Wing-mounted folding wing unmanned aerial vehicle cluster launching mechanism

Abstract

The invention discloses a wing-mounted folding wing unmanned aerial vehicle cluster launching mechanism, and belongs to the field of unmanned aerial vehicle launching, the wing-mounted folding wing unmanned aerial vehicle cluster launching mechanism comprises a transportation carrier, a launching cylinder, an elastic piece and a locking mechanism, the launching cylinder is detachably connected to the transportation carrier, and a launching cavity with an open lower end and used for loading an unmanned aerial vehicle is formed in the launching cylinder; an opening is formed in the side wall of the launching cylinder, the elastic piece is installed in the launching cavity, the locking mechanism comprises a locking piece, the locking piece is rotatably arranged relative to the launching cylinder, and when the launching cylinder loads the unmanned aerial vehicle, the locking piece is located at the locking position, penetrates through the opening and extends into the launching cavity, and the locking piece abuts against the unmanned aerial vehicle to limit the unmanned aerial vehicle from disengaging from the launching cavity; the unmanned aerial vehicle extrudes the elastic piece, when the launching cylinder launches the unmanned aerial vehicle, the locking piece is located at the unlocking position, the locking piece is moved out of the launching cavity, and the elastic piece pops the unmanned aerial vehicle out of the launching cavity. The unmanned aerial vehicle launching operation is simple, use is flexible and convenient, and a large number of unmanned aerial vehicles can be launched at the same time.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle (UAV) launching, and in particular to a wing-mounted folding-wing UAV cluster launching mechanism. Background Art

[0002] With the rapid development of networking and data link technology, folding-wing UAVs (patrol drones) have achieved information sharing and networked collaborative operations with each other, and can deal with multiple targets distributed in a large area at the same time, giving full play to the combat effectiveness of UAVs. In the early years, the US military proposed to deploy a large number of folding-wing UAVs (patrol drones) over specific areas. They can automatically form a combat network, thereby achieving long-term and lasting control over specific areas. The British Ministry of Defense believes that the emergence of folding-wing UAVs can enable troops to deploy weapons in advance to airspace close to potential target areas, becoming a reconnaissance or indirect launch weapon. At present, there are three common ways to launch folding-wing UAVs. One is to launch with a grenade launcher, the second is to throw it by hand, and the third is to launch it from a fixed or mobile platform, such as a main battle tank and an infantry fighting vehicle. Due to the range problem of folding-wing UAVs, these three launch methods require vehicles to be transported to a certain range of the target area before they can be launched. This is accompanied by the risk of personnel exposure and casualties. Therefore, using a mother aircraft cluster to launch folding-wing UAVs has become a better choice in the new era.

[0003] A related art discloses an air-based launch device for a UAV. The device includes a slide rail, a launch bracket, and a launcher. Each launcher has multiple launch tubes, and the launch tube includes an ejection device. The ejection device includes a single-double ear piece structure, a spring device, and a steel cable, which can hold 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 locking 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 structure and equipment of the UAV, 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 locking 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 solve at least one of the technical problems existing in the prior art. To this end, the present invention proposes a wing-mounted folding-wing UAV cluster launch mechanism, which can launch the UAV by operating the locking member to switch from the locking position to the unlocking position. The launch operation of the UAV is simple and not easy to be detected. The cost is low, and no complicated preparation work is required. It is flexible and convenient to use, and a large number of UAVs can be launched at the same time.

[0005] A wing-mounted folding-wing UAV cluster launching 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 chamber with an open lower end for loading the drone is provided in the launch tube, and an opening communicating with the launch chamber is provided on a side wall of the launch tube;

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

[0009] The locking mechanism comprises a locking member, the locking member is rotatably arranged relative to the launching tube, the locking member has a locking position and an unlocking position, when the locking member is in the locking position, the locking member passes through the opening and extends into the launching chamber; when the locking member is in the unlocking position, the locking member moves out of the launching chamber;

[0010] When the launch tube is loaded with a drone, the locking piece is located in a locking 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 located in an unlocking 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 UAV is loaded into the launch chamber of the launch tube, and the locking piece is in the locking position. The locking piece locks the UAV in the launch chamber. The launch tube is installed on the transport carrier, which can realize the cluster storage and launch of UAVs. When the UAV is launched, the locking piece switches to the unlocking position, and the elastic piece ejects the UAV from the launch chamber. The launch operation of the UAV is simple and not easy to be detected. It is low-cost and does not require complicated preparation work. It is flexible and convenient to use, and a large number of UAVs can be launched at the same time.

[0013] According to some embodiments of the present invention, the locking mechanism also includes a driving assembly, the driving assembly having a driving shaft, the driving assembly being mounted on the launching tube, the driving shaft being connected to the locking piece, the driving assembly having a free state and a working state, when the driving assembly is in the free state, the locking piece can be operably rotated around the driving shaft to switch the locking piece between the locked position and the unlocked position; when the driving assembly is in the working state, the driving assembly drives the locking piece to rotate to switch the locking piece 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, wherein the torsion spring is sleeved on the driving shaft, the torsion spring connects the locking member and the launching tube, and when the driving 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, 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.

[0016] According to some embodiments of the present invention, it also 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 downwards.

[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, a plurality of first connecting holes and a plurality of second connecting holes are provided on the reinforcement plate, 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 launching tubes are arranged in pairs to form a launching tube assembly, and a plurality of launching tube assemblies are provided. 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, 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.

[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 comprises 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, it also includes a fairing, which is detachably mounted on the fixing frame, a receiving cavity is provided inside the fairing, 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, the open end of the launching tube faces the launching port, and the fairing can be detachably arranged.

[0023] Additional aspects and advantages of the 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, wherein:

[0025] Figure 1 This is a structural schematic diagram of a wing-mounted folding-wing UAV cluster launching 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 It is a structural schematic diagram of a launching tube, a locking mechanism and UAVs of a wing-mounted folding-wing UAV cluster launching mechanism according to an embodiment of the present invention;

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

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

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

[0033] Fig. 9 A schematic diagram of the structure of a reinforcement plate of a wing-mounted folding-wing UAV cluster launching mechanism according to an embodiment of the present invention;

[0034] Fig.10 A schematic diagram of the structure of a fairing of a wing-mounted folding-wing UAV cluster launch mechanism according to an embodiment of the present invention;

[0035] Fig.11 It is a structural schematic diagram of a folding rotor UAV;

[0036] Fig.12 This is a schematic diagram of the structure 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, plugging protrusion; 412, first connecting protrusion; 4121, third connecting hole; 413, fastener; 4131, latch; 4132, R-type pin; 420, reinforcing plate; 421, first connecting hole; 422, second connecting hole;

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

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

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

[0045] Embodiments of the present invention are described in detail below, examples of which 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 only used to explain the present invention, and cannot be understood 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 positions or positional relationships based on the positions 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 a limitation on the present invention. In addition, features defined as "first" and "second" may explicitly or implicitly include one or more of the 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 clearly specified and limited, the terms "installed", "connected", and "connected" 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 present invention can be understood according to 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, and a launch chamber 210 is provided in the launch tube 200. The lower end of the launch chamber 210 is open, and the launch chamber 210 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 Fig.11 , a foldable 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 Fig.12A foldable fixed-wing UAV 700 has a notch groove 710, the groove wall of the notch groove 710 can be limited by a locking piece 310), thereby limiting 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 unlocking 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 a small folding-wing UAV 700 can effectively solve the problems of the short range of the folding-wing UAV 700 and the limited number of single launches, and meet the needs of the UAV 700 for long-distance cluster coordinated operations, reconnaissance or attack on 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 loaded on it to the target mission area in the preset airspace for launch; the launch tube 200 is used for loading, energy storage and launching the folding-wing UAV 700; after the folding-wing UAV 700 is launched in the launch tube 200 under the wing of the mother aircraft, the rotor quickly recovers from the folded state to the flight state, and the folding-wing UAV 700 uses the mother aircraft as a communication relay station in the air, and interacts with the ground station through line-of-sight communication, satellite communication, etc., so as to realize 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 UAV 700 is loaded in the launch chamber 210 of the launch tube 200, and the locking member 310 is in the locking position. The locking member 310 locks the UAV 700 in the launch chamber 210. The launch tube 200 is installed on the transport carrier 100, which can realize cluster storage and launch of the UAV 700. When the UAV 700 is launched, the locking member 310 switches to the unlocking position, and the elastic member 230 ejects the UAV 700 from the launch chamber 210. The launch operation of the UAV 700 is simple and not easy to be detected. The cost is low, and no complicated preparation work is required. It is flexible and convenient to use, and a large number of UAVs 700 can be launched at the same time.

[0052] In some embodiments, see Figure 1 , Figure 3 and Figure 4The locking mechanism 300 further includes a driving assembly 320, which has a driving shaft 321. The driving assembly 320 is mounted on the launch tube 200, and the driving shaft 321 is connected to the locking member 310. The driving assembly 320 has a free state and a working state. When the driving assembly 320 is in the free state, the locking member 310 can be operably rotated around the driving shaft 321, thereby switching the locking member 310 between the locked position and the unlocked position. When the driving assembly 320 is in the working state, the driving assembly 320 drives the locking member 310 to rotate, thereby switching the locking member 310 between the locked position and the unlocked position.

[0053] The driving assembly 320 can be a steering gear or a motor. When the steering gear is powered on, it is in a working state, and the steering gear drives the locking member 310 to rotate. When the steering gear is not powered on, it is in a free state, and the drive shaft 321 can rotate freely. The locking member 310 can be manually moved to switch between the locked position and the 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. The torsion spring 330 connects the locking member 310 and the launch tube 200. When the drive assembly 320 is in a free state, the torsion spring 330 limits the locking member 310 to the locking position. The steering gear, torsion spring 330 and other parts are used together. When the rotor drone 700 is loaded, after one end face of the rotor drone 700 (the groove wall of the notch groove 710) passes over the locking member 310, the locking member 310 automatically rebounds to the original position (locking position) under the action of the torsion spring 330, and automatically locks in the tube after the rotor drone 700 is released; when the rotor drone 700 is unlocked, the steering gear only needs to overcome the torsion of the torsion spring 330 and the friction between the locking member 310 and the end face of the drone 700 (the groove wall of the notch groove 710), which saves effort when unlocking, and a small torque steering gear can be realized.

[0055] In some embodiments, see Figure 1 and Figure 2, a thrust piece 240 is also provided in the launch chamber 210, and the thrust piece 240 is slidably connected in the launch tube 200, and the thrust piece 240 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 thrust piece 240 can be provided to prevent the spring from directly contacting the drone 700, prevent the spring from scratching the drone 700, and can also increase the force-bearing area of ​​the drone 700, ensuring 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 UAV cluster launch mechanism also includes a fixing frame 400 and a carrier rack 500. The carrier rack 500 is installed on the transport carrier 100, and the carrier rack 500 is installed under the wing of the transport carrier 100. The carrier rack 500 is detachably connected to the fixing frame 400, and a plurality of launch tubes 200 are provided. The fixing frame 400 is connected to the plurality of launch tubes 200, and the open ends of the plurality of launch tubes 200 face downward. By providing the fixing frame 400 and the carrier rack 500, the detachable installation of the plurality of launch tubes 200 and the transport carrier 100 is achieved.

[0057] In some embodiments, see Figure 5 , Figure 8 and Fig. 9 The fixing frame 400 includes a connecting plate 410 and a reinforcing plate 420. The upper ends of the plurality of launch tubes 200 are hinged to the connecting plate 410, and the reinforcing plate 420 is connected to the lower ends of the plurality of launch tubes 200. The reinforcing plate 420 is provided with a plurality of first connecting holes 421 and a plurality of second connecting holes 422. One launch tube 200 corresponds to one first connecting hole 421 and one second connecting hole 422. The screw passes through the first connecting hole 421 to connect with the launch tube 200, and the screw passes through the second connecting hole 422 to connect with the launch tube 200. The lower end of the launch tube 200 is connected to the reinforcing plate 420 by two screws, so that the launch tube 200 cannot rotate relative to the connecting plate 410 around the upper end. The upper ends of the plurality of launch tubes 200 are hinged to the connecting plate 410, and the lower ends are connected to the reinforcing plate 420 by two screws, so that the plurality of launch tubes 200 can be assembled into a whole, and the structure is stable.

[0058] In some embodiments, see Figure 2 and Figure 5The launch tubes 200 are arranged in pairs to form a launch tube assembly, and a plurality of launch tube assemblies are provided. The launch tube assembly is connected with a first mounting member 250, a second mounting member 260 and a third mounting member 270. 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 part 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 hinged to the connecting plate 410, the locking mechanism 300 is installed on the second mounting member 260, and the third mounting member 270 is connected to the reinforcement plate 420. The second mounting member 260 is provided with two first mounting holes, and the two launch tubes 200 are respectively penetrated through the two first mounting holes; the third mounting member 270 is provided with two second mounting holes, and the two launch tubes 200 are respectively penetrated through the two second mounting holes. 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 a plug-in protrusion 411 and a first connecting protrusion 412, and 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, and 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 plug-in protrusion 411 to extend into and for limiting the axial rotation of the plug-in protrusion 411 around the third connecting hole 4121. A limiting pad 521 is provided on the inner wall of the slot 520, and when the plug-in protrusion 411 is inserted into the slot 520, the limiting pad 521 abuts against the plug-in protrusion 411. The fastener 413 includes a latch pin 4131 and an R-shaped pin 4132 . The latch pin 4131 is provided with a fastening hole. The latch pin 4131 penetrates the third connection hole 4121 and the fourth connection hole 511 , and the R-shaped pin 4132 penetrates 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 limiting 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 Fig.10The wing-mounted folding-wing UAV cluster launch mechanism also includes a fairing 600, which is detachably mounted on the fixing frame 400, and a receiving cavity is provided in the fairing 600. A launching port 610 is provided at the lower end of the fairing 600, and the launching port 610 is connected to the receiving cavity. The launching tube 200 is installed in the receiving cavity, and the open end of the launching tube 200 faces the launching port 610. The fairing 600 can be detachably arranged. 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 folding state.

[0065] 3. Manually move the locking member 310 to move the locking member 310 out of the launch chamber 210 . The locking member 310 is in the unlocked position, and then the folded rotor drone 700 is inserted into the launch chamber 210 .

[0066] 4. After the rotary-wing UAV 700 moves to the designated position, the locking piece 310 is released, and the locking piece 310 extends into the launching chamber 210 under the action of the torsion spring 330, and the locking piece 310 abuts against the groove wall of the notch groove 710 of the UAV 700. At this time, the tail end of the rotary-wing UAV 700 is thrusted by the thrust piece 240, and a part of the middle section (the groove wall of the notch groove 710) abuts against the end face of the locking piece 310, so that the rotary-wing UAV 700 is locked in the launching tube 200.

[0067] 5. According to the above steps 2, 3, and 4, insert the remaining folding-wing UAVs 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 the level flight state and prepares to launch the folding-wing UAV 700. First, the ground station sends an unlocking command to the mother aircraft 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 groove 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 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 the mission (reconnaissance or suicide attack on the target), the mother aircraft returns.

[0069] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0070] Although the 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 present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. A wing-mounted folding-wing UAV cluster launching mechanism, characterized in that: include: Transport carrier; A launch tube, detachably connected to the transport carrier, wherein a launch chamber with an open lower end for loading the drone is provided in the launch tube, and an opening communicating with the launch chamber is provided on a side wall of the launch tube; An elastic member, installed in the firing chamber; The locking mechanism comprises a locking member, the locking member is rotatably arranged relative to the launching tube, the locking member has a locking position and an unlocking position, when the locking member is in the locking position, the locking member passes through the opening and extends into the launching chamber; when the locking member is in the unlocking position, the locking member moves out of the launching chamber; When the launch tube is loaded with a drone, the locking piece is located in a locking 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 located in an unlocking position, and the elastic piece pops the drone out of the launch chamber.

2. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 1 is characterized in that: The locking mechanism also includes a driving assembly, which has a driving shaft. The driving assembly is installed on the launching tube, and the driving shaft is connected to the locking piece. The driving assembly has a free state and a working state. When the driving assembly is in the free state, the locking piece can be operably rotated around the driving shaft to switch the locking piece between the locking position and the unlocking position; when the driving assembly is in the working state, the driving assembly drives the locking piece to rotate to switch the locking piece between the locking position and the unlocking position.

3. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 2 is characterized in that: The locking mechanism also includes a torsion spring, which is sleeved on the driving shaft and connects the locking member and the launching tube. When the driving assembly is in a free state, the torsion spring limits the locking member to a locking position.

4. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 1 is 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 UAV, the UAV abuts against the thrust piece and the thrust piece squeezes the elastic piece. When the launching tube launches the UAV, the elastic piece ejects the UAV from the launching chamber through the thrust piece.

5. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 1 is characterized in that: It also 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 downwards.

6. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 5 is characterized in that: 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. 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. The screw passes through the first connecting hole to connect to the launching tube, and the screw passes through the second connecting hole to connect to the launching tube.

7. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 6 is 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.

8. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 5 is characterized in that: 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 bracket 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 bracket 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.

9. The wing-mounted folding-wing UAV cluster launching mechanism according to claim 8, characterized in that: 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 comprises 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.

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

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