A vertical take-off compound wing unmanned aerial vehicle

Abstract

This invention provides a vertical takeoff and landing (VTOL) compound wing unmanned aerial vehicle (UAV), comprising a fuselage, with wings on both sides of the middle section of the fuselage. Each wing includes a middle wing section and an outer wing section. One end of the middle wing section is connected to the fuselage, and the outer wing section is connected to the other end of the middle wing section. A foldable cantilever is mounted on the side of the middle wing section, and a central propeller is mounted at the end of the foldable cantilever. A tail fin and a tail propeller are located at the tail of the fuselage, and a vertical tail is located at the bottom of the fuselage. This invention offers the following advantages: the cantilever of the VTOL compound wing UAV features a multi-level self-locking connection, ensuring reliable locking and excellent anti-loosening performance. The self-locking connection mechanism integrates multiple locking structures such as hinges, self-locking nuts, self-locking rods, and locking arc plates. After deployment, it achieves mechanical self-locking, effectively resisting flight vibrations, strong wind loads, and maneuvering impacts, preventing loosening, and ensuring high safety.

Description

Technical Field

[0001] This invention is a vertical take-off and landing compound wing unmanned aerial vehicle (UAV), belonging to the field of UAV technology. Background Technology

[0002] To achieve good cruise efficiency, fixed-wing compound-wing UAVs typically have a large wingspan. This makes them extremely inconvenient to transport, store, and carry by individual soldiers. Folding the arms (especially multi-rotor arms for vertical takeoff and landing) and the main wing can significantly reduce packaging size, allowing them to be easily placed in a vehicle trunk or specialized backpack, greatly expanding the application scenarios of UAVs. However, the folding mechanism itself is a "joint," naturally becoming a weak point in structural rigidity. During flight, especially during vertical takeoff and landing and mode transitions, the arms bear enormous aerodynamic loads and vibrations. If the joint rigidity is insufficient, it can cause arm vibration, severely affecting flight control stability and flight efficiency.

[0003] In addition, fixed-wing drones deploy their wings to take off and perform missions. After the mission is completed, they return to the ground for storage and transport. Upon returning to the ground, the outer wing sections need to be disassembled first, followed by the middle wing sections. This process leaves the arms with considerable space, making storage inconvenient, and necessitates folding the arms.

[0004] Conventional folding mechanisms used in VTOL drones generate a significant yaw torque during startup. This torque acts directly on the arm carrying the motor and the folding mechanism connected to the fuselage, creating a strong torsional torque. Under the repeated action of this torsional torque, the locking nuts used to secure the motor or folding mechanism are prone to loosening. Once the nuts loosen, the folding structure may suddenly and unexpectedly open under external force or vibration, causing damage to the VTOL drone's propellers due to sudden changes in attitude. In severe cases, this could even lead to a mid-air crash, posing a significant safety hazard.

[0005] Therefore, a vertical take-off and landing compound wing UAV is needed to solve the above problems. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide a vertical take-off and landing (VTOL) compound wing unmanned aerial vehicle (UAV).

[0007] To achieve the above objectives, the present invention is implemented through the following technical solution: A vertical takeoff and landing (VTOL) compound wing unmanned aerial vehicle (UAV) includes a fuselage, with a wing on each side of the middle section of the fuselage. Each wing includes a middle wing section and an outer wing section. One end of the middle wing section is connected to the fuselage, and the outer wing section is connected to the other end of the middle wing section. A foldable cantilever is installed on the side of the middle wing section, and a central propeller is installed at the end of the foldable cantilever. A tail fin and a tail propeller are provided at the tail of the fuselage, and a vertical tail is provided at the bottom of the fuselage.

[0008] Furthermore, the foldable cantilever includes a fixed wing rod and a movable wing rod. One end of the fixed wing rod is fixedly connected to the middle wing section, and the other end of the middle wing section is connected to the movable wing rod through a self-locking connection mechanism. The middle propeller is installed at the end of the movable wing rod.

[0009] Furthermore, the self-locking connection mechanism includes a first wing rod connector, a second wing rod connector, and a self-locking nut. The first wing rod connector and the second wing rod connector are respectively fixed to the ends of the fixed wing rod and the movable wing rod. The first wing rod connector and the second wing rod connector are hinged together. The first wing rod connector is fitted with a self-locking nut. The second wing rod connector has a left-hand external thread at one end near the first wing rod connector. The self-locking nut is threadedly connected to the left-hand external thread.

[0010] Furthermore, docking seat 1 and docking seat 2 are respectively fixed at opposite ends of the wing rod connector 1 and the wing rod connector 2. The docking seat 1 and the docking seat 2 are pressed together. The docking seat 1 is provided with a number of positioning protrusions on the side near the docking seat 2. The docking seat 2 is provided with positioning grooves that are adapted to the positioning protrusions.

[0011] Furthermore, the self-locking connection mechanism also includes a fixing seat 1 and a fixing seat 2 fixed at the ends of the wing rod connector 1 and the wing rod connector 2, respectively. A self-locking rod 1 and a self-locking rod 2 are respectively hinged to opposite sides of the fixing seat 1 and the fixing seat 2. The self-locking rod 1 is engaged with the self-locking nut, and the self-locking rod 2 is engaged with the outside of the self-locking rod 1.

[0012] Furthermore, the inner side of the self-locking rod two is provided with a groove that matches the self-locking rod one, and the outer surface of the self-locking rod two is provided with a locking groove.

[0013] Furthermore, the self-locking nut is provided with a mating groove that is compatible with the self-locking rod.

[0014] Furthermore, the fixed base has a through hole, and a sliding rod passes through the through hole. One end of the sliding rod is fixed with a locking arc plate, and the end of the locking arc plate is engaged in the locking groove. The other end of the sliding rod is fixed to the outer surface of the fixed ring. The fixed ring slides on the outer surface of the fixed wing rod. The outer surface of the fixed ring has a left-hand threaded groove, and an external threaded ring is threaded into the left-hand threaded groove. The external threaded ring is fixed to the end of the internal threaded ring, and the internal threaded ring is threaded onto the left-hand external thread two. The left-hand external thread two is fixed on the fixed wing rod.

[0015] Furthermore, the sliding rod and the locking arc plate are an integral structure.

[0016] The beneficial effects of this invention are: The vertical take-off and landing compound wing UAV provided by this invention solves the technical problems of poor reliability of folding structures, inconvenient storage, low positioning accuracy, and cumbersome operation in the prior art.

[0017] The vertical take-off and landing compound wing UAV provided by this invention has a foldable cantilever for easy storage and carrying. The foldable cantilever is provided on the side of the middle section of the wing. The cantilever consists of a fixed wing rod and a movable wing rod. It can be rotated and folded around the hinge, which greatly reduces the lateral size of the whole aircraft and facilitates transportation, storage and rapid deployment in the field.

[0018] The cantilever of the vertical take-off and landing compound wing UAV provided by this invention achieves multi-level self-locking connection, which is reliable in locking and has a good anti-loosening effect. The self-locking connection mechanism integrates multiple locking structures such as hinges, self-locking nuts, self-locking rods, and locking arc plates. After unfolding, it can achieve mechanical self-locking, effectively resisting flight vibration, strong wind load and motor impact, avoiding loosening, and ensuring high safety.

[0019] The vertical take-off and landing compound wing UAV provided by this invention has precise cantilever positioning and quick installation. The docking seat one and docking seat two are precisely matched by positioning protrusions and positioning grooves to ensure the coaxiality and positioning accuracy of the cantilever after folding and unfolding, ensure the consistency of the installation position of the central propeller, and improve power efficiency and flight stability.

[0020] The vertical take-off compound wing UAV provided by this invention is easy to operate and can quickly unfold and retract. By rotating the inner and outer threaded rings, the sliding rod and locking arc plate can be driven to lock or unlock. No additional tools are required, and a single person can quickly complete the folding and unfolding, which greatly improves the work efficiency.

[0021] The vertical takeoff and landing (VTOL) composite wing UAV provided by this invention has high structural strength and good stability. The fuselage, wings and tail are integrated into one design. With the tail propeller and vertical tail, it can balance the stability of vertical takeoff and landing and hovering with the efficiency of fixed-wing cruise. It is suitable for complex environments and long-endurance operations.

[0022] The vertical takeoff and landing compound wing UAV provided by this invention has a compact structure and is easy to maintain. The modular design of each component makes it easy to disassemble and assemble, which facilitates later maintenance and parts replacement and reduces the cost of use. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1This is a schematic diagram of the overall structure of a vertical take-off compound wing unmanned aerial vehicle (UAV) according to the present invention; Figure 2 This is a schematic diagram of the connection structure between the mid-wing section and the foldable cantilever of a vertical take-off and landing compound wing UAV according to the present invention. Figure 3 This is a schematic diagram of a partial structure of a foldable cantilever of a vertical take-off compound wing UAV according to the present invention; Figure 4 This is a partial structural diagram of a self-locking connection mechanism for a vertical take-off and landing compound wing UAV according to the present invention. Figure 1 ; Figure 5 This is a partial structural diagram of a self-locking connection mechanism for a vertical take-off and landing compound wing UAV according to the present invention. Figure 2 ; Figure 6 This is a partial structural diagram of a self-locking connection mechanism for a vertical take-off and landing compound wing UAV according to the present invention. Figure 3 ; Figure 7 This is a partial structural diagram of a self-locking connection mechanism for a vertical take-off and landing compound wing UAV according to the present invention. Figure 4 ; Figure 8 This is a partial structural diagram of a self-locking connection mechanism for a vertical take-off and landing compound wing UAV according to the present invention. Figure 5 ; Figure 9 This is a partial structural diagram of a self-locking connection mechanism for a vertical take-off and landing compound wing UAV according to the present invention. Figure 6 ; Figure 10 This is a partial structural diagram of a self-locking connection mechanism for a vertical take-off and landing compound wing UAV according to the present invention. Figure 7 ; Figure 11 This is a partial structural diagram of a self-locking connection mechanism for a vertical take-off and landing compound wing UAV according to the present invention. Figure 8 ; Figure 12 This is a schematic diagram of the self-locking rod structure of a vertical take-off compound wing UAV according to the present invention.

[0025] In the diagram: 1. Fuselage; 2. Vertical tail; 3. Tail fin; 4. Tail propeller; 5. Wing; 6. Mid-wing section; 7. Outer wing section; 8. Foldable cantilever; 9. Mid-propeller; 10. Fixed wingstock; 11. Movable wingstock; 12. Self-locking connection mechanism; 13. Wingstock connector one; 14. Wingstock connector two; 15. Self-locking nut; 16. Hinge; 17. Left-hand external thread one; 18. Dating seat one; 19. Dating seat two; 20. Positioning protrusion; 21. Positioning groove; 22. Fixed seat one; 23. Fixed seat two; 24. Self-locking rod one; 25. Self-locking rod two; 26. Dating groove; 27. Groove; 28. Locking groove; 29. ​​Perforation; 30. Sliding rod; 31. Locking arc plate; 32. Fixed ring; 33. Left-hand threaded groove; 34. Internal threaded ring; 35. External threaded ring. Detailed Implementation

[0026] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] Please see Figures 1-12 This invention provides a vertical takeoff and landing (VTOL) compound wing unmanned aerial vehicle (UAV) technical solution, including a fuselage 1. A wing 5 is provided on each side of the middle portion of the fuselage 1. Each wing 5 includes a middle wing section 6 and an outer wing section 7. One end of the middle wing section 6 is connected to the fuselage 1, and the outer wing section 7 is connected to the other end of the middle wing section 6. A foldable cantilever 8 is installed on the side of the middle wing section 6, and a central propeller 9 is installed at the end of the foldable cantilever 8. A tail fin 3 and a tail propeller 4 are provided at the tail of the fuselage 1. A vertical tail 2 is provided at the bottom of the fuselage 1. The foldable cantilever 8 includes a fixed wing rod 10 and a movable wing rod 11. One end of the fixed wing rod 10 is fixedly connected to the middle wing section 6, and the other end of the middle wing section 6 is connected to the movable wing rod 11 through a self-locking connection mechanism 12. The central propeller 9 is installed at the end of the movable wing rod 11.

[0028] See Figures 4-5The self-locking connection mechanism 12 includes a first wing rod connector 13, a second wing rod connector 14, and a self-locking nut 15. The first wing rod connector 13 and the second wing rod connector 14 are respectively fixed to the ends of the fixed wing rod 10 and the movable wing rod 11. The first wing rod connector 13 and the second wing rod connector 14 are hinged together by a hinge 16. The first wing rod connector 13 is fitted with a self-locking nut 15. The second wing rod connector 14 has a left-hand external thread 17 at one end near the first wing rod connector 13. The self-locking nut 15 is threadedly connected to the left-hand external thread 17. Through the design of the self-locking nut 15 and the left-hand external thread 17, when the central propeller 9 starts and the motor generates a clockwise deflection torque, the left-hand thread and the nut have a self-locking tendency under the relative motion trend, which can effectively prevent the nut from loosening due to vibration or torque, and significantly improve the locking reliability.

[0029] See Figure 6 The first wing rod connector 13 and the second wing rod connector 14 are respectively fixed with docking seats 18 and 19 at opposite ends. The first docking seat 18 and the second docking seat 19 are pressed together. The first docking seat 18 is provided with a number of positioning protrusions 20 on the side near the second docking seat 19. The second docking seat 19 is provided with positioning grooves 21 that are adapted to the positioning protrusions 20. Through the design of the positioning protrusions 20 and the positioning grooves 21, while achieving rapid docking and improving docking accuracy, when the central propeller 9 is started and the motor generates deflection torque, the positioning grooves 21 can form circumferential rigid abutment with the corresponding positioning protrusions 20, thereby effectively weakening or offsetting the torsional effect of the deflection torque on the folding structure and avoiding the torque from being directly transmitted to the locking component.

[0030] See Figures 7-12The self-locking connection mechanism 12 further includes a fixing seat 22 and a fixing seat 23 fixed to the ends of the first wing rod connector 13 and the second wing rod connector 14. A self-locking rod 24 and a self-locking rod 25 are respectively hinged to opposite sides of the fixing seat 22 and the fixing seat 23. The self-locking rod 24 is engaged with the self-locking nut 15, and the self-locking rod 25 is engaged with the outer side of the self-locking rod 24. A groove 27 adapted to the self-locking rod 24 is provided on the inner side of the self-locking rod 25. The surface has a locking groove 28, and the self-locking nut 15 has a mating groove 26 that matches the self-locking rod 24. The fixing base 22 has a through hole 29, and a sliding rod 30 passes through the through hole 29. One end of the sliding rod 30 is fixed with a locking arc plate 31. The sliding rod 30 and the locking arc plate 31 are an integral structure. The end of the locking arc plate 31 is engaged in the locking groove 28. The other end of the sliding rod 30 is fixed to the outer surface of the fixing ring 32, and the fixing ring 32 slides on the fixing wing. On the outer surface of the rod 10, the outer surface of the fixing ring 32 is provided with a left-hand threaded groove 33. An external threaded ring 35 is internally threaded into the left-hand threaded groove 33. The external threaded ring 35 is fixed to the end of the internal threaded ring 34. The internal threaded ring 34 is threaded onto the left-hand external thread 2, which is fixed to the fixed wing rod 10. After the self-locking nut 15 is screwed and fixed to the left-hand external thread 17, and the wing rod connector 13 and wing rod connector 2 14 are connected as a whole, the self-locking rod 24 can be rotated and engaged sequentially. The self-locking nut 15 is inserted into the mating groove 26 on its outer surface. The self-locking rod 25 is then rotated and snapped onto the outside of the self-locking rod 24. Next, the fixing ring 32 is pushed axially so that the sliding rod 30 can push the locking arc plate 31 along the wing rod connector 13 and snap it into the locking groove 28 on the outer surface of the two adjacent self-locking rods 25, thereby locking and fixing the self-locking rod 25 and improving the locking effect. At the same time, the external threaded ring 35 is screwed into the left-hand threaded groove 33 on the outer surface of the fixing ring 32 by rotating the internal threaded ring 34 to the left again, further improving the locking connection effect.

[0031] The heat dissipation holes and maintenance doors in the space of circuits and electronic components, modules and controllers or adapted electrical equipment are all existing technologies that can be fully implemented by those skilled in the art, and need not be elaborated upon. The content protected by this application does not involve improvements to software and methods or heat dissipation and maintenance.

[0032] When in use, after the drone completes its operation, the foldable cantilever 8 needs to be retracted to reduce the overall size of the drone. Rotating the inner threaded ring 34 and the outer threaded ring 35 drives the fixed ring 32 to move axially along the fixed wing rod 10, causing the sliding rod 30 and the locking arc plate 31 to disengage from the locking groove 28 on the side of the self-locking rod 25, thus releasing the lock. Next, the self-locking nut 15 is rotated in the opposite direction, causing the self-locking nut 15 to retract along the left-hand external thread 17, loosening the connection between the wing rod connector 13 and the wing rod connector 2 14. Then, the movable wing rod 11 rotates inward around the hinge 16 and folds, causing the central propeller 9 to approach the middle wing section 6, completing the cantilever folding. After folding, the overall lateral size of the drone is significantly reduced, making it easier to transport and store.

[0033] Although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A vertical take-off and landing compound wing unmanned aerial vehicle, characterized in that, The fuselage (1) includes a fuselage (1), and a wing (5) is provided on each side of the middle part of the fuselage (1). The wing (5) includes a middle wing section (6) and an outer wing section (7). One end of the middle wing section (6) is connected to the fuselage (1), and the outer wing section (7) is connected to the other end of the middle wing section (6). A foldable cantilever (8) is installed on the side of the middle wing section (6), and a central propeller (9) is installed at the end of the foldable cantilever (8). The tail of the fuselage (1) is provided with a tail fin (3) and a tail propeller (4), and the bottom of the fuselage (1) is provided with an aircraft vertical tail (2).

2. The vertical take-off and landing compound wing UAV according to claim 1, characterized in that, The foldable cantilever (8) includes a fixed wing rod (10) and a movable wing rod (11). One end of the fixed wing rod (10) is fixedly connected to the middle wing section (6), and the other end of the middle wing section (6) is connected to the movable wing rod (11) through a self-locking connection mechanism (12). The middle propeller (9) is installed at the end of the movable wing rod (11).

3. The vertical take-off and landing compound wing UAV according to claim 2, characterized in that, The self-locking connection mechanism (12) includes a first wing rod connector (13), a second wing rod connector (14), and a self-locking nut (15). The first wing rod connector (13) and the second wing rod connector (14) are respectively fixed to the ends of the fixed wing rod (10) and the movable wing rod (11). The first wing rod connector (13) and the second wing rod connector (14) are hinged together by a hinge (16). The first wing rod connector (13) is fitted with a self-locking nut (15). The second wing rod connector (14) has a left-hand external thread (17) at one end near the first wing rod connector (13). The self-locking nut (15) is threadedly connected to the left-hand external thread (17).

4. A vertical take-off and landing compound wing UAV according to claim 3, characterized in that, The first wing rod connector (13) and the second wing rod connector (14) are respectively fixed with a first docking seat (18) and a second docking seat (19) at opposite ends. The first docking seat (18) and the second docking seat (19) are pressed together. The first docking seat (18) has several positioning protrusions (20) on the side near the second docking seat (19). The second docking seat (19) has a positioning groove (21) that matches the positioning protrusions (20).

5. A vertical take-off and landing compound wing UAV according to claim 4, characterized in that, The self-locking connection mechanism (12) further includes a fixing seat (22) and a fixing seat (23) fixed at the ends of the first wing rod connector (13) and the second wing rod connector (14). The first fixing seat (22) and the second fixing seat (23) are respectively hinged to a self-locking rod (24) and a self-locking rod (25) on opposite sides. The first self-locking rod (24) is engaged with the self-locking nut (15), and the second self-locking rod (25) is engaged with the outside of the first self-locking rod (24).

6. A vertical take-off and landing compound wing UAV according to claim 5, characterized in that, The inner side of the self-locking rod 2 (25) is provided with a groove (27) that is compatible with the self-locking rod 1 (24), and the outer surface of the self-locking rod 2 (25) is provided with a locking groove (28).

7. A vertical take-off and landing compound wing UAV according to claim 6, characterized in that, The self-locking nut (15) has a mating groove (26) that is compatible with the self-locking rod (24).

8. A vertical take-off and landing compound wing UAV according to claim 7, characterized in that, The fixed base (22) has a through hole (29), and a sliding rod (30) is inserted through the through hole (29). One end of the sliding rod (30) is fixed with a locking arc plate (31), and the end of the locking arc plate (31) is engaged in the locking groove (28). The other end of the sliding rod (30) is fixed to the outer surface of the fixed ring (32). The fixed ring (32) slides on the outer surface of the fixed wing rod (10). The outer surface of the fixed ring (32) has a left-hand threaded groove (33). The left-hand threaded groove (33) is internally threaded with an external threaded ring (35). The external threaded ring (35) is fixed to the end of the internal threaded ring (34). The internal threaded ring (34) is threaded on the left-hand external thread two. The left-hand external thread two is fixed on the fixed wing rod (10).

9. A vertical take-off and landing compound wing UAV according to claim 8, characterized in that, The sliding rod (30) and the locking arc plate (31) are an integral structure.

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