Quick-release connecting assembly for a compound wing unmanned aerial vehicle

Abstract

The utility model discloses a kind of quick-release connection components for composite wing unmanned aerial vehicle, including fuselage and fixed wing installed on fuselage, both sides of fixed wing are equipped with mounting seat, and detachable multi-rotor mounting frame is installed on mounting seat.The beneficial effects of the utility model are as follows: by setting first spring, first lifting rod and installation pipe cooperation can make first lifting rod and first lifting plate can be lifted along installation pipe, drive the first locking groove on locking block and the locking block on fixed wing are inserted and locked, complete the quick installation of fuselage and fixed wing, second lifting rod is inserted into second locking groove under the action of second spring, complete the locking installation of mounting seat and multi-rotor mounting frame, so as to realize the quick installation and disassembly of multi-rotor on multi-rotor mounting frame, facilitate the disassembly and transportation of unmanned aerial vehicle, avoid wing damage in the process of transportation, knock damage, prolong the service life of unmanned aerial vehicle wing.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a quick-release connection component for a compound-wing UAV. Background Technology

[0002] The development of drone technology and the market is generally showing a trend of diversification and rapid growth, and the commercial sales market is also expanding. However, with the continuous expansion of drone application scenarios, the market demand for high-performance and high-efficiency drones is increasing. Against this backdrop, compound-wing drones have emerged, riding the wave of the times, thanks to the continuous development of modern materials science, power systems, and automatic control technologies. A compound-wing drone is a design that combines the characteristics of fixed-wing and multi-rotor drones, aiming to reduce flight energy consumption, improve flight efficiency, and expand flight range by leveraging the advantages of two different flight principles. Compound-wing drones typically employ a fixed-wing aerodynamic design to achieve long-duration cruise flight, while combining rotors or other vertical take-off and landing devices for take-off, landing, and hovering in confined spaces.

[0003] Compound-wing UAVs are equipped with multiple fixed wings and multi-rotors to meet various flight requirements. In some existing compound-wing UAVs, the wings are generally fixedly connected to the fuselage, resulting in a large overall space occupation of the UAV. This not only increases the difficulty of transporting and handling the UAV, but also makes the wings more susceptible to damage during transportation, leading to increased maintenance costs. Utility Model Content

[0004] The purpose of this invention is to overcome the shortcomings of existing composite wing drones, where the wings and fuselage are generally fixedly connected, resulting in a large overall space occupation of the drone. This not only increases the difficulty of transporting and handling the drone, but also makes the wings prone to damage during transportation, leading to increased maintenance costs. The invention provides a quick-release connection component for composite wing drones.

[0005] The purpose of this utility model is achieved through the following technical solution: a quick-release connection component for a compound wing UAV, including a fuselage and a fixed wing mounted on the fuselage, with mounting seats installed on both sides of the fixed wing, and a detachable multi-rotor mounting bracket installed on the mounting seats;

[0006] The fuselage has slots on its inner top and bottom walls. A plug that matches the slots is provided on one side of the fixed wing. An installation tube is installed on the fuselage. A first lifting rod is installed inside the installation tube. A first lifting plate that is slidably connected to the installation tube is installed in the middle of the first lifting rod. The first lifting plate can be raised and lowered along the inner wall of the installation tube. A first spring is installed between the bottom of the first lifting plate and the inner bottom wall of the installation tube. The bottom of the first lifting rod extends into the fuselage and is fitted with a locking block. Locking blocks are installed on the inner top and bottom walls of the fixed wing. A first locking groove that matches the locking block is provided on one side of the locking block.

[0007] By setting up a first spring, a first lifting rod, and an installation tube, the first lifting rod and the first lifting plate can move up and down along the installation tube. When installing the fuselage and fixed wing, first press the first lifting rod to move the locking block closer to the middle of the fuselage. After the insert on the fixed wing is inserted into the slot on the fuselage, release the first lifting rod. At this time, the first lifting rod rises and resets under the action of the first spring and the first lifting plate, which drives the first locking groove on the locking block to insert and lock with the locking block on the fixed wing, completing the quick installation of the fuselage and fixed wing. When disassembling, press the first lifting rod again to release the locking block from the first locking groove on the locking block, completing the quick disassembly of the fixed wing.

[0008] The mounting base has a mounting slot, and a second lifting rod is installed on the mounting base, penetrating the mounting slot and extending into the mounting base. A second lifting plate is installed in the middle of the second lifting rod, which is slidably connected to the inner wall of the mounting slot. A second spring is installed between the bottom wall of the second lifting plate and the bottom wall of the mounting slot. One end of the multi-rotor mounting frame extends into the mounting base and has a second locking groove. The bottom of the second lifting rod is adapted to the second locking groove. When installing the multi-rotor mounting frame, first lift the second lifting rod to compress the second spring. After inserting the multi-rotor mounting frame into the mounting base, release the second lifting rod. When the second locking groove slides to the bottom of the second lifting rod, the second lifting rod extends into the second locking groove under the action of the second spring to complete the locking installation of the mounting base and the multi-rotor mounting frame. Disassembly is the same as the above operation, thereby realizing the quick installation and removal of the multi-rotor on the multi-rotor mounting frame, facilitating the transportation of the UAV, avoiding damage to the wings during transportation, and extending the service life of the UAV wings.

[0009] A further technical solution involves installing a rotating block on the upper part of the first lifting rod, providing a sliding groove on the inner wall of the mounting tube, and installing a slider on the first lifting plate that is slidably connected to the sliding groove. The mounting tube is rotatably connected to the machine body. This rotatable connection between the mounting tube and the machine body allows the first lifting rod to rotate via the rotating block. With the cooperation of the sliding groove and the slider, the mounting tube rotates to lock the block, thereby retracting the locking block into the machine body. This prevents damage to the locking block during transportation and ensures the service life of the equipment.

[0010] A further technical solution is to install a rotating rod on the first lifting rod and two sets of stops on the machine body. The stops are used to limit the rotation angle of the rotating rod and the first lifting rod by setting the stops, which facilitates the docking of the first locking groove on the locking block at the bottom of the first lifting rod with the locking block, thereby improving the installation efficiency of the equipment.

[0011] A further technical solution is that the end of the locking block furthest from the machine body is tapered. This tapered design facilitates the docking and installation of the locking block with the first locking groove.

[0012] A further technical solution is to install a pressing block on the upper part of the second lifting rod. By setting the pressing block, the second lifting rod can be easily lifted, improving the convenience of operation.

[0013] A further technical solution is that the joints of the fuselage, fixed wing, mounting base, and multi-rotor mounting frame are all hollow. This hollow joint design facilitates the connection of wiring and avoids unnecessary risks caused by exposed wiring.

[0014] This utility model has the following advantages: By setting a first spring, a first lifting rod, and a mounting tube in cooperation, the first lifting rod and the first lifting plate can move up and down along the mounting tube, driving the first locking groove on the locking block to engage and lock with the locking block on the fixed wing, thus completing the rapid installation of the fuselage and the fixed wing. When disassembling, pressing the first lifting rod again releases the locking block from the first locking groove on the locking block, completing the rapid disassembly of the fixed wing. Under the action of the second spring, the second lifting rod extends into the second locking groove to lock the mounting base and the multi-rotor mounting frame, thereby realizing the rapid installation and disassembly of the multi-rotor on the multi-rotor mounting frame, facilitating the disassembly and transportation of the UAV, avoiding damage to the wings during transportation, and extending the service life of the UAV wings. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0016] Figure 2 This is a partial cross-sectional schematic diagram of the fixed-wing structure of this utility model;

[0017] Figure 3 For the present utility model Figure 2 Enlarged schematic diagram of structure A in the middle;

[0018] Figure 4 This is a cross-sectional view of the mounting base of this utility model;

[0019] In the diagram, 1. Fuselage; 2. Fixed wing; 3. Mounting base; 4. Multirotor mounting bracket; 5. Mounting tube; 6. First lifting rod; 7. Rotating block; 8. First lifting plate; 9. Locking block; 10. First locking groove; 11. Locking block; 12. Rotating rod; 13. Stop block; 14. Slot; 15. Insert block; 16. Pressing block; 17. Slide groove; 18. First spring; 19. Second lifting plate; 20. Second spring; 21. Mounting groove; 22. Second lifting rod; 23. Second locking groove; 24. Slider. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0021] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0022] It should be noted that, where there is no conflict, the embodiments and features in the embodiments of this utility model can be combined with each other.

[0023] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0024] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this utility model is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are only used for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first," "second," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0025] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0026] like Figures 1-4As shown, a quick-release connection component for a compound wing UAV includes a fuselage 1 and a fixed wing 2 mounted on the fuselage 1. Mounting seats 3 are installed on both sides of the fixed wing 2, and a detachable multi-rotor mounting bracket 4 is installed on the mounting seats 3.

[0027] The fuselage 1 has slots 14 on its inner top and bottom walls. The fixed wing 2 has a plug 15 on one side that matches the slot 14. The fuselage 1 is equipped with an installation tube 5. The installation tube 5 is equipped with a first lifting rod 6. The middle of the first lifting rod 6 is equipped with a first lifting plate 8 that is slidably connected to the installation tube 5. The first lifting plate 8 can be raised and lowered along the inner wall of the installation tube 5. A first spring 18 is installed between the bottom of the first lifting plate 8 and the inner bottom wall of the installation tube 5. The bottom of the first lifting rod 6 extends into the fuselage 1 and is equipped with a locking block 9. The fixed wing 2 has locking blocks 11 on its inner top and bottom walls. The locking block 9 has a first locking groove 10 on one side that matches the locking block 11.

[0028] By setting the first spring 18, the first lifting rod 6, and the mounting tube 5 in coordination, the first lifting rod 6 and the first lifting plate 8 can be raised and lowered along the mounting tube 5. When installing the fuselage 1 and the fixed wing 2, first press the first lifting rod 6 to move the locking block 9 closer to the middle of the fuselage 1. After the insertion block 15 on the fixed wing 2 is inserted into the slot 14 on the fuselage 1, release the first lifting rod 6. At this time, the first lifting rod 6 rises and resets under the action of the first spring 18 and the first lifting plate 8, which drives the first locking groove 10 on the locking block 9 to be inserted and locked into the locking block 11 on the fixed wing 2, thus completing the quick installation of the fuselage 1 and the fixed wing 2. When disassembling, press the first lifting rod 6 again to unlock the locking block 11 and the first locking groove 10 on the locking block 9, thus completing the quick disassembly of the fixed wing 2.

[0029] The mounting base 3 is provided with a mounting groove 21. A second lifting rod 22 is installed on the mounting base 3, penetrating the mounting groove 21 and extending into the interior of the mounting base 3. A second lifting plate 19 is installed in the middle of the second lifting rod 22, which is slidably connected to the inner wall of the mounting groove 21. A second spring 20 is installed between the bottom wall of the second lifting plate 19 and the inner bottom wall of the mounting groove 21. One end of the multi-rotor mounting frame 4 extends into the mounting base 3 and has a second locking groove 23. The bottom of the second lifting rod 22 is adapted to the second locking groove 23. When installing the multi-rotor mounting frame 4, the second lifting rod is first... 22 is lifted to compress the second spring 20. After the multi-rotor mounting bracket 4 is inserted into the mounting base 3, the second lifting rod 22 is released. When the second locking groove 23 slides below the second lifting rod 22, the second lifting rod 22 extends into the second locking groove 23 under the action of the second spring 20 to complete the locking installation of the mounting base 3 and the multi-rotor mounting bracket 4. Disassembly is the same as the above operation, thereby realizing the quick installation and disassembly of the multi-rotor on the multi-rotor mounting bracket 4, which facilitates the transportation of the UAV, avoids damage to the wings during transportation, and extends the service life of the UAV wings.

[0030] A rotating block 7 is installed on the upper part of the first lifting rod 6. A sliding groove 17 is opened on the inner side wall of the mounting tube 5. A slider 24 that is slidably connected to the sliding groove 17 is installed on the first lifting plate 8. The mounting tube 5 is rotatably connected to the machine body 1. The mounting tube 5 is rotatably connected to the machine body 1 so that the first lifting rod 6 can be rotated by the rotating block 7. With the cooperation of the sliding groove 17 and the slider 24, the mounting tube 5 is driven to rotate the locking block 9, thereby storing the locking block 9 inside the machine body 1, avoiding damage to the locking block 9 during transportation and ensuring the service life of the equipment.

[0031] A rotating rod 12 is installed on the first lifting rod 6, and two sets of stop blocks 13 are installed on the machine body 1. The stop blocks 13 are used to limit the rotation angle of the rotating rod 12. By setting the stop blocks 13, the rotation angle of the rotating rod 12 and the first lifting rod 6 is limited, so that the first locking groove 10 on the locking block 9 at the lower part of the first lifting rod 6 can be connected with the locking block 11, thereby improving the installation efficiency of the equipment.

[0032] The end of the locking block 11 away from the body 1 is tapered. This tapered design facilitates the docking and installation of the locking block 11 with the first locking groove 10.

[0033] A pressing block 16 is installed on the upper part of the second lifting rod 22. The pressing block 16 facilitates the lifting of the second lifting rod 22 and improves the ease of operation.

[0034] The joints of the fuselage 1, fixed wing 2, mounting base 3, and multi-rotor mounting frame 4 are all hollow. This hollow design facilitates the connection of wiring and avoids unnecessary risks caused by exposed wiring.

[0035] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A quick-release connection assembly for a compound-wing unmanned aerial vehicle, comprising a fuselage (1) and a fixed wing (2) mounted on the fuselage (1), characterized in that: Mounting seats (3) are installed on both sides of the fixed wing (2), and a detachable multi-rotor mounting frame (4) is installed on the mounting seats (3); The inner top and bottom walls of the fuselage (1) are provided with slots (14), and the fixed wing (2) is provided with a plug (15) that matches the slot (14) on one side. The fuselage (1) is equipped with an installation tube (5), and a first lifting rod (6) is installed inside the installation tube (5). A first lifting plate (8) that is slidably connected to the installation tube (5) is installed in the middle of the first lifting rod (6). The first lifting plate (8) can be raised and lowered along the inner wall of the installation tube (5). A first spring (18) is installed between the bottom of the first lifting plate (8) and the inner bottom wall of the installation tube (5). The bottom of the first lifting rod (6) extends into the fuselage (1) and is equipped with a locking block (9). The inner top and bottom walls of the fixed wing (2) are equipped with locking blocks (11). A first locking groove (10) that matches the locking block (11) is provided on one side of the locking block (9). The mounting base (3) is provided with a mounting groove (21). A second lifting rod (22) is installed on the mounting base (3) through the mounting groove (21) and extending into the interior of the mounting base (3). A second lifting plate (19) is installed in the middle of the second lifting rod (22) and is slidably connected to the inner wall of the mounting groove (21). A second spring (20) is installed between the bottom wall of the second lifting plate (19) and the bottom wall of the mounting groove (21). One end of the multi-rotor mounting frame (4) extends into the mounting base (3) and is provided with a second locking groove (23). The bottom of the second lifting rod (22) is adapted to the second locking groove (23).

2. The quick-release connection assembly for a compound-wing unmanned aerial vehicle according to claim 1, characterized in that: A rotating block (7) is installed on the upper part of the first lifting rod (6), a sliding groove (17) is provided on the inner side wall of the mounting tube (5), a slider (24) is installed on the first lifting plate (8) and is slidably connected to the sliding groove (17), and the mounting tube (5) is rotatably connected to the machine body (1).

3. The quick-release connection assembly for a compound-wing unmanned aerial vehicle according to claim 2, characterized in that: A rotating rod (12) is installed on the first lifting rod (6), and two sets of stop blocks (13) are installed on the body (1). The stop blocks (13) are used to limit the rotating rod (12).

4. The quick-release connection assembly for a compound-wing unmanned aerial vehicle according to claim 1, characterized in that: The locking block (11) is tapered at the end away from the fuselage (1).

5. The quick-release connection assembly for a compound-wing unmanned aerial vehicle according to claim 1, characterized in that: A pressing block (16) is installed on the upper part of the second lifting rod (22).

6. The quick-release connection assembly for a compound-wing unmanned aerial vehicle according to claim 1, characterized in that: The joints of the fuselage (1), fixed wing (2), mounting base (3) and multi-rotor mounting frame (4) are all hollow.

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