Vertical take-off and landing fixed-wing unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing fixed-wing unmanned aerial vehicle which comprises a vehicle body, an empennage detachably arranged at the top of the vehicle body, wings arranged on the two sides of the vehicle body, power arms detachably arranged at the bottoms of the wings, and vertical motors and speed regulators arranged on the power arms. Vertical paddles are fixed to the output end of the vertical motor, a pod is clamped to the bottom of the fuselage, an upper cabin cover is arranged at the position, corresponding to the pod, of the top end of the fuselage in an opening and closing mode, at least two electric drive top blocks are arranged on the inner wall of the bottom of the fuselage, an abdomen load cabin is clamped between the electric drive top blocks, and a tail thrust power module is arranged at one end of the fuselage. The power arm and the empennage are detachably arranged in an indoor scene and other easy-to-control scenes, the empennage is selectively disassembled to reduce the weight, the power arm and the empennage are independently stored after being disassembled and are easy to store, and the abdomen load cabin can quickly replace a load and can be replaced by a power battery according to requirements, so that the load capacity and the battery capacity are adjusted.

Description

Technical Field

[0001] This utility model mainly relates to the field of unmanned aerial vehicle (UAV) technology, specifically a vertical take-off and landing (VTOL) fixed-wing UAV. Background Technology

[0002] Vertical take-off and landing (VTOL) fixed-wing unmanned aerial vehicles (UAVs) are aircraft that can perform vertical take-off, landing, and translational propulsion without a pilot, and they have broad application prospects in the civilian sector. They can be used in fields such as environmental protection, meteorological monitoring, geological exploration, and emergency rescue. For example, by carrying various sensors and equipment, VTOL fixed-wing UAVs can perform tasks such as air quality monitoring, meteorological data collection, and emergency rescue for earthquakes and geological disasters. VTOL fixed-wing UAVs can also be used in the logistics and transportation sectors.

[0003] Vertical take-off and landing (VTOL) fixed-wing drones possess the capability for vertical take-off and landing and employ a fixed-wing design to improve flight efficiency and stability. However, to achieve VTOL functionality and adapt to complex outdoor scenarios, existing technologies often incorporate fixed VTOL motors and tail fins. This increases the drone's weight and drag, while also resulting in low space utilization. Furthermore, to prevent excessive weight, the drone's payload capacity and battery capacity are opposite and fixed in size, making them unadjustable for various application scenarios and hindering ease of use. Utility Model Content

[0004] The purpose of this invention is to provide a vertical take-off and landing fixed-wing unmanned aerial vehicle (UAV) to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a vertical take-off and landing fixed-wing unmanned aerial vehicle (UAV), comprising a fuselage, a tail fin detachably mounted on the top of the fuselage, wings mounted on both sides of the fuselage, a power arm detachably mounted on the bottom of the wings, a vertical take-off motor and a speed controller mounted on the power arm, a vertical take-off blade fixed to the output end of the vertical take-off motor, a pod mounted on the bottom of the fuselage, an upper hatch mounted on the top of the fuselage at a position corresponding to the pod, at least two electric drive top blocks mounted on the bottom inner wall of the fuselage, an abdominal payload compartment mounted between the electric drive top blocks, and a tail thrust module mounted at one end of the fuselage.

[0006] Preferably, a first limiting protrusion is formed at the bottom of the wing, and a first limiting groove is formed on the power arm that fits with the first limiting protrusion. The bottom of the wing is provided with a plurality of first buckles, the number of which is even and they are symmetrically distributed about the first limiting protrusion as the axis of symmetry. A first locking slot is formed on the power arm that fits with the first buckles. The first limiting protrusion and the first limiting groove work together to restrict the power arm from detaching from the wing in the horizontal direction, and the first buckles and the first locking slot work together to restrict the power arm from detaching from the wing in the vertical direction, thus providing bidirectional reinforcement for the installation of the power arm.

[0007] Preferably, a second limiting protrusion is formed at the bottom of the tail fin, and a second limiting groove is formed on the fuselage to fit the second limiting protrusion. A plurality of second buckles are flipped at the bottom of the tail fin. The number of the second buckles is even and they are symmetrically distributed with the second limiting protrusion as the axis of symmetry. A second latch is formed on the fuselage to fit the second buckles. The second limiting protrusion and the second limiting groove work together to restrict the tail fin from detaching from the fuselage in the horizontal direction, and the second buckles and the second latch work together to restrict the tail fin from detaching from the fuselage in the vertical direction, thereby providing bidirectional reinforcement for the installation of the tail fin.

[0008] Preferably, two connecting carbon tubes are inserted between the two wings, and the connecting carbon tubes penetrate the fuselage to connect and reinforce the two wings to the fuselage.

[0009] Preferably, an installation cavity is fixedly provided inside the fuselage, and the number of installation cavities is the same as that of the electric drive top blocks. The electric drive top blocks are movably inserted into one side of the outer wall of the installation cavity. A spring is provided between the installation cavity and the electric drive top blocks. A push-pull motor is fixedly provided on the outer wall of the installation cavity on the side opposite to the electric drive top blocks. The output end of the push-pull motor is inserted into the installation cavity and fixedly connected to the electric drive top blocks. The bottom end of the outer wall of the electric drive top blocks is arc-shaped. A slot is formed on the outer wall of the abdominal load compartment that fits with the electric drive top blocks. The electric drive top blocks are self-locked and fixed by the spring after the abdominal load compartment is inserted to the position where the electric drive top blocks are aligned with the slot. The push-pull motor controls the electric drive top blocks to retract and unlock, thereby allowing the abdominal load compartment to be disassembled and assembled.

[0010] Preferably, the fuselage is equipped with a vertical lift battery and a driving battery. The vertical lift battery is electrically connected to the vertical lift motor, and the driving battery is electrically connected to the tail thrust module. The driving battery has a parallel line that extends into the belly load compartment. By using two types of batteries, the vertical lift motor and the tail thrust module are supplied with power separately, so as to avoid the vertical lift motor's insufficient kinetic energy or the tail thrust module's excessive power consumption due to inconsistent voltage requirements between the two.

[0011] Preferably, an airspeed tube is provided at one end of the tail thrust module of the fuselage to measure the flight speed of the UAV.

[0012] Preferably, two RTK antennas are provided on the top outer wall of the fuselage, and a GPS antenna is provided between the RTK antennas, so that the UAV can be located by the cooperation of the RTK antennas and the GPS antenna.

[0013] Preferably, a tripod is fixed to the bottom of the fuselage near the pod, which supports the fuselage and prevents the pod from directly contacting the ground.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] This utility model provides a vertical take-off and landing fixed-wing drone, which can be disassembled and fixed horizontally by limiting protrusions and limiting grooves on the power arm and tail fin, and disassembled and fixed vertically by buckles and buckles. In indoor or other easily controllable scenarios with less interference, the tail fin can be selectively disassembled to reduce weight and improve the drone's endurance. After the power arm and tail fin are disassembled, they can be stored independently with high space utilization and easy to store.

[0016] This utility model provides a vertical take-off and landing fixed-wing UAV. After the electric drive top block is inserted into the belly payload compartment and aligned with the slot by a spring, the electric drive top block is self-locked and fixed. A push-pull motor controls the electric drive top block to retract and unlock, thereby allowing the belly payload compartment to be disassembled and assembled for quick payload replacement. It can also be replaced with a power battery as needed. The driving battery has a parallel circuit that extends into the belly payload compartment to connect to the power battery, so as to adjust the payload capacity and battery capacity of the UAV. It is easy to use.

[0017] The present invention will be explained in detail below with reference to the accompanying drawings and specific embodiments. Attached Figure Description

[0018] The accompanying drawings are only used to illustrate the principles, implementation methods, applications, features, and effects of the present invention and other related contents, and should not be considered as limitations on the present invention.

[0019] In the accompanying drawings of the instruction manual:

[0020] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0021] Figure 2 This is a side sectional view of the overall structure of this utility model;

[0022] Figure 3 This is a schematic diagram of the electric drive top block drive structure of this utility model;

[0023] Figure 4 This is a schematic diagram of the wing bottom structure of this utility model;

[0024] Figure 5 This is a partial structural diagram of the connection between the wing and the power arm of this utility model;

[0025] Figure 6 This is a partial structural diagram of the connection between the tail fin and the fuselage of this utility model;

[0026] Figure label:

[0027] 1. Fuselage; 2. Wing; 3. Power arm; 4. Vertical lift blade; 5. Pod; 6. Landing gear; 7. Pitot tube; 8. RTK antenna; 9. GPS antenna; 10. Upper hatch; 11. Driving battery; 12. Connecting carbon fiber tube; 13. Belly payload bay; 14. Electric drive top block; 15. Tail fin; 16. Tail thrust module; 17. Mounting cavity; 18. Push-pull motor; 19. Spring; 20. Vertical lift motor; 21. Speed ​​controller; 22. First latch; 23. First latch; 24. First limiting groove; 25. First limiting protrusion; 26. Second limiting groove; 27. Second limiting protrusion; 28. Second latch; 29. ​​Second latch; 30. Vertical lift battery. Detailed Implementation

[0028] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this utility model, and should not be construed as limiting this utility model.

[0029] The technical solution of this utility model will be further described below with reference to the accompanying drawings and specific embodiments.

[0030] like Figures 1 to 6 As shown, a vertical takeoff and landing fixed-wing unmanned aerial vehicle (UAV) includes a fuselage 1, a tail fin 15 detachably mounted on the top of the fuselage 1, wings 2 mounted on both sides of the fuselage 1, and power arms 3 detachably mounted on the bottom of the wings 2. A vertical takeoff motor 20 and a speed controller 21 are mounted on the power arms 3. A vertical takeoff blade 4 is fixed to the output end of the vertical takeoff motor 20. A pod 5 is mounted on the bottom of the fuselage 1. An upper hatch 10 is mounted on the top of the fuselage 1 at a position corresponding to the pod 5. Two electric drive top blocks 14 are mounted on the inner bottom wall of the fuselage 1, and a belly payload bay 13 is mounted between the electric drive top blocks 14. A tail thrust module 16 is mounted on one end of the fuselage 1.

[0031] like Figure 4 and Figure 5As shown, the power arm 3 is located at 25% of the mid-span of the wing 2 and is arc-shaped when viewed from the side. A first limiting protrusion 25 is formed at the bottom of the wing 2, and a first limiting groove 24 is formed on the power arm 3 to fit the first limiting protrusion 25. Four first buckles 22 are flipped on the bottom of the wing 2. The first buckles 22 are symmetrically distributed about the first limiting protrusion 25. A first latch 23 is formed on the power arm 3 to fit the first buckles 22. The first limiting protrusion 25 and the first limiting groove 24 work together to restrict the power arm 3 from detaching from the wing 2 in the horizontal direction, and the first buckles 22 and the first latch 23 work together to restrict the power arm 3 from detaching from the wing 2 in the vertical direction, thus providing bidirectional reinforcement for the installation of the power arm 3.

[0032] like Figure 1 and Figure 6 As shown, the tail fin 15 forms a 10-degree angle with the horizontal plane of the fuselage 1 and sweeps backward. An elevator surface is arranged on each side. A second limiting protrusion 27 is formed at the bottom of the tail fin 15. A second limiting groove 26 is formed on the fuselage 1 to fit the second limiting protrusion 27. Four second buckles 28 are flipped at the bottom of the tail fin 15. The second buckles 28 are symmetrically distributed with the second limiting protrusion 27 as the axis of symmetry. A second latch 29 is formed on the fuselage 1 to fit the second buckles 28. The second limiting protrusion 27 and the second limiting groove 26 work together to restrict the tail fin 15 from detaching from the fuselage 1 in the horizontal direction. The second buckles 28 and the second latch 29 work together to restrict the tail fin 15 from detaching from the fuselage 1 in the vertical direction, thus providing bidirectional reinforcement for the installation of the tail fin 15.

[0033] like Figure 1 and Figure 4 As shown, the wings 2 are fixed to the fuselage 1 by bolts, and two connecting carbon tubes 12 are inserted between the two wings 2. The connecting carbon tubes 12 penetrate the fuselage 1 and reinforce the connection between the two wings 2 and the fuselage 1.

[0034] like Figure 2 and Figure 3As shown, a mounting cavity 17 is fixedly provided inside the fuselage 1. The number of mounting cavities 17 is the same as that of the electric drive top block 14. The electric drive top block 14 is movably inserted into the right outer wall of the mounting cavity 17. A spring 19 is provided between the mounting cavity 17 and the electric drive top block 14. A push-pull motor 18 is fixedly provided on the left outer wall of the mounting cavity 17. The output end of the push-pull motor 18 is inserted into the mounting cavity 17 and fixedly connected to the electric drive top block 14. The bottom end of the outer wall of the electric drive top block 14 is arc-shaped. A slot is formed on the outer wall of the abdominal load compartment 13 to fit the electric drive top block 14. After the abdominal load compartment 13 is inserted to the position where the electric drive top block 14 is aligned with the slot, the spring 19 self-locks the electric drive top block 14. The push-pull motor 18 controls the electric drive top block 14 to retract and unlock, thereby allowing the abdominal load compartment 13 to be disassembled and assembled.

[0035] like Figure 2 As shown, the fuselage 1 is equipped with a vertical lift battery 30 and a driving battery 11. The capacity of the driving battery 11 is greater than that of the vertical lift battery 30. The vertical lift battery 30 is electrically connected to the vertical lift motor 20, and the driving battery 11 is electrically connected to the tail thrust module 16. The driving battery 11 has a parallel line that extends into the belly load compartment 13. The two types of batteries provide power to the vertical lift motor 20 and the tail thrust module 16 separately. The voltage required by the vertical lift motor 20 is greater than that required by the tail thrust module 16. This avoids the vertical lift motor 20 having too low a voltage and insufficient kinetic energy, or the tail thrust module 16 having too high a voltage and excessive power consumption, due to the inconsistency in their voltage requirements.

[0036] like Figure 1 As shown, a pitot tube 7 is provided at one end of the tail thrust module 16 on the left side of the fuselage 1. The pitot tube 7 is a dynamic and static pressure pitot tube used to measure the flight speed of the UAV.

[0037] like Figure 1 As shown, two RTK antennas 8 are provided on the top outer wall of the fuselage 1, and a GPS antenna 9 is provided between the RTK antennas 8. The RTK antennas 8 and the GPS antenna 9 work together to locate the UAV.

[0038] like Figure 1 As shown, a tripod 6 is fixed on the bottom left side of the fuselage 1 near the pod 5. The tripod 6 is bow-shaped and has good overall bending and stress resistance when in contact with the ground. It is installed on the fuselage 1 and forms a three-point support with the tail of the fuselage 1. The tripod 6 supports the fuselage 1 to prevent the pod 5 from directly contacting the ground.

[0039] The implementation principle of this application embodiment is as follows: When this product is stored, the first buckle 22 is rotated to disengage it from the first latch 23, thereby causing the power arms 3 on both sides to move downward in the vertical direction and be disassembled from the fuselage 1. The bolts between the fuselage 1 and the wings 2 are removed to separate the wings 2 from the fuselage 1 and the connecting carbon tube 12 is pulled out. The second buckle 28 is rotated to disengage it from the second latch 29, thereby causing the tail fin 15 to move upward in the vertical direction and be disassembled from the fuselage 1. Thus, the fuselage 1, wings 2, power arms 3 and tail fin 15 can be stored independently, resulting in high space utilization during storage.

[0040] When using this product, the tail fin 15 can be selectively installed or removed depending on the application scenario. The vertical lift battery 30 supplies power to the vertical lift motor 20, and the driving battery 11 supplies power to the tail thrust module 16, ensuring that the vertical lift motor 20 and the tail thrust module 16 are at the optimal voltage. After the spring 19 is inserted into the abdominal payload compartment 13 and aligned with the slot, the electric drive top block 14 is self-locked. The push-pull motor 18 controls the electric drive top block 14 to retract and unlock, thereby allowing the abdominal payload compartment 13 to be installed or removed for quick payload replacement. The parallel circuit of the driving battery 11 extends into the abdominal payload compartment 13. Power batteries, testing equipment, cargo, etc., can be installed in the abdominal payload compartment 13 according to usage requirements to adjust the payload capacity and battery capacity of the drone. It is easy to use.

[0041] It will be apparent to those skilled in the art that this application is not limited to the details of the exemplary embodiments described above, and that this application can be implemented in other specific forms without departing from its essential characteristics. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of this application is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within this application. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. A vertical takeoff and landing fixed-wing unmanned aerial vehicle, comprising a fuselage (1), characterized in that: The fuselage (1) is detachably equipped with a tail fin (15) on its top. The fuselage (1) is equipped with wings (2) on both sides. The wings (2) are detachably equipped with power arms (3) at their bottom. The power arms (3) are equipped with a vertical lift motor (20) and a speed controller (21). The output end of the vertical lift motor (20) is fixed with a vertical lift blade (4). The fuselage (1) is equipped with a pod (5) at its bottom. The fuselage (1) is equipped with an upper hatch (10) at its top corresponding to the pod (5). The fuselage (1) is equipped with at least two electric drive top blocks (14) on its bottom inner wall. The electric drive top blocks (14) are equipped with a belly load compartment (13). The fuselage (1) is equipped with a tail thrust module (16) at one end. The bottom of the wing (2) forms a first limiting protrusion (25), and the power arm (3) forms a first limiting groove (24) that fits with the first limiting protrusion (25). The bottom of the wing (2) is provided with a plurality of first buckles (22). The number of the first buckles (22) is even and they are symmetrically distributed with the first limiting protrusion (25) as the axis of symmetry. The power arm (3) forms a first latch (23) that fits with the first buckles (22). The bottom of the tail fin (15) forms a second limiting protrusion (27), and the fuselage (1) forms a second limiting groove (26) that fits the second limiting protrusion (27). The bottom of the tail fin (15) is provided with a plurality of second buckles (28). The number of the second buckles (28) is even and they are symmetrically distributed with the second limiting protrusion (27) as the axis of symmetry. The fuselage (1) forms a second latch (29) that fits the second buckles (28). The fuselage (1) is fixedly provided with an installation cavity (17), the number of which is the same as that of the electric drive top block (14). The electric drive top block (14) is movably inserted into one side of the outer wall of the installation cavity (17). A spring (19) is provided between the installation cavity (17) and the electric drive top block (14). A push-pull motor (18) is fixedly provided on the outer wall of the installation cavity (17) away from the electric drive top block (14). The output end of the push-pull motor (18) is inserted into the installation cavity (17) and fixedly connected to the electric drive top block (14). The bottom end of the outer wall of the electric drive top block (14) is arc-shaped. A slot that fits the electric drive top block (14) is formed on the outer wall of the abdominal load compartment (13). The fuselage (1) is equipped with a vertical lift battery (30) and a driving battery (11). The vertical lift battery (30) is electrically connected to the vertical lift motor (20), and the driving battery (11) is electrically connected to the tail thrust module (16). The driving battery (11) has a parallel line that extends into the belly load compartment (13).

2. The vertical takeoff and landing fixed-wing unmanned aerial vehicle according to claim 1, characterized in that: Two connecting carbon tubes (12) are inserted between the two wings (2), and the connecting carbon tubes (12) penetrate the fuselage (1).

3. A vertical takeoff and landing fixed-wing unmanned aerial vehicle according to claim 1, characterized in that: A pitot tube (7) is provided at one end of the tail thrust module (16) of the fuselage (1).

4. A vertical takeoff and landing fixed-wing unmanned aerial vehicle according to claim 1, characterized in that: Two RTK antennas (8) are provided on the top outer wall of the fuselage (1), and a GPS antenna (9) is provided between the RTK antennas (8).

5. A vertical takeoff and landing fixed-wing unmanned aerial vehicle according to claim 1, characterized in that: A tripod (6) is fixed to the bottom of the fuselage (1) near the pod (5).

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