Unmanned aerial vehicle

Abstract

The invention relates to an unmanned aerial vehicle which comprises a vehicle body, a fixed wing, a rotary wing, a framework and a rotary wing connecting mechanism, the framework, the vehicle body and the fixed wing are detachably connected, and the rotary wing connecting mechanism is movably arranged on the fixed wing. Compared with the prior art, due to the adoption of a detachable connection design, when the unmanned aerial vehicle is in a non-working state or needs to be stored, the transversely arranged internal framework can be integrally drawn out from the vehicle body and the fixed wings and is compactly placed in the front-back direction of the vehicle body of the unmanned aerial vehicle, so that the situation that the framework occupies too much space in the transverse direction is effectively avoided; the fixed wings can also be arranged in the front-back direction of the fuselage after being detached, at the moment, the rotor wing connecting mechanisms can be movably adjusted, the postures of the rotor wing connecting mechanisms and the rotor wings are placed in the front-back direction of the fuselage, space occupation of the rotor wing connecting mechanisms and the rotor wings in the transverse or height direction is remarkably reduced, and the storage and transportation efficiency of the whole unmanned aerial vehicle is improved.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV. Background Technology

[0002] The low-altitude economy utilizes airspace below 1,000 meters as its resource, aiming to build a complete industrial chain integrating aircraft research and development, manufacturing, market operation, comprehensive support, and extended services.

[0003] Unmanned aerial vehicles (UAVs) are a core element of the national low-altitude economy. As the main carrier of low-altitude flight activities, they are a key force driving the vigorous development of this emerging economic form. With their significant advantages such as low cost, wide range of applications, and high transportation efficiency, UAVs have become a link connecting various stages. From agricultural and forestry plant protection and power line inspection to logistics distribution, emergency rescue, and now to the exploration of urban air traffic, UAVs are continuously expanding their application scenarios, transforming the potential value of low-altitude airspace into tangible economic and social benefits. They are the cornerstone for the low-altitude economy to move from concept to large-scale, routine operation.

[0004] With the rapid development of the low-altitude economy, the number of drones has exploded, and the challenges of storage and transportation have become increasingly prominent.

[0005] In related technologies, traditional fixed-wing or conventional multi-rotor drones occupy a significant amount of physical space when idle or during transport. When a large number of drones need to be deployed centrally, such as in logistics distribution centers, large-scale agricultural operations, or cross-regional dispatching, this space occupation problem is amplified, not only increasing warehousing costs but also posing a huge challenge to the space utilization of transport vehicles.

[0006] Therefore, it is necessary to develop a new type of drone to improve the aforementioned problems in related technologies. Summary of the Invention

[0007] The purpose of this invention is to provide a drone that can reduce space occupation when the drone is not in operation.

[0008] The objective of this invention can be achieved through the following technical solutions:

[0009] The drone provided by this invention includes:

[0010] Airframe, fixed wing, rotary wing, frame, and rotor connection mechanism;

[0011] The frame extends through the fuselage and into the fixed wing;

[0012] The frame, the fuselage, and the fixed wing are detachably connected.

[0013] The rotating wing is mounted on the rotor connecting mechanism, and the rotor connecting mechanism is movably mounted on the fixed wing.

[0014] Furthermore, the rotor connection mechanism includes a fixed part and a rotating part, the fixed part is glued to the fixed wing, the rotating part is rotatably connected to the fixed part, and the rotating wing is disposed on the rotating part.

[0015] Furthermore, the rotating part and the fixed part are hinged together, and the rotating part swings in the plane where the fixed wing is located.

[0016] Furthermore, the fixing part is located in the plane where the fixing wing is located.

[0017] Furthermore, the rotating part and the fixed part are hinged together, and the swinging posture of the rotating part includes at least the extension direction of the rotating part being the same as the extension direction of the fixed wing.

[0018] Furthermore, the extension direction of the fixed part is perpendicular to the extension direction of the fixed wing; the rotating part swings between a first extreme position and a second extreme position, the rotating part pointing forward or backward of the UAV when it is in the first extreme position, and pointing towards the wingtip of the fixed wing when it is in the second extreme position.

[0019] Furthermore, at least two rotor connection mechanisms are disposed on the front and rear sides of the fixed wing, and the movement trajectories of the rotor connection mechanisms are mirror-symmetrical.

[0020] Furthermore, the tail section of the fuselage is provided with a tail fin and a rear landing gear, the rear landing gear extending downward perpendicular to the plane of the fixed wing, and the tail fin is detachably connected to the fuselage.

[0021] Furthermore, the tail fin is a V-shaped tail fin.

[0022] Furthermore, the rotating part and the fixed part are fixed together by a quick-release buckle.

[0023] Compared with the prior art, the drone provided by the present invention has the following beneficial effects:

[0024] 1. This invention provides a drone, comprising: a fuselage, fixed wings, rotary wings, a frame, and a rotor connection mechanism. The frame extends laterally through the entire fuselage structure, with both ends extending into the interior of the fixed wings on both sides. The frame, fuselage, and fixed wings are detachably connected. The rotary wing unit is mounted on the rotor connection mechanism, which is movably mounted on the fixed wings, allowing for attitude adjustment during storage or transportation. Due to the detachable connection design, when the drone is not in operation or needs to be stored, the laterally arranged internal frame can be completely extracted from the fuselage and fixed wings and compactly arranged along the front-rear direction of the drone fuselage, effectively avoiding excessive space occupation by the frame laterally. After disassembly, the fixed wings can also be arranged along the front-rear direction of the fuselage. In this case, the rotor connection mechanism can be adjusted to be positioned along the front-rear direction of the fuselage along with the attitude of the rotary wings, significantly reducing the space occupied by the rotor connection mechanism and the rotary wings in the lateral or vertical directions, and improving the overall storage and transportation efficiency of the drone.

[0025] 2. The rotor connection mechanism includes a fixed part and a rotating part. The fixed part is connected to the fixed wing by adhesive bonding to form a non-detachable connection, while the rotating part is rotatably connected to the fixed part. The rotor unit is installed on the rotating part, which takes into account both power supply during operation and attitude adjustment during storage.

[0026] 3. The fixed part is located in the plane of the fixed wing as a whole. The rotating part is connected to the fixed part by a hinge structure, so that the rotating part can swing at a certain angle in the plane of the fixed wing. During the swinging process, there is at least one posture in which its extension direction is consistent with the extension direction of the fixed wing, which can further reduce the space occupied during storage.

[0027] 4. The extension direction of the fixed part is set to be perpendicular to the extension direction of the fixed wing; the rotating part can swing between the first extreme position and the second extreme position. When the rotating part is in the first extreme position, it points to the front or rear direction of the UAV; when it is in the second extreme position, it points to the wingtip of the fixed wing. This attitude direction can avoid interference with the airframe during attitude adjustment when storing the UAV. Moreover, the wingtip width of the fixed wing is generally smaller than that of the wing root. This attitude direction can make full use of the space left by the smaller wingtip width to place the rotating part.

[0028] 5. At least two sets of rotor connection mechanisms are symmetrically arranged on the front and rear sides of the fixed-wing structure, and the movement trajectory is mirror symmetrical. This improves the overall power performance and balance of the UAV, and enables the storage and retrieval of multi-rotor UAVs.

[0029] 6. The tail section of the fuselage is also equipped with a tail structure and a rear landing gear. The tail section is detachably connected to the fuselage, which is convenient for disassembly and storage. The rear landing gear not only provides landing support, but also supports the fuselage when disassembled and stored. The rear landing gear extends downward perpendicular to the plane of the fixed wing, so it will not occupy lateral space when stored. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the structure of the UAV in an embodiment of the present invention;

[0031] Figure 2 This is a schematic diagram of the structure of the UAV in an embodiment of the present invention;

[0032] Figure 3 for Figure 1 Enlarged view of point A in the middle;

[0033] Figure 4 for Figure 1 The diagram shown illustrates the storage of the drone.

[0034] Figure label:

[0035] 1. Organism;

[0036] 2. Fixed wing; 21. Wingtip; 22. Wing root; 23. Spall; 231. Transverse spall; 232. Longitudinal spall;

[0037] 3. Rotary wing;

[0038] 4. Skeleton; 41. Middle region; 42. End region;

[0039] 5. Rotor connecting mechanism; 51. Fixed part; 52. Rotating part; 53. Rotating pair assembly;

[0040] 6. Tail fin;

[0041] 71. Front landing gear; 72. Rear landing gear. Detailed Implementation

[0042] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. These embodiments are based on the technical solution of the present invention and provide detailed implementation methods and specific operating procedures. However, the scope of protection of the present invention is not limited to the following embodiments.

[0043] This invention provides a drone, with reference to... Figure 1 and Figure 2It includes: fuselage 1, fixed wing 2, rotary wing 3, frame 4 and rotor connection mechanism 5; frame 4 passes through fuselage 1 and extends into fixed wing 2; frame 4, fuselage 1 and fixed wing 2 are detachably connected; rotary wing 3 is mounted on rotor connection mechanism 5, and rotor connection mechanism 5 is movably mounted on fixed wing 2.

[0044] In some specific embodiments, reference is made to Figure 1 The fixed-wing 2 generates lift through relative motion with the air, enabling the UAV to achieve long-distance, high-speed flight. The rotary-wing 3 provides capabilities such as vertical takeoff and landing, hovering, and low-altitude maneuvering.

[0045] In some specific embodiments, reference is made to Figure 1 and Figure 3 The fuselage 1 includes a cabin, which serves as the physical carrier for functional components. The frame 4 is a rod-shaped structure with a circular cross-section. The middle section of the frame 4 connects to the fuselage 1, specifically extending laterally through the entire side wall of the cabin, with the connection point near the top of the fuselage 1. Both ends of the frame 4 extend outside the fuselage 1 and insert into the fixed wing 2 from the wing root 22. The fixed wing 2 has spar 23 inside, at least a portion of which is arranged longitudinally and laterally. The spar 23 has several holes, and the frame 4 extends and passes sequentially through these holes. The rotor connection mechanism 5 is a rod-shaped structure, with both ends connecting the rotor 3 and the fixed wing 2, respectively.

[0046] In some specific embodiments, the outer wall of the frame 4, the inner wall of the hole in the fuselage 1, and the inner wall of the hole in the fixed wing 2 are fitted together and fixed to each other by friction. During disassembly, an external force is applied to resist the friction between the contact surfaces of the two parts, thereby achieving separation.

[0047] In other embodiments, the frame 4, the fuselage 1 and the fixed wing 2 can also be fixed by fastening or threaded connection.

[0048] In some specific embodiments, reference is made to Figure 3 The rotor connection mechanism 5 includes a movable component and a fixed component. The fixed component is fixedly connected to the fixed wing 2, specifically to the wing beam 23 inside the fixed wing 2. The movable component is mounted on the fixed component through a movable connection, and the two form a kinematic pair assembly to achieve mobility, thereby adjusting the attitude of the movable component and driving the adjustment of the attitude of the rotor 3.

[0049] In some specific embodiments, reference is made to Figure 3 The rotor connection mechanism 5 is a rotating pair component 53, which drives the rotating blade 3 to swing in the plane circumferentially by rotating, so that it moves closer to or away from the fixed blade 2.

[0050] In other embodiments, the rotor connection mechanism 5 is a movable pair component, which can be a guide rail structure or a telescopic structure. It moves the rotor 3 in a straight line to move it closer to or away from the fixed wing 2.

[0051] In other embodiments, the rotor connection mechanism 5 is a spherical sub-assembly that drives the rotor 3 to swing spatially, causing it to move closer to or away from the fixed wing 2.

[0052] In some embodiments of the present invention, reference is made to Figure 3 The rotor connection mechanism 5 includes a fixed part 51 and a rotating part 52. The fixed part 51 is glued to the fixed wing 2, and the rotating part 52 is rotatably connected to the fixed part 51. The rotating wing 3 is disposed on the rotating part 52.

[0053] In other embodiments, the fixing part 51 and the fixing wing 2 may be fixed by threaded connection or mortise and tenon joint.

[0054] In some embodiments of the present invention, reference is made to Figure 3 The rotating part 52 and the fixed part 51 are hinged together, and the rotating part 52 swings in the plane where the fixed wing 2 is located.

[0055] In some specific embodiments, reference is made to Figure 3 The rotor connecting mechanism 5 has a movable component and a fixed component, namely a rotating part 52 and a fixed part 51, which are hinged to form a rotating pair assembly 53.

[0056] In some specific embodiments, the rotating part 52 and the fixed part 51 are hinged on one side and a quick-release buckle is provided on the other side. After the quick-release buckle is released, the rotating part 52 can rotate relative to the fixed part 51. When the rotating part 52 rotates back and the axes of the rotating part 51 and the fixed part 51 coincide, the quick-release buckle locks and fixes the relative position between the two.

[0057] In some embodiments of the present invention, reference is made to Figure 3 The fixing part 51 is located in the plane where the fixed wing 2 is located.

[0058] In some embodiments of the present invention, the rotating part 52 and the fixed part 51 are hinged together, and the swing posture of the rotating part 52 includes at least the extension direction of the rotating part 52 being the same as the extension direction of the fixed wing 2.

[0059] In some embodiments of the present invention, reference is made to Figure 3 The extension direction of the fixed part 51 is perpendicular to the extension direction of the fixed wing 2; the rotating part 52 swings between the first extreme position and the second extreme position. When the rotating part 52 is in the first extreme position, it points to the front or rear direction of the UAV, and when the rotating part 52 is in the second extreme position, it points to the wingtip 21 of the fixed wing 2.

[0060] In some specific embodiments, reference is made to Figure 1 and Figure 3 Following standard practice in the aviation field, the FRD (Front-Right-Down) coordinate system is adopted. The front is the X-axis, pointing towards the front of the nose. The right is the Y-axis, pointing towards the right side of the fuselage, i.e., laterally. The bottom is the Z-axis, pointing perpendicular to the lower side of the fuselage 1. The rotating part 52 swings within the plane formed by the X and Y axes of the plane containing the fixed wing 2, and the fixed part 51 is positioned in the X-axis direction or its opposite direction.

[0061] In some specific embodiments, reference is made to Figure 1 and Figure 3 When the rotating part 52 is in the first extreme position, the direction of the rotating part 52 is the X-axis direction or its opposite direction. When the rotating part 52 is in the second extreme position, the direction of the rotating part 52 is consistent with the direction of the front or rear edge of the fixed wing 2.

[0062] In some specific embodiments, reference is made to Figure 1 The extension direction of the fixed wing 2 includes the wingtip 21 pointing towards the fixed wing 2 and the wing root 22 pointing towards the fixed wing 2, and the two directions are opposite.

[0063] In other embodiments, the oscillation of the rotating part 52 can also oscillate in the XZ plane or the YZ plane to reduce the space occupied during storage.

[0064] In some embodiments of the present invention, reference is made to Figure 1 At least two rotor connection mechanisms 5 are provided on the front and rear sides of the fixed wing 2, and the movement trajectories of the rotor connection mechanisms 5 are mirror-symmetrical.

[0065] In some specific embodiments, reference is made to Figure 1 Two sets of rotor connection mechanisms 5 and rotating blades 3 are provided on one side of the fixed wing 2. One set is located at the front edge of the fixed wing 2, and the other set is located at the rear edge of the fixed wing 2. The movement trajectories of the two rotor connection mechanisms 5 are mirror symmetrical, that is, they can both swing towards the wingtip 21 of the fixed wing 2, so that the rotating parts 52 of the two rotor connection mechanisms 5 point to the wingtip 21 of the fixed wing 2.

[0066] In some embodiments of the present invention, reference is made to Figure 1 The tail section of the fuselage 1 is provided with a tail fin and a rear landing gear 72. The rear landing gear 72 extends downward perpendicular to the plane where the fixed wing 2 is located, and the tail fin is detachably connected to the fuselage 1.

[0067] In some embodiments of the present invention, reference is made to Figure 1The tail is a V-shaped tail, which includes two tail fins 6. The connection positions of the tail fins 6 and the fuselage 1 and the connection positions of the rear landing gear 72 and the fuselage 1 are the same in the longitudinal direction of the UAV, so that the tail fins 6 and the rear landing gear 72 are equally spaced in the circumferential direction.

[0068] In some embodiments of the present invention, reference is made to Figure 2 The fuselage 1 is also equipped with a front landing gear 71, which is formed by two landing support rods in a V-shape. The fixed wing 2, tail fin 6 and frame 4 are placed between the two landing support rods when stored.

[0069] In some embodiments of the present invention, reference is made to Figure 4 The drone can be stored in a rectangular box-shaped structure (not shown in the figure). The front-to-back direction of the fuselage 1 is consistent with the length direction of the box-shaped structure. After being separated from the fuselage 1, the two fixed wings 2 are placed on both sides of the fuselage 1 with the wingtips 21 pointing forward and the wing roots 22 pointing backward. The plane of the fixed wings 2 is kept within the plane formed by the front and downward directions of the fuselage 1. The rotating part 52 of the rotor connecting mechanism 5 rotates and points towards the wingtips 21. After being separated from the fuselage 1, the tail fin 6 is placed in the space formed between the two landing support rods of the front landing gear 71 below the fuselage 1. The frame 4 (not shown in the figure) is placed in the same direction as the length direction of the box-shaped structure. The fuselage 1, fixed wings 2, tail fin 6 and other drone components can be fixed in the box-shaped structure by several plate-like structures with grooves.

[0070] In some specific embodiments, the two ends of the frame 4 penetrate the fuselage 1 and extend into the fixed wing 2. The middle region 41 of the frame 4, i.e., the part connected to the fuselage 1, is rectangular, and the end region 42 of the frame 4, i.e., the part entering the fixed wing 2, is circular. The cross-sectional shape of the frame 4 smoothly transitions from the middle region to the end region. The wing spars 23 include a longitudinal wing spars 232 and a transverse wing spars 231. The longitudinal wing spars 232 are arranged along the front-rear direction of the fuselage 1, and the transverse wing spars 231 are arranged along the left-right direction of the fuselage 1. The longitudinal wing spars 232 are provided with frame 4 connection holes, through which the frame 4 passes. The longitudinal wing spars 232 connect to the transverse wing spars 231 and abut against the side of the frame 4.

[0071] In some specific embodiments, the extension direction of the transverse spar 231 is inclined to the extension direction of the frame 4, the depth of the arc-shaped groove gradually decreases in the direction pointing to the wingtip 21 of the fixed wing 2, and the depth of the arc-shaped groove gradually increases in the direction away from the wingtip 21 and penetrates the transverse spar 231, so that the end of the transverse spar 231 forms a forked structure.

[0072] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention 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 invention.

[0073] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0074] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; 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; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0075] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0076] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0077] The preferred embodiments of the present invention have been described in detail above. It should be understood that those skilled in the art can make numerous modifications and variations based on the concept of the present invention without creative effort. Therefore, all technical solutions that can be obtained by those skilled in the art based on the concept of the present invention through logical analysis, reasoning, or limited experimentation on the basis of existing technology should be within the scope of protection defined by the claims.

Claims

1. A drone, characterized in that, include: Airframe (1), fixed wing (2), rotary wing (3), frame (4) and rotor connection mechanism (5); The frame (4) passes through the fuselage (1) and extends into the fixed wing (2); The frame (4), the body (1) and the fixed wing (2) are detachably connected; The rotating wing (3) is mounted on the rotor connecting mechanism (5), and the rotor connecting mechanism (5) is movably mounted on the fixed wing (2).

2. The UAV according to claim 1, characterized in that, The rotor connection mechanism (5) includes a fixed part (51) and a rotating part (52). The fixed part (51) is glued to the fixed wing (2). The rotating part (52) is rotatably connected to the fixed part (51). The rotating wing (3) is disposed on the rotating part (52).

3. The UAV according to claim 2, characterized in that, The rotating part (52) and the fixed part (51) are hinged together, and the rotating part (52) swings in the plane where the fixed wing (2) is located.

4. The UAV according to claim 2, characterized in that, The fixing part (51) is located in the plane of the fixing wing (2).

5. The UAV according to claim 2, characterized in that, The rotating part (52) and the fixed part (51) are hinged together, and the swing posture of the rotating part (52) includes at least the extension direction of the rotating part (52) being the same as the extension direction of the fixed wing (2).

6. The UAV according to claim 5, characterized in that, The extension direction of the fixed part (51) is perpendicular to the extension direction of the fixed wing (2); the rotating part (52) swings between a first extreme position and a second extreme position. When the rotating part (52) is in the first extreme position, it points to the front or rear direction of the UAV. When the rotating part (52) is in the second extreme position, it points to the wingtip (21) of the fixed wing (2).

7. The UAV according to any one of claims 1 to 6, characterized in that, At least two rotor connection mechanisms (5) are provided on the front and rear sides of the fixed wing (2), and the movement trajectories of the rotor connection mechanisms (5) are mirror-symmetrical.

8. The UAV according to claim 1, characterized in that, The tail of the fuselage (1) is provided with a tail fin and a rear landing gear (72). The rear landing gear (72) extends downward perpendicular to the plane where the fixed wing (2) is located. The tail fin is detachably connected to the fuselage (1).

9. The UAV according to claim 8, characterized in that, The tail fin is a V-shaped tail fin.

10. The UAV according to claim 2, characterized in that, The rotating part (52) and the fixed part (51) are fixed together by a quick-release buckle.

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