Composite wing unmanned aerial vehicle

Abstract

The invention relates to a composite wing unmanned aerial vehicle which comprises a main body and a composite wing structure, and the composite wing structure is installed on the main body. The main body is provided with a first vertical datum plane passing through the central axis of the main body, and the gravity center of the composite wing structure and the gravity center of the main body are both located on the first vertical datum plane; the composite wing structure comprises a fixed wing assembly and a rotor wing assembly; the fixed wing assembly comprises a main wing, an aileron and a vehicle arm; the main wing is fixedly connected with the main body and is provided with an extension part extending in the direction far away from the main body; the aileron is rotationally mounted on the aileron, so that the direction of the composite wing unmanned aerial vehicle can be adjusted through rotation; the arms are fixedly mounted at the lower end of the extension part and arranged in the extension direction of the extension part, and the two arms are located at the two ends of the aileron respectively; the unmanned aerial vehicle has the advantages of being stable in operation and high in flexibility.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a compound-wing unmanned aerial vehicle. Background Art

[0002] With the advent of the low-altitude economy boom, the unmanned aerial vehicle technology has developed rapidly and is increasingly widely used in military, civilian, and industrial fields.

[0003] Traditional unmanned aerial vehicles are mainly fixed-wing or multi-rotor types. Among them, fixed-wing unmanned aerial vehicles are known for their efficient aerodynamic performance and long endurance, and are widely used in long-distance transportation and cruising missions. However, due to their inability to take off and land vertically, they have high requirements for takeoff and landing sites, which limits their use scenarios in complex environments; multi-rotor unmanned aerial vehicles have extremely strong vertical takeoff and landing capabilities and flexible hovering characteristics, and are suitable for operations in complex terrains. However, due to their short endurance and slow cruising speed, it is difficult for them to meet the requirements of long-distance transportation and efficient cruising.

[0004] In order to take into account the advantages of the above two traditional unmanned aerial vehicles, a compound-wing unmanned aerial vehicle has also been designed in the prior art, that is, by integrating a multi-rotor power system on a fixed-wing structure, enabling it to switch between vertical takeoff and landing and horizontal cruising modes.

[0005] However, for existing compound-wing unmanned aerial vehicles, the design of the power system (such as the wing structure and the driving unit of the wing structure) is complex, which easily leads to problems such as poor flexibility and stability of the wings. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to overcome the defects in the prior art, so as to provide a compound-wing unmanned aerial vehicle.

[0007] To achieve the above object, the present invention adopts the following technical solutions: A compound-wing unmanned aerial vehicle, including a main body and a compound-wing structure, the compound-wing structure is mounted on the main body; There is a first vertical reference plane passing through the central axis of the main body, and the center of gravity of the compound-wing structure and the center of gravity of the main body are both located on the first vertical reference plane; The compound-wing structure includes a fixed-wing assembly and a rotor assembly; The fixed-wing assembly includes a main wing, an aileron, and an arm; The main wing is fixedly connected to the main body and has an extension portion extending away from the main body; The aileron is rotatably mounted on the aileron to be able to adjust the direction of the compound-wing unmanned aerial vehicle by rotation; The arm is fixedly installed at the lower end of the extension part, and at least two arms are arranged along the extension direction of the extension part, and two of the arms are respectively located at both ends of the aileron; The rotor assembly is installed on the arm.

[0008] Preferably, two arms are arranged on one side of the main body, one of which is installed at the first installation position provided on the extension part, and the other is installed at the second installation position provided on the extension part; The minimum distance from the first installation position to the main body is H1, and the extension length of the extension part is H, then H1 and H satisfy: 1 / 4 ≤ H1 / H ≤ 1 / 3; The minimum distance from the second installation position to the main body is H2, then H2 and H satisfy: 2 / 3 ≤ H2 / H ≤ 3 / 4.

[0009] Preferably, the extension part is provided with a three-stage arc transition structure; The outer part of the extension part located outside the outermost arm has an arc side wall.

[0010] Preferably, the arm includes a balance connecting arm and a mounting part; The balance connecting arm is fixedly connected to the extension part, extends in a direction perpendicular to the extension direction of the extension part, and forms a flow guiding part with a gradually decreasing cross-sectional area at the end; The mounting part is located at the upper end of the flow guiding part, is arc-connected to the flow guiding part, and the cross-sectional area of the mounting part gradually increases in the direction from top to bottom.

[0011] Preferably, the rotor assemblies on the same side of the main body are centrally symmetrically distributed about the center of the extension part on the same side; and / or, The arm is made of carbon fiber composite material, and at least the balance connecting arm is provided with a hollow structure.

[0012] Preferably, among the four rotor assemblies installed on two adjacent arms, the rotation directions are the same diagonally and opposite on the same side; and / or, The rotor assembly includes a power source, a rotating shaft, and a propeller fixed to one end of the rotating shaft, and the power source is used to drive the rotating shaft to rotate; the surface of the propeller is treated by a low-friction coating process, and the inclination angle of the propeller is adjustable.

[0013] Preferably, the main wing is provided as an integral frame structure; The middle section of the main wing is provided as a connecting part, and the connecting part is fixedly installed at the upper end of the main body; The extension parts are symmetrically distributed about the connecting part.

[0014] Preferably, two main wings are symmetrically arranged with respect to the main body; Each of the main wings has an extension part, one end of the extension part is provided with a plug rod, and is plugged into one side of the main body through the plug rod; The extension part and the main body are fixedly connected by a fastener; The plug rods of the two extension parts are fixedly connected by a fastener.

[0015] Preferably, the fixed wing assembly further includes a vertical tail, a horizontal tail, a rudder and an elevator, The vertical tail and the horizontal tail are both fixedly installed on the main body, and the vertical tail is parallel to the first vertical reference plane, and the horizontal tail is perpendicular to the first vertical reference plane; The rudder is rotatably installed on the vertical tail and can rotate -30° to +30° relative to the vertical tail, so as to be able to adjust the direction of the compound wing UAV by rotation; The elevator is rotatably installed on the horizontal tail and can rotate -30° to +30° relative to the horizontal tail, so as to be able to adjust the lift of the compound wing UAV by rotation; Both ends of the rudder are respectively located at 10% and 90% of the span of the vertical tail, and the projected area of the rudder on the first vertical reference plane is S11, and the projected area of the rudder and the vertical tail on the first vertical reference plane is S12, then S11 / S12 ≤ 30%; Both ends of the elevator are respectively located at 10% and 90% of the span of the horizontal tail, and the projected area of the elevator on the horizontal plane is S21, and the projected area of the elevator and the horizontal tail on the horizontal plane is S22, then S21 / S22 ≤ 30%.

[0016] Preferably, the main wing has a preset dihedral angle, and the dihedral angle can be set to -3° to -1°; And / or, The projected area of the aileron on the horizontal plane is S31, and the sum of the projected areas of the main wing and the aileron on the horizontal plane is S32, then S31 / S32 ≤ 12%; And / or, The aileron can rotate -30° to +30° relative to the main wing; And / or; It further includes a landing gear, the landing gear is fixedly arranged at the lower end of the main body and is symmetrically arranged with respect to the first vertical reference plane, And / or; It also includes a front propeller, which is rotatably installed at the front end of the main body. The front propeller includes a rotating shaft, blades, and a protective cover covering the front end of the rotating shaft.

[0017] Compared with the prior art, the beneficial effects of the present invention are as follows: For a compound-wing unmanned aerial vehicle provided by the present invention, by setting the center of gravity of the compound-wing structure and the center of gravity of the main body on the first vertical reference plane (passing through the central axis of the main body), that is, the compound-wing structure is symmetrically distributed about the vertical plane where the central axis of the main body is located (i.e., the first vertical reference plane), it is beneficial to increase the balance of the entire compound-wing unmanned aerial vehicle, so that when the unmanned aerial vehicle does not exceed the rated load, its center of gravity will not shift, enabling the unmanned aerial vehicle to maintain stability and balance without adding additional weight structures, and capable of reducing the self-weight of the compound-wing unmanned aerial vehicle to a certain extent.

[0018] Furthermore, the fixed-wing assembly is set as a combined structure of a main wing, ailerons, and arms. That is, arms are installed at the lower end of the extension part of the main wing, and at least two arms are arranged at both ends of the ailerons. On the one hand, the setting of the arms can increase the support effect on the extension part, thereby effectively increasing the structural rigidity and bending resistance of the extension part, further improving the structural stability of the extension part, and avoiding the deformation of the extension part affecting the flight stability of the unmanned aerial vehicle; on the other hand, due to the stable support of the two arms on the same side of the main body, the part of the extension part between the two arms has better structural rigidity and bending resistance, and the ailerons are installed in the area between the two arms, enabling the stable installation and operation of the ailerons, and further enabling the ailerons to more sensitively and accurately control the unmanned aerial vehicle to perform rolling motion, providing the flexibility of the unmanned aerial vehicle.

[0019] In addition, the setting of the rotor assembly can improve the wind resistance of the unmanned aerial vehicle and enhance the flight stability; at the same time, installing the rotor assembly on the arms can not only meet the stable installation of the rotor assembly, but also ensure that the installation and operation of the rotor assembly will not affect the extension part of the main wing, and guarantee the structural strength and bending resistance of the extension part. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0021] Figure 1 It is a schematic structural diagram of the compound-wing unmanned aerial vehicle provided by the present invention.

[0022] Figure 2 ForFigure 1 Schematic diagram of the structure from another perspective.

[0023] Figure 3 For Figure 1 Enlarged schematic diagram of the position D1 in

[0024] Figure 4 For Figure 2 Partial schematic diagram of

[0025] Figure 5 Schematic diagram of the connection of the main wing, aileron, arm, and rotor assembly.

[0026] Figure 6 Schematic diagram of the connection of the vertical tail, horizontal tail, rudder, and elevator.

[0027] Figure 7 Schematic diagram of another embodiment of the main wing and the main body provided by the present invention.

[0028] Figure 8 For Figure 7 Enlarged schematic diagram of the position D2 in

[0029] Figure 9 For Figure 7 Schematic diagram of the structure of the main body in

[0030] Figure 10 Schematic diagram of the connection of the main wing and the aileron in 7.

[0031] Explanation of reference numerals: 1. Main body; 11. Connection notch; 12. Middle section connection hole; 13. Middle section card slot; 14. Tail card slot; 15. Tail mounting hole; 2. Fixed wing assembly; 21. Main wing; 211. Extension part; 2110. Arc side wall; 2111. First section; 2112. Second section; 2113. Third section; 212. Connection part; 213. Insertion rod; 22. Aileron; 23. Arm; 231. Balanced connection arm; 2311. Flow guiding part; 232. Mounting part; 24. Vertical tail; 25. Horizontal tail; 26. Rudder; 27. Elevator; 3. Rotor assembly; 31. Rotating shaft; 32. Propeller; 4. First mounting position; 5. Second mounting position; 6. Landing gear; 7. Front propeller. Detailed implementation manners

[0032] Next, the technical solutions of the present invention will be clearly and completely described in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0033] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0034] In the description of the present invention, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0035] See Figures 1 to 10 , an embodiment of the present invention provides a compound-wing unmanned aerial vehicle, including a main body 1 and a compound-wing structure, and the compound-wing structure is installed on the main body 1.

[0036] Specifically, a first vertical reference plane passing through the central axis of the main body 1 is provided (see M1 in Figure 1 ), and the center of gravity of the compound-wing structure and the center of gravity of the main body 1 are both located on the first vertical reference plane.

[0037] It is not difficult to understand that by setting the center of gravity of the compound-wing structure and the center of gravity of the main body 1 on the first vertical reference plane (passing through the central axis of the main body 1), that is, the compound-wing structure is symmetrically distributed about the vertical plane where the central axis of the main body 1 is located (i.e., the first vertical reference plane), which is beneficial to increasing the balance of the entire compound-wing unmanned aerial vehicle. When the compound-wing unmanned aerial vehicle does not exceed the rated load, its center of gravity will not shift. Furthermore, the compound-wing unmanned aerial vehicle can maintain stability and balance without adding an additional counterweight structure, and can reduce the self-weight of the compound-wing unmanned aerial vehicle to a certain extent.

[0038] Furthermore, the compound wing structure includes a fixed wing assembly 2 and a rotor assembly 3; wherein, the fixed wing assembly 2 includes a main wing 21, an aileron 22 and an arm 23; the main wing 21 is fixedly connected to the main body 1 and has an extension part 211 extending away from the main body 1; the aileron 22 is rotatably mounted on the aileron 22 to be able to adjust the direction of the compound wing UAV by rotation; the arm 23 is fixedly mounted at the lower end of the extension part 211, and at least two arms 23 are arranged along the extension direction of the extension part 211, and two of the arms 23 are respectively located at both ends of the aileron 22; the rotor assembly 3 is mounted on the arm 23.

[0039] It is not difficult to understand that in the above solution, the fixed wing assembly 2 is set as a combined structure of the main wing 21, the aileron 22 and the arm 23, that is, the arm 23 is mounted at the lower end of the extension part 211 of the main wing 21, and at least two arms 23 are arranged at both ends of the aileron 22. On the one hand, the support effect on the extension part 211 can be increased through the arrangement of the arm 23, and then the structural rigidity and bending resistance of the extension part 211 can be effectively increased, further improving the structural stability of the extension part 211 and avoiding the deformation of the extension part 211 from affecting the flight stability of the compound wing UAV; on the other hand, due to the stable support of the two arms 23 on the same side of the main body 1, the part of the extension part 211 between the two arms 23 has better structural rigidity and bending resistance, and the aileron 22 is mounted in the area between the two arms 23, so that the stable installation and operation of the aileron 22 can be realized, and then the aileron 22 can control the UAV to perform roll motion more sensitively and accurately, providing the flexibility of the UAV.

[0040] In addition, the anti-wind ability of the UAV can be improved through the setting of the rotor assembly 3, enhancing the flight stability; at the same time, mounting the rotor assembly 3 on the arm 23 can not only meet the stable installation of the rotor assembly 3, but also ensure that the installation and operation of the rotor assembly 3 will not affect the extension part 211 of the main wing 21, and guarantee the structural strength and bending resistance of the extension part 211.

[0041] It can be seen from the above that in this embodiment, through the connection of the extension part 211, the arm 23 and the rotor assembly 3, first, while meeting the stable installation of the rotor assembly 3, it does not affect the structural strength and bending resistance of the extension part 211; second, the support effect on the extension part 211 is increased, and then the structural rigidity and bending resistance of the extension part 211 are enhanced, which can ensure the stable operation of the UAV. In addition, the position of the aileron 22 cooperates with the arm 23, and the stable installation of the aileron 22 on the extension part 211 can be realized, so that it can control the roll motion more sensitively and accurately, improving the flight flexibility.

[0042] It should be understood that in the above solution, there are at least two extension parts 211 symmetrically arranged with respect to the main body 1 (that is, they can be two parts of a whole, or directly the extension parts 211 of two main wings 21, specifically refer to the following description), and at least two arms 23 are arranged on each extension part 211.

[0043] In addition, the compound-wing unmanned aerial vehicle in this embodiment can be applied in fields such as logistics transportation, agricultural production, and military reconnaissance.

[0044] See Figures 1 to 5 , two arms 23 are arranged on one side of the main body 1, one of which is installed at the first installation position 4 arranged on the extension part 211, and the other is installed at the second installation position 5 arranged on the extension part 211; the minimum distance from the first installation position 4 to the main body 1 is H1, the minimum distance from the second installation position 5 to the main body 1 is H2, and the extension length of the extension part 211 is H, then H1 / H = 1 / 3, H2 / H = 2 / 3. Furthermore, it helps to effectively share the bending moment generated by the lift difference of the compound-wing unmanned aerial vehicle, and can more evenly distribute the force borne by the extension part 211 of the main wing 21, reduce the deformation risk of the main wing 21, and improve the overall structural stability.

[0045] It is not difficult to understand that the entire compound-wing unmanned aerial vehicle is provided with four arms 23, which are evenly distributed on both sides of the main body 1 and are symmetrically distributed with respect to the first vertical reference plane. For the convenience of the installation and position calibration of the arms 23, the arms 23 located at the same extension length position (that is, the arms 23 at the same position on both sides of the main body 1) are attached to the same positions of the two extension parts 211.

[0046] Of course, H1 and H satisfy: 1 / 4 ≤ H1 / H ≤ 1 / 3; H2 and H satisfy: 2 / 3 ≤ H2 / H ≤ 3 / 4 are both acceptable. In other embodiments, the corresponding ratio can be specifically set according to actual needs.

[0047] Furthermore, the extension part 211 is set as a three-segment arc-transition structure; the outer part of the arm 23 located at the outermost side of the extension part 211 has an arc side wall 2110.

[0048] Specifically, the extension part 211 includes a first segment 2111, a second segment 2112, and a third segment 2113. The first segment 2111, the second segment 2112, and the third segment 2113 are sequentially connected by arc transitions along their extension directions; among them, among the two arms 23 on the same side of the main body 1, one is fixedly connected to the first segment 2111, and the other is fixedly connected to the second segment 2112, while the third segment 2113 (that is, the wing tip segment) has an arc side wall 2110, that is, the third segment 2113 gradually decreases in width from the second segment 2112 in the direction away from the main body 1 to form the arc side wall 2110.

[0049] It is not difficult to understand that adopting an arc curve design for transition in the third section 2113 (i.e., the outer part of the outermost arm 23 of the extension part 211, which is the wing tip) can avoid large aerodynamic interference at the wing tip, make the airflow more evenly distributed on the surface of the entire extension part 211, avoid excessive lift loss, and improve lift efficiency and overall stability. The high-lift design of the extension part 211 provides the main aerodynamic lift in the cruise mode. A streamlined transition structure can also be adopted at the connection between the extension part 211 and the main body 1, which can significantly reduce air resistance and improve flight efficiency.

[0050] Furthermore, to ensure the normal operation of the compound-wing UAV under different climatic conditions, the surfaces of the main wing 21 and the aileron 22 can be covered with a highly weather-resistant coating, which can effectively resist the erosion of harsh environments such as rain and sand.

[0051] See Figures 1 to 5 , the arm 23 includes a balance connecting arm 231 and a mounting part 232; the balance connecting arm 231 is fixedly connected to the extension part 211, extends in a direction perpendicular to the extension direction of the extension part 211, and forms a flow guiding part 2311 with a gradually decreasing cross-sectional area at the end; the mounting part 232 is located at the upper end of the flow guiding part 2311, is arc-connected to the flow guiding part 2311, and in the direction from top to bottom, the cross-sectional area of the mounting part 232 gradually increases.

[0052] It is not difficult to understand that the entire arm 23 is in a U-shaped structure, and the setting of the balance connecting arm 231 can better support the extension part 211. The flow guiding parts 2311 formed at both ends of the balance connecting arm 231 and the mounting part 232 as a whole form an arc structure with a gradually changing cross-section (i.e., a streamlined cone design), which can effectively reduce the friction between the airflow and the surface of the entire arm 23, reduce the change of surface pressure difference, and further reduce the pressure drag caused by airflow separation; at the same time, the conical tip design of the flow guiding part 2311 can optimize the airflow, make the airflow flow smoothly through the end of the arm 23 (i.e., the end position of the flow guiding part 2311 far from the balance connecting arm 231), avoid violent vortex and separation phenomena of the airflow at the end of the arm 23, which is beneficial to the stable operation of the compound-wing UAV and improves aerodynamic efficiency and fuel efficiency.

[0053] In addition, the cross-sectional area of the mounting part 232 gradually increases from top to bottom, which can not only ensure the stability of the installation of the rotor assembly 3, but also prevent the part of the mounting part 232 close to the rotor assembly 3 from causing a large area of occlusion to the rotor assembly 3 and avoid lift loss.

[0054] It is also worth noting that the "gradually decreasing cross-sectional area of the flow guiding part 2311" here means that "the cross-sectional area of the flow guiding part 2311 gradually decreases from the balance connecting arm 231 to the direction away from the balance connecting arm 231".

[0055] Furthermore, the rotor assemblies 3 on the same side of the main body 1 are centrally symmetrically distributed about the center of the extension part 211 on the same side thereof; thereby enabling the rotor assemblies 3 to apply more uniform lift to the extension part 211 through rotation, which is beneficial for the UAV to achieve stable vertical takeoff and landing.

[0056] Since the main force on the arm 23 comes from the rotor assemblies 3, during vertical takeoff and landing, the lift generated by the rotation of the rotor assemblies 3 will be transmitted to the arm 23, generating a vertical force on the arm 23. At the same time, the rotor assemblies 3 are also installed on the arm 23, and thus will generate a lateral moment on the arm 23. That is, when the rotor assemblies 3 are operating, the arm 23 will be subjected to forces in the vertical direction and the horizontal direction simultaneously. Also, since the length of the arm 23 is limited to ensure the stable takeoff, landing and operation of the UAV, in one embodiment, the arm 23 is made of carbon fiber composite material, and the balance connecting arm 231 can be set to a hollow structure, thereby effectively reducing the weight of the arm 23 while maintaining sufficient stiffness and strength.

[0057] Of course, in other embodiments, the mounting part 232 can also be set to a hollow structure as long as the stable installation of the rotor assemblies 3 can be achieved.

[0058] Furthermore, among the four rotor assemblies 3 installed on two adjacent arms 23, their rotation directions are set such that the diagonal directions are the same and the same-side directions are opposite (see Figure 2 ); where "the same-side directions are opposite" means that the rotation directions of the two rotor assemblies 3 located on the same side of the extension part 211 and installed on different arms 23 are opposite, and "the diagonal directions are the same" means that the rotation directions of the two rotor assemblies 3 located on both sides of the extension part 211 and on different arms 23 are the same.

[0059] See Figures 1 to 3 , the rotor assembly 3 includes a power source, a rotating shaft 31, and a propeller 32 fixed to one end of the rotating shaft 31. The power source is used to drive the rotating shaft 31 to rotate; the surface of the propeller 32 is treated with a low-friction coating process, and the inclination angle of the propeller 32 is adjustable.

[0060] Specifically, the rotor assembly 3 includes a power source, a rotating shaft 31, and a propeller 32. Among them, the power source is fixedly installed on the mounting part 232 and is used to drive the rotating shaft 31 to rotate. The rotating shaft 31 is rotatably installed on the mounting part 232, and the end away from the mounting part 232 is fixedly connected to the propeller 32 so that it can drive the propeller 32 to rotate, thereby providing lift for the compound-wing UAV.

[0061] Furthermore, the power source can be set as a drive motor and an electric drive device. Each drive motor of the rotor assembly 3 is equipped with an independent electric drive device to enhance the stability of a single rotor assembly 3 and achieve efficient power output.

[0062] Furthermore, the blade surfaces of each propeller 32 are treated by a low-friction coating process, which can effectively reduce the resistance of the airflow to the rotor assembly 3 and improve the lift efficiency of the rotor assembly 3 at the same time.

[0063] Furthermore, the propeller 32 can be set as a two-blade propeller and is symmetrically distributed with respect to the rotating shaft 31. The blades of the propeller 32 can be adjusted in angle according to flight requirements, and the adjustable angle range of the blades can be set from -5° to +5°. It should be noted that "+" means rotating upward relative to the horizontal plane for adjustment, and "-" means rotating downward relative to the horizontal plane for adjustment.

[0064] See Figures 1 to 6 , the fixed-wing assembly 2 further includes a vertical stabilizer 24, a horizontal stabilizer 25, a rudder 26 and an elevator 27, which are used to control the yaw movement and pitch movement of the compound-wing unmanned aerial vehicle, so as to improve the longitudinal and lateral stability of the unmanned aerial vehicle.

[0065] Specifically, the vertical stabilizer 24 and the horizontal stabilizer 25 are both fixedly installed on the main body 1, and the vertical stabilizer 24 is parallel to the first vertical reference plane, and the horizontal stabilizer 25 is perpendicular to the first vertical reference plane. The vertical stabilizer 24 and the rudder 26 cooperate with each other to control the yaw movement of the compound-wing unmanned aerial vehicle, and the horizontal stabilizer 25 and the elevator 27 control the pitch movement of the compound-wing unmanned aerial vehicle.

[0066] Furthermore, the rudder 26 is rotatably installed on the vertical stabilizer 24 and can rotate relative to the vertical stabilizer 24 from -30° to +30°, so as to be able to adjust the direction of the compound-wing unmanned aerial vehicle by rotation. Among them, "+" means rotating clockwise relative to the first vertical reference plane, and "-" means rotating counterclockwise relative to the first vertical reference plane, that is, the rudder 26 rotates with the axis L2 as the center of rotation axis (see Figure 6 ).

[0067] Furthermore, the elevator 27 is rotatably installed on the horizontal stabilizer 25 and can rotate relative to the horizontal stabilizer 25 from -30° to +30°, so as to be able to adjust the lift of the compound-wing unmanned aerial vehicle by rotation; among them, "-" means rotating downward relative to the horizontal plane, and "+" means rotating upward relative to the horizontal plane, that is, the elevator 27 rotates with the axis L3 as the center of rotation axis (see Figure 6 ).

[0068] Furthermore, the two ends of the rudder 26 are respectively located at 10% and 90% of the span of the vertical stabilizer 24, and the projected area of the rudder 26 on the first vertical reference plane is S11, and the projected area of the rudder 26 and the vertical stabilizer 24 on the first vertical reference plane is S12, then S11 / S12 ≤ 30%; Furthermore, both ends of the elevator 27 are respectively located at the 10% and 90% of the span of the horizontal stabilizer 25, and the projected area of the elevator 27 on the horizontal plane is S21, and the projected area of the elevator 27 and the horizontal stabilizer 25 on the horizontal plane is S22, then S21 / S22 ≤ 30%.

[0069] See Figures 1 to 6 , the main wing 21 has a preset dihedral angle, and the dihedral angle can be set from -3° to -1°, where the "-" indicates a downward rotation relative to the horizontal plane. It is not difficult to understand that the setting of the dihedral angle of the main wing 21 can improve the maneuverability of the UAV.

[0070] See Figures 1 to 6 , the projected area of the aileron 22 on the horizontal plane is S31, and the sum of the projected areas of the main wing 21 and the aileron 22 on the horizontal plane is S32, then S31 / S32 ≤ 12%.

[0071] See Figures 1 to 6 , the aileron 22 can rotate relative to the main wing 21 from -30° to +30°, where the "-" indicates a downward rotation relative to the horizontal plane, and the "+" indicates a downward rotation relative to the horizontal plane, that is, the aileron 22 rotates with the axis L2 as the center of rotation axis (see Figure 5 ).

[0072] It should be noted that the aileron 22, the rudder 26, and the elevator 27 are respectively rotatably mounted on the main wing 21, the vertical stabilizer 24, and the horizontal stabilizer 25 through power shafts, and their rotation angles are controlled by the ground console. For example, the power shaft is connected to a motor, and the motor is wirelessly communicatively connected to the ground console.

[0073] See Figures 1 to 6 , it further includes a landing gear 6, and the landing gear 6 is fixedly provided at the lower end of the main body 1 and is symmetrically arranged with respect to the first vertical reference plane. Specifically, the cross-section of the landing gear 6 in the direction perpendicular to the first vertical reference plane is trapezoidal. In addition, the landing gear 6 can be set as a rod connection structure, that is, a hollow design is formed. At the same time, the landing gear 6 can also be made of carbon fiber material, which can effectively reduce the weight of the aircraft and improve the fuel efficiency of the aircraft.

[0074] See Figures 1 to 6 , it further includes a front propeller 7, and the front propeller 7 is rotatably mounted at the front end of the main body 1. The front propeller 7 includes a shaft, blades, and a protective cover covering the front end of the shaft. The blades of the front propeller 7 can also be adjusted according to flight requirements, and the adjustment range of the angle is between -5° and 5°. In addition, the front propeller 7 can be driven by an engine, and in the working state, the blades of the front propeller 7 rotate to generate thrust to achieve a higher thrust-to-weight ratio.

[0075] The specific structure of the main wing 21 can be set according to the actual situation.

[0076] See Figures 1 to 5 In one embodiment, the main wing 21 is arranged as an integral frame structure. The middle section of the main wing 21 is arranged as a connecting portion 212, and the connecting portion 212 is fixedly arranged at the upper end of the main body 1. The extending portions 211 are symmetrically distributed with respect to the connecting portion 212. It is not difficult to understand that the main wing 21 is an integral structure, and the connecting portion 212 area of the main wing 21 can be connected to the main body 1 through fasteners.

[0077] Furthermore, for the convenience of installation and to limit the displacement of the main wing 21 along the central axis direction of the compound-wing unmanned aerial vehicle (i.e., the main body 1), a connecting notch 11 for the connecting portion 212 to be snapped into can also be arranged on the main body 1.

[0078] It is worth noting that the "connecting portion 212" can be understood as the part where the main wing 21 and the main body 1 overlap in the horizontal plane projection, and the "extending portion 211" can be understood as the part where the main wing 21 and the main body 1 do not overlap in the horizontal plane projection.

[0079] See Figures 7 to 10 In another embodiment, two main wings 21 are symmetrically arranged with respect to the main body 1. Each main wing 21 has an extending portion 211, and one end of the extending portion 211 is provided with a plugging rod 213, and the extending portion 211 is plugged into one side of the main body 1 through the plugging rod 213. The extending portion 211 and the main body 1 are fixedly connected through fasteners. The plugging rods 213 of the two extending portions 211 are fixedly connected through fasteners. It is not difficult to understand that at this time, on the one hand, the extending portion 211 can be directly fixedly connected to the main body 1, on the other hand, it can also be connected through the plugging rod 213. At the same time, the two symmetrically distributed extending portions 211 can also be fixedly connected through their respective plugging rods 213, increasing the installation stability of the extending portion 211 and reducing the installation difficulty of the main wing 21.

[0080] Specifically, the main body 1 of the compound-wing unmanned aerial vehicle can adopt a traditional helicopter design to accommodate power, battery and control systems. The main body 1 is provided with a middle-section connection hole 12 and a middle-section card slot 13. The main wing 21 is inserted into the middle-section card slot 13, and the main body 1 and the main wing 21 are fixedly connected by passing fasteners through the middle-section connection hole 12 and the connection hole on the main wing 21.

[0081] Furthermore, between the vertical tail 24 and the tail of the main body 1, and between the horizontal tail 25 and the tail of the main body 1, positioning connections can be achieved through the tail card slot 14 and the tail installation hole 15 arranged on the main body 1 (the connection method is the same as that between the main body 1 and the main wing 21, not elaborated here). At the same time, the vertical tail 24, the horizontal tail 25 and the main body 1 can also be connected through a truss structure to increase the structural stability.

[0082] It should be noted that when the above compound-wing UAV is operating, the propeller blades of the propeller 32 rotate to achieve vertical takeoff and landing. During vertical takeoff and landing, the main wing 21 should preferably maintain an angle of attack of 0° to reduce the interference of ground effect. After reaching the working altitude, it transitions to the cruise state through the pulling force of the front propeller 7 and the thrust (pulling force) component brought about by the deflection of the propeller blades of the propeller 32. In the transition state, the aileron 22, rudder 26, and elevator 27 start to work to assist the compound-wing UAV in rolling and yawing, maintaining the balance of the compound-wing UAV and ensuring the stability of the flight direction.

[0083] In the cruise state, the main wing 21 gradually provides the main lift required for cruising, and according to the actual working requirements, gradually reduces the rotational speed of the propeller blades of the propeller 32 to improve the energy conversion efficiency. At this time, the thrust (pulling force) required to maintain the cruise speed is mainly provided by the front propeller 7.

[0084] To meet the needs of long-duration cruise missions, photovoltaic cell materials are added to the upper surface of the main wing 21 for solar supplementary power supply during flight to extend the flight time.

[0085] The above embodiments are only the preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and substitutions made by those skilled in the art based on the present invention fall within the scope of protection required by the present invention.

Claims

1. A compound-wing unmanned aerial vehicle, characterized in that, Comprising a main body (1) and a composite wing structure, the composite wing structure being mounted on the main body (1); There is a first vertical reference plane passing through the central axis of the main body (1), and the center of gravity of the composite wing structure and the center of gravity of the main body (1) are both located on the first vertical reference plane; The composite wing structure includes a fixed wing assembly (2) and a rotor assembly (3); The fixed wing assembly (2) includes a main wing (21), an aileron (22) and an arm (23); The main wing (21) is fixedly connected to the main body (1) and has an extension part (211) extending away from the main body (1); The aileron (22) is rotatably mounted on the aileron (22) so as to be able to adjust the direction of the composite wing UAV by rotation; The arm (23) is fixedly mounted at the lower end of the extension part (211), and along the extending direction of the extension part (211), at least two arms (23) are arranged, and two of the arms (23) are respectively located at both ends of the aileron (22); The rotor assembly (3) is mounted on the arm (23).

2. The compound-wing unmanned aerial vehicle according to claim 1, characterized in that, There are two arms (23) arranged on one side of the main body (1), one of which is mounted on a first mounting position (4) provided on the extension part (211), and the other is mounted on a second mounting position (5) provided on the extension part (211); The minimum distance from the first mounting position (4) to the main body (1) is H1, and the span length of the extension part (211) is H, then H1 and H satisfy: 1 / 4 ≤ H1 / H ≤ 1 / 3; The minimum distance from the second mounting position (5) to the main body (1) is H2, then H2 and H satisfy: 2 / 3 ≤ H2 / H ≤ 3 / 4.

3. The compound-wing unmanned aerial vehicle according to claim 2, wherein, The extension part (211) is provided with a three-stage arc transition structure; The outer part of the extension part (211) located outside the outermost arm (23) has an arc side wall (2110).

4. The compound-wing unmanned aerial vehicle according to claim 2, wherein, The arm (23) includes a balance connecting arm (231) and a mounting part (232); The balance connecting arm (231) is fixedly connected to the extension part (211), extends in a direction perpendicular to the extending direction of the extension part (211), and forms a flow guiding part (2311) with a gradually decreasing cross-sectional area at the end; The mounting part (232) is located above the flow guiding part (2311), is arc-connected to the flow guiding part (2311), and in the direction from top to bottom, the cross-sectional area of the mounting part (232) gradually increases.

5. The compound-wing unmanned aerial vehicle according to claim 4, characterized in that, The rotor assemblies (3) on the same side of the main body (1) are centrally symmetrically distributed about the center of the extension part (211) on the same side; and / or The arm (23) is made of carbon fiber composite material, and at least the balance connecting arm (231) is provided with a hollow structure.

6. The compound-wing unmanned aerial vehicle according to claim 5, wherein Among the four rotor assemblies (3) mounted on two adjacent arms (23), their rotation directions are the same diagonally and opposite on the same side; and / or The rotor assembly (3) includes a power source, a rotating shaft (31), and a propeller (32) fixed to one end of the rotating shaft (31), and the power source is used to drive the rotating shaft (31) to rotate; the surface of the propeller (32) is treated by a low-friction coating process, and the inclination angle of the propeller (32) is adjustable.

7. A compound-wing unmanned aerial vehicle according to claim 1, wherein, The main wing (21) is provided as an integral frame structure; The middle section of the main wing (21) is provided as a connecting portion (212), and the connecting portion (212) is fixed to the upper end of the main body (1); The extension portions (211) are symmetrically distributed with respect to the connecting portion (212).

8. The compound-wing unmanned aerial vehicle according to claim 1, characterized in that, Two main wings (21) are symmetrically arranged with respect to the main body (1); Each main wing (21) has an extension portion (211), and one end of the extension portion (211) is provided with a plug rod (213), and is inserted into one side of the main body (1) through the plug rod (213); The extension portion (211) and the main body (1) are fixedly connected by fasteners; The plug rods (213) of the two extension portions (211) are fixedly connected by fasteners.

9. A compound-wing unmanned aerial vehicle according to claim 1, characterized in that, The fixed-wing assembly (2) further includes a vertical tail (24), a horizontal tail (25), a rudder (26), and an elevator (27), The vertical tail (24) and the horizontal tail (25) are both fixedly installed on the main body (1), and the vertical tail (24) is parallel to the first vertical reference plane, and the horizontal tail (25) is perpendicular to the first vertical reference plane; The rudder (26) is rotatably installed on the vertical tail (24), and can rotate -30° to +30° relative to the vertical tail (24), so as to be able to adjust the direction of the compound-wing unmanned aerial vehicle by rotation; The elevator (27) is rotatably installed on the horizontal tail (25), and can rotate -30° to +30° relative to the horizontal tail (25), so as to be able to adjust the lift of the compound-wing unmanned aerial vehicle by rotation; Both ends of the rudder (26) are respectively located at 10% and 90% of the span of the vertical tail (24), and the projected area of the rudder (26) on the first vertical reference plane is S11, and the projected area of the rudder (26) and the vertical tail (24) on the first vertical reference plane is S12, then S11 / S12 ≤ 30%; Both ends of the elevator (27) are respectively located at 10% and 90% of the span of the horizontal tail (25), and the projected area of the elevator (27) on the horizontal plane is S21, and the projected area of the elevator (27) and the horizontal tail (25) on the horizontal plane is S22, then S21 / S22 ≤ 30%.

10. A compound-wing unmanned aerial vehicle according to claim 1, wherein, The main wing (21) has a preset dihedral angle, and the dihedral angle can be set to -3° to -1°; and / or, The projected area of the aileron (22) on the horizontal plane is S31, and the sum of the projected areas of the main wing (21) and the aileron on the horizontal plane is S32, then S31 / S32 ≤ 12%; and / or, The aileron (22) is capable of rotating relative to the main wing (21) by -30° to +30°; and / or; It further includes a landing gear (6), and the landing gear (6) is fixedly arranged at the lower end of the main body (1) and is symmetrically arranged with respect to the first vertical reference plane. and / or; It further includes a front propeller (7), and the front propeller (7) is rotatably installed at the front end of the main body (1). The front propeller (7) includes a rotating shaft, blades, and a protective cover covering the front end of the rotating shaft.

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