point, the rear end of the rotary-wing drone 700 is thrust by the thrust member 240, and a portion of its midsection (the wall of the notch 710) abuts against the end face of the locking member 310, thus locking the rotary-wing drone 700 in the launch tube 200.

[0067] 5. Following the process of steps 2, 3, and 4 above, insert the remaining folding-wing drones 700 into each launch tube 200, lock them, and then install the fairing 600;

[0068] 6. After the mother aircraft takes off from the airport and flies to the pre-arrival airspace, it enters a level flight state and prepares to launch the folding-wing UAV 700. First, the ground station sends an unlocking command to the mother aircraft's autopilot, and then a servo drives the locking member 310 to rotate 90°. At this time, the middle section of the rotor UAV 700 (the groove wall of the notch 710) is no longer restricted and is in a free state. Under the action of gravity and the thrust of the thrust member 240, the rotor UAV 700 moves out of the launch tube 200. After leaving the tube, its rotor automatically unfolds and it enters the flight state under the intervention of the autopilot program. Similarly, after launching the remaining folding-wing UAVs 700, the mother aircraft hovers in the pre-arrival airspace as a signal relay station. After the rotor UAV 700 completes its mission (reconnaissance and attack targets), the mother aircraft returns.

[0069] Throughout this specification, reference to terms such as "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples" means that a specific feature, structure, material, or characteristic described in conjunction with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, illustrative uses of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0070] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to the embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the claims and their equivalents.

Claims

1. A wing-mounted folding-wing UAV cluster launch mechanism, characterized in that: include: transport carrier; a launch tube, detachably connected to the transport carrier, wherein a launch cavity with an open lower end for loading the drone is provided in the launch tube, and an opening communicating with the launch cavity is provided on a side wall of the launch tube; an elastic member, installed in the firing chamber; The locking mechanism includes a locking member, the locking member being rotatably arranged relative to the launching tube, the locking member having a locked position and an unlocked position, wherein when the locking member is in the locked position, the locking member extends through the opening into the launching chamber; when the locking member is in the unlocked position, the locking member is removed from the launching chamber; When the launch tube is loaded with a drone, the locking member is in a locked position, abutting against the drone to prevent the drone from escaping from the launch chamber, and the drone squeezes the elastic member; when the launch tube is launching the drone, the locking member is in an unlocked position, and the elastic member ejects the drone from the launch chamber; The locking mechanism further includes a drive assembly, wherein the drive assembly has a drive shaft, the drive assembly is mounted on the launching tube, the drive shaft is connected to the locking member, and the drive assembly has a free state and a working state. When the drive assembly is in the free state, the locking member is operably rotated about the drive shaft to switch the locking member between the locked position and the unlocked position; when the drive assembly is in the working state, the drive assembly drives the locking member to rotate to switch the locking member between the locked position and the unlocked position. The invention also includes a fixing frame and a carrier rack, wherein the carrier rack is mounted on the transport carrier, the carrier rack is detachably connected to the fixing frame, a plurality of the launch tubes are provided, the fixing frame is connected to the plurality of the launch tubes, and the open ends of the plurality of the launch tubes face downwards; The fixing frame includes a connecting plate and a reinforcing plate, the upper ends of the plurality of launching tubes are hinged to the connecting plate, the reinforcing plate is connected to the lower ends of the plurality of launching tubes, the reinforcing plate is provided with a plurality of first connecting holes and a plurality of second connecting holes, one launching tube corresponds to one first connecting hole and one second connecting hole, a screw is passed through the first connecting hole to connect to the launching tube, and a screw is passed through the second connecting hole to connect to the launching tube; The fixing frame is provided with a plug-in protrusion and a first connecting protrusion, the first connecting protrusion is provided with a third connecting hole for a fastener to pass through, the carrier hanger is provided with a second connecting protrusion, the second connecting protrusion is provided with a fourth connecting hole for the fastener to pass through, and the carrier hanger is provided with a slot for the plug-in protrusion to extend into and for limiting the axial rotation of the plug-in protrusion around the third connecting hole; A limiting pad is provided on the inner wall of the slot, and when the plug-in protrusion is inserted into the slot, the limiting pad abuts against the plug-in protrusion; The fastener includes a latch and an R-shaped pin. The latch is provided with a fastening hole. The latch is passed through the third connecting hole and the fourth connecting hole, and the R-shaped pin is passed through the fastening hole.

2. The wing-mounted folding-wing UAV cluster launch mechanism according to claim 1, characterized in that: The locking mechanism further comprises a torsion spring, which is sleeved on the drive shaft and connects the locking member and the launching tube. When the drive assembly is in a free state, the torsion spring limits the locking member to a locked position.

3. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 1, characterized in that: It also includes a thrust piece, which is slidably connected in the launching tube and connected to the elastic piece. When the launching tube is loaded with a drone, the drone abuts against the thrust piece and the thrust piece squeezes the elastic piece. When the launching tube launches the drone, the elastic piece ejects the drone from the launching chamber through the thrust piece.

4. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 1, characterized in that: The launching tubes are arranged in pairs to form a launching tube assembly, and there are multiple launching tube assemblies. A first mounting member, a second mounting member and a third mounting member are connected to the launching tube assembly. The first mounting member is connected to the upper end of the launching tube assembly, the second mounting member is connected to the middle part of the launching tube assembly, and the third mounting member is connected to the lower end of the launching tube assembly. The first mounting member is hinged to the connecting plate, the locking mechanism is installed on the second mounting member, and the third mounting member is connected to the reinforcement plate.

5. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 1, characterized in that: It also includes a fairing, which is detachably mounted on the fixing frame. A receiving cavity is provided in the fairing, and a launching port connected to the receiving cavity is provided at the lower end of the fairing. The launching tube is installed in the receiving cavity, and the open end of the launching tube faces the launching port. The fairing can be detachably mounted.

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