A sub-UAV storage-launch unit, a UAV swarm storage-launch device and a UAV system

Abstract

This utility model relates to a sub-UAV storage-launch unit, a UAV swarm storage-launch device, and a UAV system, belonging to the field of aerospace technology. It solves the problems of low launch efficiency and poor environmental adaptability in existing ground-based UAV launch devices, and the complex sub-launch structure and low modularity of airborne launch devices. This utility model provides a sub-UAV storage-launch unit, including a cylinder and a locking structure. The cylinder accommodates the sub-UAVs. The locking structure is located outside the cylinder and includes a movable cover plate hinged to the outer wall of the bottom of the cylinder. In the locked state, the movable cover plate is closed, located at the bottom of the cylinder, and blocks the launch port. In the unlocked state, the movable cover plate is open, exposing the launch port. This utility model achieves strong environmental adaptability, simple structure, high modularity, and high launch efficiency.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, and in particular to a sub-UAV storage-launch unit, a UAV swarm storage-launch device, and a UAV system. Background Technology

[0002] With the widespread application of drones in logistics delivery, emergency rescue, light shows, and topographic mapping, multi-drone collaborative operations are gradually becoming an industry trend. Existing single drones have inherent limitations such as limited endurance and payload capacity. Therefore, enabling mission relay and functional expansion through the deployment of sub-drone systems has become an important technological direction. Traditional solutions often use fixed ground launchers or simple mounting devices, which are insufficient to meet the dynamic deployment requirements of mobile platforms and suffer from drawbacks such as susceptibility to environmental interference and long preparation cycles for repeated use. Currently, the integrated storage and rapid sequential launch of multiple sub-drones on aerial platforms still face technical bottlenecks, mainly manifested in issues such as excessive load on the carrier platform due to redundant cabin structures and limited response speed of the launch mechanism. Utility Model Content

[0003] Based on the above analysis, the present invention aims to provide a sub-UAV storage-launch unit, a UAV swarm storage-launch device, and a UAV system to solve the problems of low launch efficiency and poor environmental adaptability of existing ground-based UAV launch devices, and complex launch structure and low modularity of air-based launch devices.

[0004] The objective of this utility model is mainly achieved through the following technical solutions:

[0005] One aspect of this utility model is to provide a sub-UAV storage-launch unit, including a cylindrical body and a locking structure;

[0006] The cylindrical body is used to accommodate the sub-UAV; the locking structure is disposed on the outside of the cylindrical body; the locking structure includes a movable cover plate; the movable cover plate is hinged to the outer wall surface of the bottom of the cylindrical body;

[0007] In the locked state, the movable cover is closed and located at the bottom of the cylinder, blocking the cylinder's firing port; in the unlocked state, the movable cover is open, exposing the cylinder's firing port.

[0008] Furthermore, the locking structure also includes a first elastic element, one end of which is fixed to the outer side of the top of the cylinder, and the other end is fixed to the side of the movable cover plate away from the hinge.

[0009] Furthermore, the locking structure also includes a track; the track includes a first track, a second track, and a third track;

[0010] The first track is disposed on the cylinder; the second track is disposed at the hinge point between the bottom of the cylinder and the movable cover plate; the third track is disposed outside the movable cover plate.

[0011] When the movable cover is closed, the first elastic element is on the first track, the second track, and the third track; when the movable cover is open, the first elastic element is on the first track, and the side of the movable cover away from the hinge faces the first track.

[0012] Furthermore, it also includes a catapult structure; the catapult structure is disposed inside the cylinder and is used to catapult the sub-UAV out of the cylinder;

[0013] The ejection structure includes an ejector and a second elastic element;

[0014] Multiple second elastic elements are provided. One end of the second elastic element is fixed to the inner wall surface of the bottom of the cylinder, and the other end of the second elastic element is fixed to the edge of the push-out member. The push-out member can slide along the inner wall surface of the cylinder.

[0015] When the sub-drone is stored, the ejector is located at the top of the cylinder and abuts against the sub-drone; when the sub-drone is launched, the ejector ejects the sub-drone from the cylinder.

[0016] Furthermore, the inner wall of the cylinder is provided with inserts circumferentially; there are longitudinal receiving grooves between adjacent inserts; the number and shape of the receiving grooves correspond to the number and shape of the wing hinges of the sub-UAV.

[0017] A second aspect of this utility model provides a drone swarm storage-launch device, comprising a housing, a support frame, and the aforementioned sub-drone storage-launch unit;

[0018] Multiple sub-UAV storage-launch units are provided; the multiple sub-UAV storage-launch units are arranged in a circular array on the support frame;

[0019] The support frame is disposed within the housing; the support frame is rotatable relative to the housing.

[0020] Furthermore, the bottom of the housing is provided with an opening that extends radially from the center of the bottom of the housing;

[0021] The opening has a starting portion, an extension portion, and an end portion; the starting portion and the extension portion are used for flipping the movable cover, and the end portion is used for the sub-UAV to pass through during launch; the width of the starting portion and the extension portion is smaller than the width of the end portion.

[0022] Furthermore, it also includes a drive unit, which is disposed on the upper part of the support frame; the drive unit is used to drive the support frame to rotate.

[0023] Furthermore, the drive unit includes a drive component, a transmission component, and a rotating shaft; the rotating shaft is disposed on the central axis of the support frame.

[0024] A third aspect of this utility model is to provide an unmanned aerial vehicle (UAV) system, including a mother UAV, daughter UAVs, and the aforementioned UAV swarm storage-launch device;

[0025] The sub-drones are housed within the drone swarm storage-launch device, which is suspended from the mother drone.

[0026] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0027] (1) In this utility model, the sub-UAV storage-launch unit is provided with a locking structure, which includes a movable cover plate. The movable cover plate is hinged to the bottom side wall of the cylinder; in the locked state, the movable cover plate closes the bottom of the cylinder, blocks the UAV launch port, and prevents the sub-UAV from leaving the cylinder; in the unlocked state, the movable cover plate opens, opens the UAV launch port, and the sub-UAV is launched. It is convenient to operate, locks quickly, helps to achieve rapid launch when the sub-UAV is launched, and has high mechanical reliability.

[0028] (2) In this utility model, the opening and closing of the movable cover is controlled by a first elastic element. One end of the first elastic element is fixed to the outer side of the top of the cylinder, and the other end is fixed to the side of the movable cover away from the hinge. When the movable cover needs to be closed, the movable cover pulls the first elastic element to tension. When the movable cover needs to be opened, the first elastic element returns to its original position, pulling the movable cover to open from the hinge. During use, the locking mechanism automatically returns to its original position without manual adjustment. Furthermore, the arrangement of the first track, the second track, and the third track ensures that the end of the first elastic element runs along the track, guaranteeing that the opening and closing of the movable cover is accurate and reliable.

[0029] (3) Inserts are provided circumferentially on the inner wall of the cylinder, and there are longitudinal receiving grooves between adjacent inserts. The receiving grooves are used to accommodate the wing hinges of the sub-UAV. The number and shape of the receiving grooves correspond to the number and shape of the wing hinges of the sub-UAV. The setting of the inserts and receiving grooves prevents the sub-UAV from rotating or tilting inside the cylinder when it is launched.

[0030] (4) When storing the sub-drone, the present invention uses a catapult structure to push against the top of the sub-drone. One end of the second elastic member is connected to the catapult and the other end is fixed to the bottom of the cylinder, thereby storing a large amount of energy. When the sub-drone is launched, the catapult pushes the sub-drone out. The sub-drone is launched under its own weight and the pushing force of the catapult, and the response is fast.

[0031] (5) In this invention, the sub-UAV storage-launch units are arranged in a circular array on the support frame. The support frame rotates around its own axis under the control of the drive unit to achieve sequential launch of the sub-UAVs, which has high reliability. Moreover, the circular array of the sub-UAV storage-launch units in this invention is similar to a honeycomb storage mode, which improves the storage density of the sub-UAVs.

[0032] (6) In this utility model, the bottom of the shell is provided with an opening, which has a starting part, an extension part and an end part; the width of the starting part and the extension part is smaller than the width of the end part to prevent the sub-UAV from passing through the starting part and the extension part. The starting part and the extension part are used for the flipping of the movable cover plate. The end part of the opening is used for the sub-UAV to pass through during launch, thereby improving storage security.

[0033] (7) Compared with the prior art, this utility model adopts a modular cabin design, with multiple sub-UAV storage-launch units set inside the shell. An opening is provided at the bottom of the shell, and the sub-UAV storage-launch units are set on a support frame, which can rotate relative to the shell. By rotating the support frame relative to the shell, the sub-UAVs are launched sequentially through the opening. The opening of the shell and the double locking of the locking structure together realize the safe storage and rapid sequential launch of multiple sub-UAVs on the flight platform. The structure is simple, safe and reliable, highly modular, and can improve the rapid deployment capability and mission continuity of UAV swarms, and provide all-weather, all-terrain aerial operation support for disaster relief and other fields.

[0034] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages will become apparent from the description or be learned by practicing this invention. The objectives and other advantages of this invention can be realized and obtained from the details specifically pointed out in the text and accompanying drawings. Attached Figure Description

[0035] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0036] Figure 1 A schematic diagram of the sub-UAV storage-launch unit when the locking structure is unlocked;

[0037] Figure 2 This is a schematic diagram of the sub-UAV storage-launch unit when the locking structure is engaged.

[0038] Figure 3 A schematic diagram of the structure of the sub-UAV after its wings are folded;

[0039] Figure 4 A top-view diagram of the structure of the sub-UAV after its wings have been folded.

[0040] Figure 5 This is a schematic diagram of the bottom structure of the cylinder;

[0041] Figure 6 This is a front view of the end face of the insert;

[0042] Figure 7 This is a schematic diagram of the insert's structure;

[0043] Figure 8 A schematic diagram of the structure of the sub-UAV after its wings have been deployed;

[0044] Figure 9 This is a schematic diagram of the shell and its internal structure;

[0045] Figure 10 This is a structural diagram of the support frame and the sub-UAV storage-launch unit;

[0046] Figure 11 This is a schematic diagram of the opening in the shell.

[0047] Figure 12 This is a schematic diagram showing the alignment of the bottom opening of the housing with the sub-UAV storage-launch unit when the locking unit is in the unlocked position.

[0048] Figure 13 A schematic diagram showing the structure in which the bottom opening of the housing is offset from the sub-UAV storage-launch unit when the locking unit is in the locked position;

[0049] Figure 14 This is a schematic diagram of the structure of an unmanned aerial vehicle (UAV) system.

[0050] Figure label:

[0051] 1-Shell, 11-Opening, 111-Starting part, 112-Extension part, 113-End, 12-Hanging ear, 13-First support column, 2-Sub-UAV storage-launch unit, 21-Cylinder, 211-Insert, 212-Receiving slot, 22-Locking structure, 221-Modible cover, 222-First elastic element, 223-Hinge, 224-Railway, 2241-First track, 2242-Second track, 2243-Third track, 23-Ejection structure, 231-Push-out element, 232-Second elastic element, 3-Rotation shaft, 4-Support frame, 41-First plate, 42-Second plate, 43-Second support column, 5-Sub-UAV, 51-Wing hinge, 6-Mother UAV. Detailed Implementation

[0052] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0053] Example 1

[0054] A specific embodiment of this utility model is as follows: Figure 1 and Figure 2 As shown, a sub-UAV storage-launch unit is disclosed, including a cylinder 21 and a locking structure 22.

[0055] The cylindrical body 21 is used to accommodate the sub-UAV 5; the locking structure 22 is disposed outside the cylindrical body 21; the locking structure 22 includes a movable cover plate 221; the movable cover plate 221 is hinged to the outer wall surface of the bottom of the cylindrical body 21;

[0056] In the locked state, the movable cover 221 is closed and located at the bottom of the cylinder 21, blocking the firing port of the cylinder 21; in the unlocked state, the movable cover 221 is open, opening the firing port of the cylinder 21.

[0057] Specifically, the sub-UAV 5 is stored inside the cylinder 21 and launched from the cylinder 21.

[0058] like Figure 3 and Figure 4 As shown, when the sub-drone 5 is stored inside the cylinder 21, its wings are in a folded state, and the wing hinges 51 at least partially protrude from the side of the sub-drone 5. In this embodiment, the sub-drone 5 has four rotors, therefore there are four wing hinges 51. Figures 5-7As shown, an insert 211 is provided on the inner wall of the cylinder 21. Exemplarily, the insert 211 is integrally formed with the cylinder 21, or the insert 211 is detachably connected to the inner wall surface of the cylinder 21. A longitudinal receiving groove 212 is formed between adjacent inserts 211 for accommodating the wing hinge 51 of the sub-UAV 5 during storage. The inserts 211 and the receiving grooves 212 are circumferentially spaced. Corresponding to the wing hinge 51 of the sub-UAV, four receiving grooves 212 are provided, and the shape of the receiving grooves 212 is adapted to the shape of the wing hinge 51.

[0059] When the sub-drone 5 is launched, the insert 211 and the receiving slot prevent the sub-drone 5 from rotating or tilting during launch.

[0060] like Figure 1 and Figure 2 As shown, the locking structure 22 includes a movable cover plate 221. The movable cover plate 221 is hinged to the outer wall surface of the bottom of the cylinder 21 and can rotate about the hinge point to open or close the bottom of the cylinder 21. Figure 1 As shown, when the sub-UAV 5 is launched, the movable cover 221 opens, exposing the launch port of the cylinder 21. Figure 2 As shown, when the sub-drone 5 is stored, the movable cover 221 is closed. The movable cover 221 is located at the bottom of the cylinder 21, blocking the launch port of the cylinder 21 and preventing the sub-drone 5 from leaving the cylinder 21.

[0061] Furthermore, to prevent the movable cover 221 from detaching, a hinge 223 is provided at the hinge joint between the movable cover 221 and the cylinder 21. When the movable cover 221 is closed, it engages with the limiting part 211 at the bottom of the cylinder 21, ensuring that the sub-UAV 5 inside the cylinder 21 is stored securely and reliably.

[0062] Furthermore, the locking structure 22 also includes a first elastic element 222, through which the opening and closing of the movable cover 221 is controlled. One end of the first elastic element 222 is fixed to the outer side of the top of the cylinder 21, and the other end is fixed to the side of the movable cover 221 away from the hinge. The movable cover 221 is hinged to the outer wall surface of the bottom of the cylinder 21. Figure 1 As shown, upon unlocking, the first elastic element 222 returns to its original position, pulling the movable cover 221 to open outwards from the hinge. Figure 2 As shown, when locked, the movable cover plate 221 pulls the first elastic member 222, and the first elastic member 222 is in a stretched state. For example, the first elastic member 222 is a tension spring.

[0063] Furthermore, such as Figure 1 and Figure 2As shown, the locking structure 22 also includes a track 224. The track 224 includes a first track 2241, a second track 2242, and a third track 2243. The first track 2241 is provided on the cylinder 21, and the length direction of the first track 2241 is the same as the height direction of the cylinder 21. The second track 2242 is provided at the hinge point between the bottom of the cylinder 21 and the movable cover plate 221, and the direction of the second track 2242 is the same as the direction of the first track 2241. The third track 2243 is provided on the outside of the movable cover plate 221, and the direction of the third track 2243 is the same as the direction of the line connecting the hinge point to the side of the movable cover plate 221 away from the hinge point. When the movable cover plate 221 is closed, the first elastic element 222 is on the first track 2241, the second track 2242, and the third track 2243. When the movable cover plate 221 is open, the first elastic element 222 is on the first track 2241, and the side of the movable cover plate 221 away from the hinge point faces the first track 2241. The arrangement of the first track 2241, the second track 2242, and the third track 2243 ensures that the second end of the first elastic element 222 runs along the track 224, guaranteeing that the opening and closing actions of the movable cover 221 are accurate and reliable.

[0064] Furthermore, the sub-UAV storage-launch unit 2 also includes a catapult structure 23; such as Figure 1 and Figure 2 As shown, the ejection structure 23 is disposed inside the cylinder 21 and is used to eject the sub-drone 5 out of the cylinder 21. Preferably, the ejection structures 23 are arranged in pairs and symmetrically arranged around the sub-drone 5. In this embodiment, there are two ejection structures 23, symmetrically arranged on both sides of the sub-drone 5.

[0065] The ejection structure 23 includes a pusher 231 and a second elastic member 232. One end of the second elastic member 232 is fixed to the inner wall surface of the lower part of the cylinder 21, and the other end of the second elastic member 232 is disposed on the pusher 231. The pusher 231 can slide along the inner wall surface of the cylinder 21. When the sub-drone 5 is stored, the pusher 231 is located at the top of the cylinder 21 and abuts against the sub-drone 5. One end of the second elastic member 232 is connected to the pusher 231, and the other end is fixed to the inner wall surface of the lower part of the cylinder 21, thereby storing a large amount of energy. When the sub-drone 5 is launched, the pusher 231 ejects the sub-drone 5 from the cylinder 21. The sub-drone 5 is launched under the action of its own gravity and the pushing force of the pusher 231, with a rapid response. For example, the second elastic member 232 is a tension spring.

[0066] like Figure 3 As shown, when storing, the sub-UAV 5 folds its rotors to allow it to enter the cylinder 21; as Figure 8 As shown, when the sub-UAV 5 is launched, after leaving the cylinder 21, it unfolds its folded rotor and enters flight mode.

[0067] Example 2

[0068] This embodiment discloses a storage-launch device for unmanned aerial vehicle (UAV) swarms, such as... Figure 9 As shown, it includes a housing 1, a sub-UAV storage-launch unit 2 of Embodiment 1, and a support frame 4;

[0069] Multiple sub-UAV storage-launch units 2 are provided; the multiple sub-UAV storage-launch units 2 are arranged in a circular array on the support frame 4;

[0070] The support frame 4 is disposed in the housing 1; the support frame 4 is rotatable relative to the housing 1.

[0071] For example, such as Figure 9 As shown, in this embodiment, the housing 1 is a hollow cylindrical structure with a central axis. The housing 1 is provided with a plurality of first support columns 13 for supporting the housing 1. The first support columns 13 are disposed between the top and bottom of the housing 1. Preferably, in order to improve the stability of the housing 1 and avoid interference with the sub-UAV storage-launch unit 2, the first support columns 13 are arranged in a circumferential array along the edge of the housing 1.

[0072] The housing 1 has a through hole in the center for inserting the rotating shaft 331. The top of the housing 1 is also provided with a hanging lug 12 for hanging on the mother drone 6.

[0073] The support frame 4 is disposed in the housing 1, and the support frame 4 is rotatable relative to the housing 1 about its central axis. Preferably, the support frame 4 is coaxial with the housing 1.

[0074] like Figure 10 As shown, the support frame 4 includes a first plate 41, a second plate 42, and a second support column 43. The second support column 43 is disposed between the first plate 41 and the second plate 42 for connecting the first plate 41 and the second plate 42. Preferably, to provide stable support, the second support columns 43 are arranged in an array along the edge of the support frame 4. The first plate 41 and the second plate 42 each have corresponding through holes for inserting the sub-UAV storage-launch unit 2. Further, the through holes are arranged in a circumferential array.

[0075] A drive unit is provided on the upper part of the support frame 4 for driving the support frame 4 to rotate. Exemplarily, the drive unit includes a drive component, a transmission component, and a rotating shaft 3. The rotating shaft 3 is located on the central axis of the support frame 4. In this embodiment, the drive component is a servo motor, and the transmission component consists of a driving gear and a driven gear. Specifically, the output end of the servo motor is connected to the driving gear, the driven gear meshes with the driving gear, and the driven gear is located on the rotating shaft 3. Thus, the servo motor drives the rotating shaft 3 to rotate through the driving gear and the driven gear, causing the support frame 4 and the sub-UAV storage-launch unit 2 on it to rotate accordingly.

[0076] In this embodiment, the support frame 4 rotates relative to the housing 1, and multiple sub-UAV storage-launch units 2 are arranged in a circular array on the support frame 4, rotating with the support frame 4. When the sub-UAV 5 is launched, the rotation of the support frame 4 causes each sub-UAV storage-launch unit 2 to sequentially align with the opening 11 at the bottom of the housing 1, and launch sequentially through the opening 11, resulting in high reliability. Furthermore, in this embodiment, the circular array of the sub-UAV storage-launch units 2 resembles a honeycomb storage mode, increasing the storage density of the sub-UAV 5.

[0077] like Figure 11 As shown, the bottom of the housing 1 has an opening 11. The opening 11 extends radially from the center of the bottom of the housing 1 and has a starting portion 111, an extension portion 112, and an end portion 113. The width of the starting portion 111 and the extension portion 112 is smaller than the width of the end portion 113 to prevent the UAV from flying out of the starting portion 111 and the extension portion 112 and affecting the predetermined flight path. The starting portion 111 and the extension portion 112 are used for flipping the movable cover 221 of the sub-UAV storage-launch unit 2.

[0078] Furthermore, the end of opening 11 has the same circular shape as the bottom of the sub-UAV storage-launch unit 2. When the sub-UAV 5 is launched, as... Figure 12 As shown, the center of the end of the opening 11 coincides with the center of the bottom of one of the cylinders 21. The movable cover 221 flips through the starting part 111 and the extension part 112 of the opening 11. After flipping, the movable cover 221 is pulled to the outside of the side wall of the cylinder 21 by the first elastic member 222. The individual sub-UAV 5 is ejected sequentially through the bottom of the unobstructed cylinder 21 and the opening 11. Figure 13 As shown, when the sub-drone 5 is stored, the center of the circle at the end of the opening 11 is deviated from the center of the bottom of any cylinder 21. At this time, the bottom of the cylinder 21 does not correspond to the opening 11, and the movable cover 221 has no room to flip. The double locking ensures that the sub-drone 5 cannot pass through the opening 11, thus improving storage safety.

[0079] Compared to existing technologies, this embodiment adopts a modular cabin design, with multiple sub-UAV storage-launch units 2 housed within the shell 1. An opening 11 is provided at the bottom of the shell 1, and each sub-UAV storage-launch unit 2 is equipped with a locking structure 22. When the locking structure 22 is unlocked, one sub-UAV 5 can be launched from the opening 11; when the locking structure 22 is locked, no sub-UAV 5 can be launched from the opening 11. The sub-UAV storage-launch unit 2 is mounted on a support frame 4, which is rotatable relative to the shell 1. The rotation of the support frame 4 relative to the shell 1 allows the sub-UAVs 5 to be launched sequentially through the opening 11. The dual locking mechanism of the opening 11 and the locking structure 22 together achieves the safe storage and rapid sequential launch of multiple sub-UAVs 5 on the flight platform. This design is simple, safe, reliable, and highly modular, and enhances the rapid deployment capability and mission continuity of UAV swarms, providing all-weather, all-terrain aerial operational support for disaster relief and other fields.

[0080] Example 3

[0081] This embodiment provides an unmanned aerial vehicle (UAV) system, such as Figure 14 As shown, it includes a mother drone 6, a daughter drone 5, and the drone storage-launch device described in Example 2.

[0082] The drone storage-launch device is suspended from the lower part of the mother drone 6 so that it can be transported to the launch position via the mother drone 6.

[0083] The usage method of this embodiment is as follows:

[0084] Sub-UAV 5 storage: The drive unit drives the rotating shaft 3 to rotate the support frame 4, and the bottom center of the cylinder 21 of the sub-UAV storage-launch unit 2 coincides with the end center of the bottom opening 11 of the housing 1. The movable cover 221 of the sub-UAV storage-launch unit 2 is opened, and the arm of the sub-UAV 5 is folded and passes through the limiting part 211 at the bottom of the cylinder 21. The sub-UAV 5 abuts against the push-out member 231, pushing the sub-UAV 5 to the top. The movable cover 221 is rotated to the bottom of the cylinder 21 via the hinge 223 and locked into the limiting part 211. At this time, the first elastic member 222 is stretched. Thus, the sub-UAV is stored in the sub-UAV storage-launch unit 2.

[0085] The drive unit rotates the support frame 4 again, and loads multiple sub-UAVs 5 into the sub-UAV storage-launch unit 2 in sequence.

[0086] After loading is complete, the drive unit drives the support frame 4 to rotate until the center of the end of the opening 11 at the bottom of the housing 1 is offset from the center of the bottom of the cylinder 21 of any sub-drone storage-launch unit 2. In this embodiment, the locking structure 22 in the sub-drone storage-launch unit 2 closes the movable cover to store the sub-drone, and the opening 11 at the bottom of the housing 1 is offset from the bottom of the cylinder 21 of the sub-drone storage-launch unit 2 to further prevent the sub-drone storage-launch unit 2 from being launched, achieving double locking and improving the storage safety of the device.

[0087] Mounting: Mount the loaded sub-UAV 5 to the sub-UAV storage-launch unit 2 via the mounting lug 12 to the positioning hole on the mother UAV 6, connect the power servo motor power supply line and signal line and plug terminal, turn on the power servo motor power supply switch, and be ready to launch at any time.

[0088] Launch: The mother UAV 6 transports the device to the launch position. The servo motor rotates the support frame 4, aligning the center of the end of the opening 11 of the shell 1 with the center of the bottom of the cylinder 21 of one of the sub-UAV storage-launch units 2. The locking structure 22 of the sub-UAV 5 to the sub-UAV storage-launch unit 2 is activated. The first elastic element 222 opens the movable cover 221, connecting the opening 11 to the cylinder 21. With no bottom support, the thrust element 231 of the ejection structure 23 pushes the sub-UAV 5. Under the action of gravity and thrust, the sub-UAV 5 is ejected from the cylinder 21, passes through the opening 11, and exits the launch device. After the sub-UAV 5 is ejected with a certain acceleration, the internal accelerometer senses the ejection speed, and the internal trigger mechanism extends the arms, initiating flight and commencing operations.

[0089] Rotate the support frame 4 to launch the sub-drones 5 in sequence.

[0090] In this embodiment, the rotation of the support frame 4 relative to the housing 1 enables the sub-drones 5 to be launched sequentially through the opening 11. The opening 11 of the housing 1 and the locking structure 22 together enable the safe storage and rapid sequential launch of multiple sub-drones 5 on the flight platform. The structure is simple, safe and reliable, and can improve the rapid deployment capability and mission continuity of the drone swarm, and provide all-weather, all-terrain aerial operation support for disaster relief and other fields.

[0091] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. A sub-UAV storage-launch unit, comprising: Includes a cylindrical body (21) and a locking structure (22); The cylindrical body (21) is used to accommodate the sub-UAV (5); the locking structure (22) includes a movable cover plate (221); the movable cover plate (221) is hinged to the outer wall surface of the bottom of the cylindrical body (21); In the locked state, the movable cover (221) is closed and located at the bottom of the cylinder (21), blocking the firing port of the cylinder (21); in the unlocked state, the movable cover (221) is opened, opening the firing port of the cylinder (21).

2. The sub-UAV storage-launch unit according to claim 1, characterized in that, The locking structure (22) further includes a first elastic element (222), one end of which is fixed to the outer side of the top of the cylinder (21), and the other end is fixed to the side of the movable cover plate (221) away from the hinge.

3. The sub-UAV storage-launch unit according to claim 2, characterized in that, The locking structure further includes a track (224); the track (224) includes a first track (2241), a second track (2242) and a third track (2243); The first track (2241) is disposed on the cylinder (21); the second track (2242) is disposed at the hinge between the bottom of the cylinder (21) and the movable cover plate (221); the third track (2243) is disposed outside the movable cover plate (221); When the movable cover (221) is closed, the first elastic element (222) is on the first track (2241), the second track (2242), and the third track (2243); when the movable cover (221) is open, the first elastic element (222) is on the first track (2241), and the side of the movable cover (221) away from the hinge faces the first track (2241).

4. The sub-UAV storage-launch unit according to claim 1, characterized in that, It also includes a catapult structure (23); the catapult structure (23) is disposed inside the cylinder (21) and is used to eject the sub-UAV (5) out of the cylinder (21). The ejection structure (23) includes an ejector (231) and a second elastic element (232); Multiple second elastic elements (232) are provided. One end of the second elastic element (232) is fixed to the inner wall surface of the bottom of the cylinder (21), and the other end of the second elastic element (232) is fixed to the edge of the pusher (231). The pusher (231) can slide along the inner wall surface of the cylinder (21). When the sub-drone (5) is stored, the ejector (231) is located on top of the cylinder (21) and abuts against the sub-drone (5); when the sub-drone (5) is launched, the ejector (231) ejects the sub-drone (5) from the cylinder (21).

5. The sub-UAV storage-launch unit according to claim 1, characterized in that, The inner wall of the cylinder (21) is provided with inserts (211) circumferentially; there are longitudinal receiving grooves (212) between adjacent inserts (211); the number and shape of the receiving grooves (212) correspond to the number and shape of the wing hinges (51) of the sub-UAV (5).

6. A storage-launch device for unmanned aerial vehicle (UAV) swarms, characterized in that, It includes a housing (1), a support frame (4), and a sub-UAV storage-launch unit (2) as described in any one of claims 1-5. Multiple sub-UAV storage-launch units (2) are provided; the multiple sub-UAV storage-launch units (2) are arranged in a circular array on the support frame (4); The support frame (4) is disposed in the housing (1); the support frame (4) is rotatable relative to the housing (1).

7. The UAV swarm storage-launch device according to claim 6, characterized in that, The bottom of the housing (1) is provided with an opening (11), which extends radially from the center of the bottom of the housing (1). The opening (11) has a starting part (111), an extension part (112) and an end part (113); the starting part (111) and the extension part (112) are used for the flipping of the movable cover plate (221), and the end part (113) is used for the sub-UAV (5) to pass through during launch; the width of the starting part (111) and the extension part (112) is smaller than the width of the end part (113).

8. The UAV swarm storage-launch device according to claim 6, characterized in that, It also includes a drive unit, which is disposed on the upper part of the support frame (4); the drive unit is used to drive the support frame (4) to rotate.

9. The UAV swarm storage-launch device according to claim 8, characterized in that, The drive unit includes a drive component, a transmission component, and a rotating shaft (3); the rotating shaft (3) is located on the central axis of the support frame (4).

10. An unmanned aerial vehicle (UAV) system, characterized in that, Includes a mother drone (6), a daughter drone (5), and a drone swarm storage-launch device as described in any one of claims 6-9; The sub-UAV (5) is located inside the UAV swarm storage-launch device, which is suspended on the mother UAV (6).

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