Folding four-rotor unmanned aerial vehicle double-launching platform

Abstract

The utility model discloses a folding four-rotor unmanned aerial vehicle double launching platform which comprises a rectangular frame and a control assembly, a plurality of launching cabins are arranged in the rectangular frame, each launching cabin comprises a guide rail, a lead screw, a tray, a sliding block, a connecting plate and a driving motor, the power output end of the driving motor is connected with the vertically-arranged lead screw, and the tray is arranged on the guide rail. The lead screw is in threaded connection with a center hole of the connecting plate, one end of the connecting plate is connected with the tray, the other end of the tray is connected with the sliding block, the sliding block is matched with the guide rail in a sliding mode, the guide rail is parallel to the lead screw, the individual soldier launching system is installed on the tray, and the driving motor is electrically connected with the control assembly and controls the tray to reciprocate up and down.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicle (UAV) launch, and in particular relates to a foldable four-rotor UAV dual-launching platform. Background Art

[0002] As drone technology matures, its launch technology is receiving increasing attention and attention, especially in the military. Based on the launch volume, drones can be roughly divided into two types: platform-launched and individual-soldier-launched. Currently, most drone launch platforms are vehicle-mounted, which are bulky, heavy, and expensive. They are also difficult to disassemble and maintain, and platform-launched launches cannot be integrated with individual-soldier combat operations. Therefore, it is necessary to develop a launch platform that is lightweight, inexpensive, easy to disassemble and maintain, and can be used in conjunction with individual-soldier combat operations. Utility Model Content

[0003] The purpose of this utility model is to solve the problems of the existing technology and provide a foldable four-rotor UAV dual-launch platform, which solves the problems of the existing technology such as large size and weight, high cost, difficulty in disassembly and maintenance, and inability of platform launch to be integrated with individual combat.

[0004] In order to solve the technical problem, the technical solution of the utility model is: a folding four-rotor UAV dual-launch platform, including a rectangular frame and a control component, a number of launch cabins are arranged in the rectangular frame, each launch cabin includes a guide rail, a screw, a tray, a slider, a connecting plate and a drive motor, the power output end of the drive motor is connected to the vertically arranged screw, the screw is threadedly connected to the center hole of the connecting plate, one end of the connecting plate is connected to the tray, and the other end of the tray is connected to the slider, the slider slides in cooperation with the guide rail, the guide rail is arranged parallel to the screw, and a single-soldier launch system is installed on the tray, the drive motor is electrically connected to the control component to control the tray to move up and down.

[0005] Preferably, two launch cabins are provided in the rectangular frame, and the two launch cabins are centrally symmetrically arranged. The tray of each launch cabin is screwed to the carbon plate at the bottom of the individual launch system, and the individual launch system is equipped with a drone in a folded state.

[0006] Preferably, a baffle is installed on the outer periphery of the rectangular frame, an upper cover is installed on the top of the rectangular frame, one end of the upper cover is connected to the baffle by a hinge, and a spring latch is installed on the other end of the upper cover. A lock seat is provided at the position corresponding to the spring latch on the top of the rectangular frame, and the spring latch is cooperated with the lock seat. The opening angle of the baffle is 0°~240°, a front maintenance cover is provided on the baffle on the front side of the rectangular frame, and a rear maintenance cover is provided on the baffle on the rear side of the rectangular frame.

[0007] Preferably, there are two guide rails and two sliders, the two guide rails are respectively arranged on the inner wall of the baffle of the rectangular frame, the two sides of the tray are respectively connected to the sliders through connecting pieces, and the two sliders slide in cooperation with the guide rails.

[0008] Preferably, a screw fixing seat is provided on the top of the launch cabin of the rectangular frame, and the screw fixing seat is cooperatively connected with the screw.

[0009] Preferably, a starting travel switch is installed at a position corresponding to the lower end of the lead screw, and an end travel switch is installed at a position corresponding to the upper end of the lead screw. The starting travel switch and the end travel switch are electrically connected to the control component respectively.

[0010] Preferably, at least four handles are provided on the top of the outer periphery of the rectangular frame.

[0011] Compared with the prior art, the advantages of the present invention are:

[0012] (1) The utility model uses a power system consisting of a drive motor, a lead screw, a guide rail, and a slider. The drive motor is electrically connected to a control component, and the control component is used to control the pallet to move up and down. A single-soldier launch system is installed on the pallet, and the single-soldier launch system is loaded with a folded UAV, thereby achieving seamless integration with the single-soldier launch system.

[0013] (2) The utility model has several launch bays arranged in a rectangular frame, which can launch two or more drones at a time. Each launch bay has an independent upper cover plate, on which a spring latch is installed to unlock and lock the upper cover plate without affecting each other;

[0014] (3) The drive motor of the utility model is installed in the middle position of the bottom of the rectangular frame, the guide rail is installed in the middle position, and the two launch cabins are arranged symmetrically, which can effectively avoid mutual interference between the two individual launch systems during launch;

[0015] (4) The utility model is easy to deploy, has low noise, simple structure, small size, low cost, easy to disassemble and maintain, easy to carry, seamlessly integrated with the individual launch system, remotely controlled throughout the entire process, and has good reliability. It can be used in combination with drones and individual launch systems. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 , a schematic structural diagram of a dual-launching platform for a foldable quad-rotor UAV of the present invention;

[0017] Figure 2 , A schematic diagram of the usage status of a dual-launching platform of a foldable four-rotor UAV of the present invention.

[0018] Description of reference numerals:

[0019] 1. Rectangular frame, 2. Baffle, 3. Guide rail, 4. Front maintenance cover, 5. Screw fixing seat, 6. Screw, 7. Tray, 8. Connecting piece, 9. Slider, 10. Connecting plate, 11. Starting stroke switch, 12. Drive motor, 13. End stroke switch, 14. Handle, 15. Spring latch, 16. Lock seat, 17. Hinge, 18. Upper cover, 19. UAV, 20. Individual launching system, 21. Rear maintenance cover. DETAILED DESCRIPTION

[0020] The following describes the specific implementation of the present invention in conjunction with the embodiments:

[0021] It should be noted that the structures, proportions, sizes, etc. shown in this specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the conditions for the implementation of the present invention. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical content disclosed in this utility model without affecting the efficacy and purpose that can be achieved by the present utility model.

[0022] Example 1

[0023] like Figures 1 and 2 As shown, the utility model discloses a folding four-rotor UAV dual-launch platform, including a rectangular frame 1 and a control component. Several launch cabins are arranged in the rectangular frame 1, each launch cabin includes a guide rail 3, a screw 6, a tray 7, a slider 9, a connecting plate 10 and a drive motor 12. The power output end of the drive motor 12 is connected to the vertically arranged screw 6, the screw 6 is threadedly connected to the center hole of the connecting plate 10, one end of the connecting plate 10 is connected to the tray 7, and the other end of the tray 7 is connected to the slider 9. The slider 9 slides in cooperation with the guide rail 3, and the guide rail 3 is arranged parallel to the screw 6. A single-soldier launch system 20 is installed on the tray 7, and the drive motor 12 is electrically connected to the control component to control the tray 7 to move up and down.

[0024] Example 2

[0025] like Figure 1 As shown, preferably, two launch cabins are provided in the rectangular frame 1, and the two launch cabins are centrally symmetrically arranged. The tray 7 of each launch cabin is screwed to the carbon plate at the bottom of the individual launch system 20, and the individual launch system 20 is equipped with a drone 19 in a folded state.

[0026] The rectangular frame 1 is formed by connecting profiles or composite tubes. It is a rectangular frame with two or more launch cabins arranged therein. Each launch cabin has an independent upper cover plate 18 that can be opened / closed.

[0027] like Figure 1As shown, preferably, a baffle 2 is installed on the outer periphery of the rectangular frame 1, an upper cover 18 is installed on the top of the rectangular frame 1, one end of the upper cover 18 is connected to the baffle 2 by a hinge 17, and a spring latch 15 is installed on the other end of the upper cover 18. A lock seat 16 is provided at the position corresponding to the spring latch 15 on the top of the rectangular frame 1, and the spring latch 15 is cooperated with the lock seat 16. The opening angle of the baffle 2 is 0°~240°, and a front maintenance cover 4 is provided on the baffle 2 on the front side of the rectangular frame 1, and a rear maintenance cover 21 is provided on the baffle 2 on the rear side of the rectangular frame 1.

[0028] The upper cover plates 18 are connected to the side baffles 2 via hinges 17 and can be opened at an angle of 0° to 240°.

[0029] The drive motor 12 is installed in the middle position of the bottom of the rectangular frame 1, the guide rail 3 is installed in the middle position, and the two launch cabins are symmetrically arranged, which can effectively avoid mutual interference between the two individual launch systems 20 during launch.

[0030] Example 3

[0031] like Figure 1 As shown, preferably, there are two guide rails 3 and two sliders 9, and the two guide rails 3 are respectively arranged on the inner wall of the baffle 2 of the rectangular frame 1. The two sides of the tray 7 are connected to the sliders 9 through connecting pieces 8, and the two sliders 9 slide in cooperation with the guide rails 3.

[0032] like Figure 1 As shown, preferably, a screw fixing seat 5 is provided on the top of the launch cabin of the rectangular frame 1, and the screw fixing seat 5 is cooperatively connected with the screw 6.

[0033] like Figure 1 As shown, preferably, a starting point travel switch 11 is installed at a position corresponding to the lower end of the screw 6, and an end point travel switch 13 is installed at a position corresponding to the upper end of the screw 6.

[0034] A starting point travel switch 11 and an end point travel switch 13 are installed at corresponding positions on both ends of the lead screw 6 to limit the travel of the drive motor 12 to reach the height required when the individual launching system 20 is deployed.

[0035] like Figure 1 As shown, preferably, at least four handles 14 are provided on the top of the outer periphery of the rectangular frame 1 .

[0036] The working principle of this utility model is as follows:

[0037] like Figures 1 and 2As shown, the utility model discloses a foldable four-rotor UAV dual-launch platform, including a rectangular frame 1 connected by profiles, with thin-walled baffles 2 installed around the outside, and an upper cover 18 configured as a movable cover by a hinge 17, with a symmetrical layout, at least one maintenance cover is provided on the four baffles 2, and connected by a hinge 17, and spring latches 15 are provided on the upper cover 18 and the maintenance cover, at least four handles 14 are provided on the top of the outer periphery of the rectangular frame 1, two motors and four guide rails 3 are provided inside the rectangular frame 1, a driving motor 12 is connected to a tray 7 through a connecting plate 10, and the other two ends of the tray 7 are connected to a slider 9, which can control the two trays 7 to reciprocate up and down, and a travel switch is provided at each end of the lead screw 6 to control the limit.

[0038] The utility model comprises a power system consisting of a drive motor 12, a lead screw 6, a guide rail 3, and a slider 9 to control the tray 7 to move up and down, and the tray 7 is screwed to the carbon plate at the bottom of the individual-soldier launching system 20. The individual-soldier launching system is equipped with a folded drone 19. When launching, the upper cover 18 is first opened manually, and the drive motor 12 is controlled by the control component (remote control) to push the tray 7 and the individual-soldier launching system 20 to a specified height, and then the individual-soldier launching system 20 is controlled to launch the drone 19. The principles of the remaining launch cabins are similar.

[0039] The utility model drives a power system composed of a motor, a lead screw, a guide rail, and a slider. The drive motor is electrically connected to a control component, and the control component is used to control the tray to move up and down. A single-soldier launching system is installed on the tray, and the single-soldier launching system is loaded with a folded drone, thereby achieving seamless integration with the single-soldier launching system.

[0040] The utility model has a rectangular frame in which a plurality of launch chambers are arranged, which can launch two or more UAVs at a time. Each launch chamber has an independent upper cover plate, on which a spring latch is installed for unlocking and locking without affecting each other.

[0041] The drive motor of the utility model is installed in the middle position of the bottom of the rectangular frame, the guide rail is installed in the middle position, and the two launch cabins are symmetrically arranged, which can effectively avoid mutual interference between the two individual launch systems during launch.

[0042] The utility model has the advantages of easy deployment, low noise, simple structure, small size, low cost, easy disassembly and maintenance, convenient transportation, seamless integration with the individual launch system, full remote control, good reliability, and can be used in combination with the UAV and the individual launch system.

[0043] The utility model has the advantages of simple structure, convenient transportation, reusability, low cost, and can also launch two or more UAVs at the same time.

[0044] The preferred embodiments of the present invention are described in detail above, but the present invention is not limited to the above embodiments. Various changes can be made within the knowledge of ordinary technicians in this field without departing from the purpose of the present invention.

[0045] Many other changes and modifications can be made without departing from the concept and scope of the present invention. It should be understood that the present invention is not limited to specific embodiments, and the scope of the present invention is defined by the appended claims.

Claims

1. A foldable quad-rotor UAV dual-launch platform, characterized by: The invention comprises a rectangular frame (1) and a control component. A plurality of launch chambers are arranged in the rectangular frame (1). Each launch chamber comprises a guide rail (3), a lead screw (6), a tray (7), a slider (9), a connecting plate (10) and a driving motor (12). The power output end of the driving motor (12) is connected to a vertically arranged lead screw (6). The lead screw (6) is threadedly connected to a center hole of the connecting plate (10). One end of the connecting plate (10) is connected to the tray (7). The other end of the tray (7) is connected to the slider (9). The slider (9) slides in cooperation with the guide rail (3). The guide rail (3) and the lead screw (6) are arranged in parallel. An individual launch system (20) is installed on the tray (7). The driving motor (12) is electrically connected to the control component to control the tray (7) to reciprocate up and down.

2. A foldable quad-rotor UAV dual-launching platform according to claim 1, characterized in that: Two launch chambers are arranged in the rectangular frame (1), and the two launch chambers are arranged symmetrically with respect to the center. The tray (7) of each launch chamber is screwed to the carbon plate at the bottom of the individual launch system (20), and the individual launch system (20) contains a drone (19) in a folded state.

3. The foldable quad-rotor UAV dual-launching platform according to claim 1, characterized in that: A baffle (2) is installed on the outer periphery of the rectangular frame (1), an upper cover (18) is installed on the top of the rectangular frame (1), one end of the upper cover (18) is connected to the baffle (2) via a hinge (17), a spring latch (15) is installed on the other end of the upper cover (18), a lock seat (16) is provided at a position corresponding to the spring latch (15) on the top of the rectangular frame (1), the spring latch (15) is cooperatively connected with the lock seat (16), the opening angle of the baffle (2) is 0° to 240°, a front maintenance cover (4) is provided on the baffle (2) on the front side of the rectangular frame (1), and a rear maintenance cover (21) is provided on the baffle (2) on the rear side of the rectangular frame (1).

4. A foldable quad-rotor UAV dual-launching platform according to claim 3, characterized in that: There are two guide rails (3) and two sliders (9), and the two guide rails (3) are respectively arranged on the inner wall of the baffle (2) of the rectangular frame (1). The two sides of the tray (7) are respectively connected to the sliders (9) through connecting pieces (8), and the two sliders (9) slide in cooperation with the guide rails (3).

5. The foldable quad-rotor UAV dual-launching platform according to claim 1, characterized in that: A lead screw fixing seat (5) is provided on the top of the launch cabin of the rectangular frame (1), and the lead screw fixing seat (5) is cooperatively connected with the lead screw (6).

6. The foldable quad-rotor UAV dual-launching platform according to claim 1, characterized in that: A starting travel switch (11) is installed at a position corresponding to the lower end of the lead screw (6), and an end travel switch (13) is installed at a position corresponding to the upper end of the lead screw (6). The starting travel switch (11) and the end travel switch (13) are respectively electrically connected to the control component.

7. The foldable quad-rotor UAV dual-launching platform according to claim 1, characterized in that: At least four handles (14) are arranged at the top of the outer periphery of the rectangular frame (1).

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