Unmanned aerial vehicle with fixed wing and multi-rotor switching function

Abstract

The invention provides an unmanned aerial vehicle with a fixed wing and multi-rotor-wing switching function, and relates to the technical field of unmanned aerial vehicles, the unmanned aerial vehicle comprises an unmanned aerial vehicle body, two unmanned aerial vehicle fixed wings, two carrying frames, unmanned aerial vehicle rotor wings, auxiliary wings, rotor wing supporting frames, rotor wing check rings, motors and supporting shaft sleeves, and blocking columns are machined on the outer walls of the rotor wing check rings; a supporting shaft rod is machined at one end of the bumping post, the supporting shaft rod is sleeved with a bevel gear B, and the top of the bevel gear B is meshed with a bevel gear A; according to the technical scheme, two motors at the two ends of a carrying frame are used for controlling rotating shafts corresponding to the motors to drive bevel gears A to drive bevel gears B to rotate, and when supporting shaft rods rotate in supporting shaft sleeves, the supporting shaft rods drive unmanned aerial vehicle rotors to be switched from the horizontal state to the vertical state through bumping posts and rotor check rings; when the unmanned aerial vehicle is switched from a rotor wing flight state to a fixed wing flight state, turbulent flow of the four unmanned aerial vehicle rotors can be avoided, and the flight stability of the unmanned aerial vehicle can be improved conveniently.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), in particular to an UAV with a fixed-wing and multi-rotor switching function. Background Art

[0002] Drones are unmanned aircraft primarily controlled by radio remote control and self-contained programmable controls, or operated fully or intermittently autonomously by an onboard computer. Compared to manned aircraft, drones are often better suited for tasks deemed too "dull, dirty, or dangerous." Drones can be categorized into military and civilian applications. In the military, drones are divided into reconnaissance and target drones. In the civilian sector, drones can be used in a wide range of industries, with significant advantages in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspections, disaster relief, film and television production, and creating romance, greatly expanding the application of drones.

[0003] From a technical perspective, drones can be categorized into: unmanned fixed-wing aircraft, unmanned vertical take-off and landing aircraft, unmanned airships, unmanned helicopters, unmanned multi-rotor aircraft, and unmanned paragliders. As drones become more widely used in civilian applications, they are evolving towards smaller and lighter sizes, making them more convenient to use in urban environments.

[0004] The patent document with announcement number CN113148136B discloses a drone with fixed-wing and multi-rotor switching functions, which can realize the switching of rotors, making it have the advantages of both multi-rotor and fixed-wing drones; in addition, through the improvement of the structure of the left and right rotor tilt mechanism, the drone can start the number of rotating motors according to the kinetic energy and speed required for the drone rotor mechanism to rotate when the rotors are switched (based on the technical parameters fed back by the pitot tube, wind speed sensor, airflow sensor, flight altitude sensor, etc. on the head of the aircraft, the control system optimizes the selection of the number of rotating motors to start through big data calculation to match the kinetic energy and speed required for the drone rotor mechanism to rotate), ensuring that the left and right rotor mechanisms have sufficient power when changing direction, overcoming the reverse rotation force generated by the airflow on the propellers at both ends of the wings, so that the rotor mechanism can accurately rotate to the specified position and maintain mechanical lock.

[0005] Patent document CN110595293B discloses a method for operating a fixed-wing / rotor-wing hybrid UAV, integrating multiple functions such as cruise detection, pursuit attack, and hover strike. By integrating fixed-wing aircraft and rotary-wing UAV technologies, vector propulsion technology based on precise control of rotor angular velocity and direction, shaped-charge munition design, and rapid image processing and recognition technology, the method achieves the integration of munitions and aircraft, enabling multiple functions such as cruise detection, pursuit attack, and hover strike.

[0006] However, in the process of implementing the above technical solution, it was found that the above technical solution had the following technical problems:

[0007] This drone with fixed-wing and multi-rotor switching functions is set at both ends of the fixed wings and switches them at the right time. In actual application, the method of controlling the drone's ascent by the rotors is easily blocked by the surface of the fixed wings, which increases the obstacles that need to be overcome for its ascent and increases the energy burden.

[0008] The method of using fixed-wing assisted drone flight is susceptible to rotor turbulence at both ends of the fixed wings due to the influence of aerodynamics, which affects the stability of the drone flight. Summary of the Invention

[0009] In order to overcome the shortcomings of the existing method of controlling the rise of drones by rotors, which is easily blocked by the surface of fixed wings, increasing the obstacles that need to be overcome for its rise and increasing the energy burden; the method of using fixed wings to assist drone flight is easily affected by the rotor turbulence at both ends of the fixed wings due to the influence of aerodynamics, affecting the stability of the drone flight and not conducive to the development of drones in the direction of smaller size and lighter weight, the embodiment of the present application provides a drone with fixed-wing and multi-rotor switching functions, by using two motors at both ends of the carrier to respectively control the corresponding rotating shafts to drive bevel gear A to drive bevel gear B to rotate, thereby driving the support shaft to rotate inside the support shaft sleeve, and the support shaft drives the drone rotor inside the rotor retaining ring to switch from a horizontal state to a vertical state through a retaining column, which can avoid the turbulence of the four drone rotors when the drone switches from the rotor flight state to the fixed-wing flight state, thereby improving the stability of the drone flight;

[0010] By making the four UAV rotors switch between horizontal and vertical states along with the four rotor retaining rings, and the auxiliary wings as the coordinated part of the UAV fixed wings change synchronously with the working state of the UAV rotors, it is avoided that when the UAV is lifted to the top by the four UAV rotors, the auxiliary wings are in a vertical state to reduce the movement resistance. When the UAV fixed wings and auxiliary wings glide, the four UAV rotors push the air in the horizontal direction, thereby increasing the flight speed of the UAV and reducing energy loss.

[0011] The technical solution adopted by the embodiment of the present application to solve the technical problem is:

[0012] A UAV with fixed-wing and multi-rotor switching functions, comprising a UAV fuselage, UAV fixed wings and a carrier, wherein the UAV is provided with two fixed wings, which are symmetrically assembled and fixed to both sides of the UAV fuselage;

[0013] There are two carriers, which are symmetrically arranged on both sides of the drone body, and the layout direction is parallel to the direction of the drone body;

[0014] UAV rotors are provided at both ends of one side of the carrier, and auxiliary wings are provided at the center of the other side of the carrier;

[0015] Among them, when the drone fuselage uses four drone rotors as flight power components, the four drone rotors are all in a horizontal setting, and blow air from the top to the bottom to generate flight power, while the auxiliary wings are in a vertical state. The drone rotors rotate from a horizontal state to a vertical state on one side of the carrier along the direction of the drone fuselage, and the auxiliary wings rotate from a vertical state to a horizontal state on the other side of the carrier along the direction of the drone fuselage.

[0016] In one possible implementation, the carrier includes a V-field in the center and a field at both ends, the auxiliary wing is movable on the inner side of the V-field on the carrier, and the two UAV rotors are movably connected to the side of the field on the carrier close to the UAV fuselage.

[0017] In one possible implementation, a rotor support frame is provided at the bottom of the UAV rotor, and the same rotor retaining ring is processed around the rotor support frame. The UAV rotor is mounted to the center of the rotor support frame, which supports the UAV rotor to rotate on the inner side of the rotor retaining ring, and the tip of the V-end on the carrier is assembled and connected to one end of the UAV fixed wing.

[0018] In one possible implementation, support sleeves are machined inside both ends of the carrier, a retaining column is machined on the outer wall of the rotor retaining ring, a support shaft is machined at one end of the retaining column, a bevel gear B is sleeved on the outside of the support shaft near one end of the retaining column, the top of the bevel gear B is meshingly connected with a bevel gear A, a motor is provided on the top of the bevel gear A, the support sleeve remains perpendicular to a field part on the carrier in a horizontal plane, the motor is assembled to the top of one end of the carrier, and by extending the bevel gear A into the interior of the motor, the bevel gear A is controlled by the rotating shaft to drive the bevel gear B to rotate, thereby driving the support shaft to rotate inside the support sleeve.

[0019] In one possible implementation, a keyway parallel to its axis is machined on the curved surface of the supporting shaft, and a same pin key is pinned between the inside of the keyway and the inner side of the bevel gear B. The external sleeve of one end of the supporting shaft is connected with a limiting sleeve, and a strip groove matching the pin key is machined on the inner wall of one end of the limiting sleeve. One end of the limiting sleeve rests on one side of the bevel gear B, and one end of the pin key extends from the inner side of the bevel gear B and is pinned to the strip groove on the inner wall of one end of the limiting sleeve through the inside of the keyway.

[0020] In one possible implementation, the outside of one end of the stop column and the outside of one end of the limiting sleeve are both interference fit with bearings, the bearing on the outside of the stop column is interference fit to the outside of one end of the supporting sleeve, and the bearing on the outside of the stop column is located between the outer wall of the rotor retaining ring and one end of the supporting sleeve, and the bearing on the outside of the limiting sleeve is interference fit to the outside of the other end of the supporting sleeve.

[0021] In one possible implementation, the outer wall of one end of the supporting shaft is processed with a thread, the threaded area extends from the inside of one end of the limiting sleeve, and supports the supporting shaft to be threadedly connected to the limiting buckle cap, one side of the limiting buckle cap is buckled to the outside of one end of the supporting sleeve, and the limiting buckle cap is rotatably connected to one end of the supporting sleeve along with the supporting shaft.

[0022] In one possible implementation, the limiting sleeve includes a first circular sleeve and a second circular sleeve, the diameter of the first circular sleeve is larger than the diameter of the second circular sleeve, the bearing is sleeved on the outside of the first circular sleeve, and a hinge seat is provided on the outer wall of the second circular sleeve on the limiting sleeve.

[0023] In one possible implementation, the auxiliary wings are located on both side surfaces facing the direction of the UAV fuselage and are hingedly connected with linkage rods. One end of the two linkage rods passes through the connection point between the V-field and the first field on the carrier, and is passed through the interior of the first field on the carrier to be hingedly connected to the hinge seat on the outer wall of the limit shaft sleeve.

[0024] In one possible implementation, the auxiliary wing is hingedly connected to the inner wall of the V-field on the carrier near the center of one side of the drone fuselage, and the hinge points of the two linkage rods and the auxiliary wing are arranged up and down in the vertical direction, and the two hinge points are symmetrical about the origin.

[0025] The beneficial effects of this application are:

[0026] First, in this solution, the two motors at both ends of the carrier respectively control the corresponding rotating shafts to drive the bevel gear A to drive the bevel gear B to rotate, thereby driving the support shaft to rotate inside the support shaft sleeve. The support shaft drives the UAV rotor inside the rotor retaining ring to switch from a horizontal state to a vertical state through the retaining column. When the UAV switches from the rotary-wing flight state to the fixed-wing flight state, the turbulence of the four UAV rotors can be avoided, thereby improving the stability of the UAV flight.

[0027] Secondly, the bevel gear A is controlled by the motor to drive the bevel gear B to rotate, thereby driving the support shaft to rotate inside the support sleeve. When the support shaft drives the drone rotor inside the rotor retaining ring to switch from a horizontal state to a vertical state through the retaining column, the hinge seat at the outer wall of the limit sleeve is in a synchronous rotation state, thereby pulling the auxiliary wing to rotate around the hinge point between it and the carrier, so that the auxiliary wing switches from a vertical state to a horizontal state. When the drone rotor pushes the air in the horizontal direction, the auxiliary wing can be used to simulate the gliding state of the fixed-wing drone, and a fixed lift can be generated by taking advantage of the difference in air velocity between the top and bottom wall surfaces of the auxiliary wing.

[0028] Third, in this solution, the four UAV rotors are switched between horizontal and vertical states along with the four rotor retaining rings, and the auxiliary wings, which are the coordinated parts of the UAV fixed wings, change synchronously with the working state of the UAV rotors. This avoids the situation where the auxiliary wings are in a vertical state to reduce the movement resistance when the UAV is lifted to the top by the four UAV rotors, and when the UAV fixed wings and auxiliary wings are gliding, the four UAV rotors push the air in the horizontal direction, thereby increasing the flight speed of the UAV and reducing energy loss. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is a schematic diagram of the overall structure of a UAV with fixed-wing and multi-rotor switching functions according to the present invention;

[0030] Figure 2 This is a schematic diagram of the structure of a UAV with fixed-wing and multi-rotor switching function in use according to the present invention;

[0031] Figure 3 This is a second structural schematic diagram of a UAV with fixed-wing and multi-rotor switching functions in use according to the present invention;

[0032] Figure 4 This is a schematic diagram of the connection structure of the auxiliary wing and two limiting shaft sleeves of a UAV with fixed-wing and multi-rotor switching functions of the present invention;

[0033] Figure 5 The invention provides a UAV with fixed-wing and multi-rotor switching function. Figure 4 A magnified schematic diagram of part A in the middle;

[0034] Figure 6 This is a schematic diagram of the connection structure between the rotor retaining ring and the carrier of a UAV with fixed-wing and multi-rotor switching functions of the present invention;

[0035] Figure 7 The invention provides a UAV with fixed-wing and multi-rotor switching function. Figure 6 Enlarged schematic diagram of part B in the middle.

[0036] Reference numerals:

[0037] 1. UAV fuselage; 2. UAV fixed wing; 3. Carrier; 4. Support bushing; 5. UAV rotor; 6. Rotor retaining ring; 7. Motor; 8. Auxiliary wing; 9. Linkage rod; 10. Rotor support frame; 11. Limit buckle cap; 12. Bearing; 13. Limit bushing; 14. Support shaft rod; 15. Stop column; 16. Bevel gear A; 17. Keyway; 18. Bevel gear B; 19. Pin key. DETAILED DESCRIPTION

[0038] The technical solution in the embodiments of the present application is to solve the problems of the above-mentioned background technology, and the overall idea is as follows:

[0039] Example 1:

[0040] This embodiment introduces the specific structure of a UAV with fixed-wing and multi-rotor switching functions. Figure 1-Figure 7 As shown, it includes a drone body 1, two drone fixed wings 2 and a carrier 3 symmetrically assembled and fixed to both sides of the drone body 1, the two carriers 3 symmetrically arranged on both sides of the drone body 1 (the layout direction is parallel to the orientation of the drone body 1), drone rotors 5 are arranged at both ends of one side of the carrier 3, and an auxiliary wing 8 is arranged at the center of the other side of the carrier 3;

[0041] like Figure 4-Figure 7 As shown, support sleeves 4 are machined inside both ends of the carrier 3 (the support sleeves 4 remain perpendicular to the upper portion of the carrier 3 in the horizontal plane), a retaining column 15 is machined on the outer wall of the rotor retaining ring 6, and a support shaft 14 is machined at one end of the retaining column 15. A bevel gear B18 is sleeved on the outer portion of the support shaft 14 near one end of the retaining column 15, and a bevel gear A16 is meshingly connected to the top of the bevel gear B18. A motor 7 is provided on the top of the bevel gear A16. A rotor support frame 10 is provided at the bottom of the UAV rotor 5, and the same rotor retaining ring 6 is machined around the rotor support frame 10.

[0042] Among them, by installing the drone rotor 5 at the center of the rotor support frame 10, which supports the drone rotor 5 to rotate on the inside of the rotor retaining ring 6, the rotor retaining ring 6 can be installed to one side of the carrier 3 through the support shaft 14 and related structures (limiting sleeve 13, bearing 12 and retaining column 15). The drone rotor 5 is connected to the drone fuselage 1 through the carrier 3 and the drone fixed wing 2. When the drone rotor 5 in the working state is used to provide power for the drone fuselage 1 to move toward the top, it can be used to simulate the existing rotor-type drone;

[0043] Secondly, the carrier 3 includes a V-shaped segment in the center and segments at both ends. The tip of the V-shaped end on the carrier 3 is assembled and connected to one end of the UAV fixed wing 2. By assembling the motor 7 to the top of one end of the carrier 3 and extending the bevel gear A16 into the interior of the motor 7, the bevel gear A16 is controlled by the rotating shaft to drive the bevel gear B18 to rotate, thereby driving the support shaft 14 to rotate inside the support sleeve 4, so that the support shaft 14 can drive the UAV rotor 5 inside the rotor retaining ring 6 to switch from a horizontal state to a vertical state through the retaining column 15;

[0044] In this state, the two UAV rotors 5 are movably connected to the inner side of the two rotor retaining rings 6 on the upper side of the carrier 3 close to the UAV fuselage 1, realizing the switching from the horizontal state to the vertical state;

[0045] At the same time, because the rotor retaining ring 6 is provided on the outside of the UAV rotor 5, and the UAV rotor 5 is converted from a horizontal state to a vertical state, with the help of the rotor retaining ring 6 and the UAV rotor 5 being in a continuous working state, the gas can be pushed in the opposite direction of the UAV flight to simulate the working state of the existing turbojet aircraft (the state in which the turbojet engine provides power cannot be fully simulated), solving the problem that when the traditional UAV switches between the fixed-wing and rotor working states, the rotor is still in an easy-to-move state in the horizontal plane, which easily forms turbulence;

[0046] In addition, when the drone body 1 uses the four drone rotors 5 as the flight power components, the four drone rotors 5 are all in a horizontal arrangement, and blow air from the top to the bottom to generate flight power, while the auxiliary wings 8 are in a vertical state, which is conducive to minimizing the resistance when the drone rises to the top;

[0047] Furthermore, in order to facilitate the connection and fixation of the bevel gear B18 and the support shaft 14, as shown in FIG. Figure 4 and Figure 5 The inner wall of one end of the limiting sleeve 13 is processed with a strip groove that matches the pin key 19. By pressing one end of the limiting sleeve 13 against one side of the bevel gear B18, one end of the pin key 19 is extended from the inner side of the bevel gear B18 and is pinned to the strip groove at the inner wall of one end of the limiting sleeve 13. After the pin key 19 connects and fixes the bevel gear B18 and the support shaft 14, the limiting sleeve 13 can be connected and fixed to the support shaft 14. One end of the limiting sleeve 13 cooperates with the stop column 15 to limit the movement of the bevel gear B18 on the outside of the support shaft 14 along the axis direction of the support shaft 14.

[0048] Furthermore, in order to make the rotor retaining ring 6 rotate smoothly inside the support sleeve 4 through the retaining column 15 and the support shaft 14, as shown in FIG. Figure 6 and Figure 7 As shown, the outside of one end of the stop column 15 and the outside of one end of the limiting sleeve 13 are both interference-fitted with bearings 12. By making the bearing 12 on the outside of the stop column 15 interference-fit to the outside of one end of the support sleeve 4, and the bearing 12 on the outside of the stop column 15 being located between the outer wall of the rotor retaining ring 6 and one end of the support sleeve 4, and the bearing 12 on the outside of the limiting sleeve 13 being interference-fitted to the outside of the other end of the support sleeve 4, one bearing 12 can be supported between the stop column 15 and the other end of the support sleeve 4, and the other bearing 12 can support between one end of the limiting sleeve 13 (located on the outside of the support shaft rod 14) and one end of the support sleeve 4, so as to reduce the resistance of the support shaft rod 14 to the movement inside the support sleeve 4.

[0049] At the same time, by processing a thread on the outer wall of one end of the support shaft 14, the threaded area extends from the inside of one end of the limiting sleeve 13, and supports the support shaft 14 to be threadedly connected to the limiting buckle cap 11. When one side of the limiting buckle cap 11 is buckled to the outside of one end of the support sleeve 4, the limiting buckle cap 11 is rotatably connected to one end of the support sleeve 4 along with the support shaft 14, which can limit the movement of the support shaft 14 along the axial direction inside the support sleeve 4.

[0050] Example 2:

[0051] Based on Example 1, this example introduces the specific structure of the auxiliary wing 8, such as Figures 2 to 7 As shown, the auxiliary wings 8 are located on both side surfaces of the UAV fuselage 1 facing the direction and are hingedly connected to linkage rods 9;

[0052] like Figure 4 As shown, the limiting sleeve 13 includes a first circular sleeve and a second circular sleeve. The diameter of the first circular sleeve is larger than that of the second circular sleeve. The bearing 12 is sleeved on the outside of the first circular sleeve. A hinge seat is provided on the outer wall of the second circular sleeve on the limiting sleeve 13.

[0053] Among them, by making one end of the two linkage rods 9 pass through the connection point between the V-field and the first field on the carrier 3, pass through the interior of the first field on the carrier 3 and be hingedly connected to the hinge seat on the outer wall of the limiting shaft sleeve 13, when the motor 7 controls the bevel gear A16 to drive the bevel gear B18 to rotate by means of the rotating shaft, thereby driving the support shaft 14 to rotate inside the support shaft sleeve 4, the support shaft 14 can drive the UAV rotor 5 inside the rotor retaining ring 6 from the horizontal state to the vertical state through the blocking column 15, and the hinge seat on the outer wall of the limiting shaft sleeve 13 is in a synchronous rotation state, which is convenient for pulling the auxiliary wing 8 to rotate around the hinge point between it and the carrier 3, so that the auxiliary wing 8 is switched from the vertical state to the horizontal state;

[0054] At the same time, in order to ensure that the auxiliary wing 8 is moved by the rotation of the limiting sleeve 13, the linkage rod 9 is controlled. Figure 2 and Figure 3 As shown, the auxiliary wing 8 is hingedly connected to the inner wall of the V-field on the carrier 3 near the center of one side of the UAV fuselage 1, and the hinge points of the two linkage rods 9 and the auxiliary wing 8 are arranged up and down in the vertical direction, and the two hinge points are symmetrical about the origin. When the UAV rotor 5 is rotated from a horizontal state to a vertical state on one side of the carrier 3 along the direction of the UAV fuselage 1, the inner side of the V-field on the movable carrier 3 of the auxiliary wing 8 can be rotated from a vertical state to a horizontal state along the direction of the UAV fuselage 1.

[0055] Specifically, when using the drone with fixed-wing and multi-rotor switching functions to work:

[0056] First, based on the existing UAV control technology and control distance, the rotor retaining ring 6 carries the UAV rotor 5 on the top of the rotor support frame 10 in a horizontal state. When the UAV rotor 5 is working, it pushes the gas toward the bottom to generate lift toward the top (in this state, the auxiliary wing 8 is in a vertical state). The UAV rotor 5 is installed on the inner side of the rotor retaining ring 6, and the rotor retaining ring 6 is installed to one side of the support sleeve 4 through the retaining column 15 and the support shaft 14, and is supported by the limiting sleeve 13 outside the support shaft 14, the bearing 12 between one end of the limiting sleeve 13 and one end of the support sleeve 4, and the bearing 12 between the retaining column 15 and the other end of the support sleeve 4, driving the carrier 3, the UAV fixed wing 2 and the UAV fuselage 1 to rise from the bottom to the top, realizing the take-off of the UAV (in the process of the UAV flying with four UAV rotors 5 as power components, the UAV's movement direction control and speed control are all referred to the well-known means in the field);

[0057] Then, when the UAV flies to a certain height, the two motors 7 at both ends of the carrier 3 respectively control the corresponding rotating shafts to drive the bevel gear A16 to drive the bevel gear B18 to rotate, thereby driving the support shaft 14 to rotate inside the support shaft sleeve 4, so that the support shaft 14 can drive the UAV rotor 5 inside the rotor retaining ring 6 to switch from a horizontal state to a vertical state through the retaining column 15;

[0058] At the same time, the hinge seat at the outer wall of the limiting shaft sleeve 13 is in a synchronous rotation state, which is convenient for pulling the auxiliary wing 8 to rotate around the hinge point between it and the carrier 3, so that the auxiliary wing 8 is switched from a vertical state to a horizontal state. When the drone rotor 5 pushes the air in the horizontal direction (switched from the vertical state), the auxiliary wing 8 can be used to simulate the gliding state of the fixed-wing drone, and the air flow rate difference between the top and bottom wall surfaces of the auxiliary wing 8 can be used to generate a fixed lift, thereby increasing the moving speed of the drone in the air.

[0059] Finally, it should be noted that the above embodiments are merely examples for the purpose of illustrating the present invention and are not intended to limit the embodiments. Those skilled in the art will readily appreciate that other variations or modifications based on the above description are possible. It is not necessary and impossible to provide an exhaustive list of all embodiments. However, obvious variations or modifications arising therefrom remain within the scope of protection of the present invention.

Claims

1. A UAV with fixed-wing and multi-rotor switching function, characterized in that: include: UAV fuselage (1); The drone fixed wings (2) are provided with two fixed wings, which are symmetrically assembled and fixed to both sides of the drone fuselage (1); Two carriers (3) are provided and are symmetrically arranged on both sides of the UAV fuselage (1), and the arrangement direction is kept parallel to the direction of the UAV fuselage (1); UAV rotors (5) are provided at both ends of one side of the carrier (3), and an auxiliary wing (8) is provided at the center of the other side of the carrier (3); When the drone fuselage (1) uses four drone rotors (5) as flight power components, the four drone rotors (5) are all in a horizontal arrangement and blow air from the top to the bottom to generate flight power, while the auxiliary wings (8) are in a vertical state. The drone rotors (5) rotate from a horizontal state to a vertical state on one side of the carrier (3) along the direction in which the drone fuselage (1) is facing, while the auxiliary wings (8) rotate from a vertical state to a horizontal state on the other side of the carrier (3) along the direction in which the drone fuselage (1) is facing.

2. The UAV with fixed-wing and multi-rotor switching function as claimed in claim 1, characterized in that: The carrier (3) includes a V-shaped field in the center and two fields at both ends. The auxiliary wing (8) is movable on the inner side of the V-shaped field on the carrier (3), and the two UAV rotors (5) are movably connected to the side of the field on the carrier (3) close to the UAV fuselage (1).

3. The UAV with fixed-wing and multi-rotor switching function as claimed in claim 2, characterized in that: A rotor support frame (10) is provided at the bottom of the UAV rotor (5), and a rotor retaining ring (6) is processed around the four sides of the rotor support frame (10); The UAV rotor (5) is mounted at the center of a rotor support frame (10), which supports the UAV rotor (5) to rotate inside a rotor retaining ring (6), and the tip of the V-shaped end on the carrier (3) is assembled and connected to one end of the UAV fixed wing (2).

4. The UAV with fixed-wing and multi-rotor switching function as claimed in claim 3, characterized in that: The inside of both ends of the carrier (3) is processed with a supporting shaft sleeve (4), the outer wall of the rotor retaining ring (6) is processed with a retaining column (15), one end of the retaining column (15) is processed with a supporting shaft rod (14), the outer part of the supporting shaft rod (14) close to the end of the retaining column (15) is sleeved with a bevel gear B (18), the top of the bevel gear B (18) is meshingly connected with a bevel gear A (16), and the top of the bevel gear A (16) is provided with a motor (7); The support sleeve (4) is kept vertical to a portion of an upper field of the carrier (3) in a horizontal plane, the motor (7) is assembled to the top of one end of the carrier (3), and the bevel gear A (16) is inserted into the interior of the motor (7), and the bevel gear A (16) is controlled by a rotating shaft to drive the bevel gear B (18) to rotate, thereby driving the support shaft (14) to rotate inside the support sleeve (4).

5. The UAV with fixed-wing and multi-rotor switching function as claimed in claim 4, characterized in that: The curved surface of the support shaft (14) is processed with a keyway (17) parallel to its axis, the inside of the keyway (17) and the inner side of the bevel gear B (18) are pin-connected with a same pin key (19), and the outer sleeve of one end of the support shaft (14) is connected to a limited sleeve (13); A strip groove matching the pin key (19) is machined on the inner wall of one end of the limiting sleeve (13), one end of the limiting sleeve (13) abuts against one side of the bevel gear B (18), one end of the pin key (19) extends from the inner side of the bevel gear B (18) and is pin-connected to the strip groove on the inner wall of one end of the limiting sleeve (13) through the inside of the keyway (17).

6. The UAV with fixed-wing and multi-rotor switching function as claimed in claim 4, characterized in that: The outer portion of one end of the blocking column (15) and the outer portion of one end of the limiting sleeve (13) are both interference-fitted with a bearing (12); The bearing (12) outside the retaining column (15) is interference-fitted to the outside of one end of the supporting sleeve (4), and the bearing (12) outside the retaining column (15) is located between the outer wall of the rotor retaining ring (6) and one end of the supporting sleeve (4), and the bearing (12) outside the limiting sleeve (13) is interference-fitted to the outside of the other end of the supporting sleeve (4).

7. The UAV with fixed-wing and multi-rotor switching function as claimed in claim 4, characterized in that: The outer wall of one end of the support shaft rod (14) is processed with a thread, and the threaded area extends from the inside of one end of the limiting sleeve (13) and supports the support shaft rod (14) to be threadedly connected to the limiting buckle cap (11); One side of the limit buckle cap (11) is buckled onto the outside of one end of the support shaft sleeve (4), and the limit buckle cap (11) is rotatably connected to one end of the support shaft sleeve (4) along with the support shaft rod (14).

8. The UAV with fixed-wing and multi-rotor switching function as claimed in claim 6, characterized in that: The limiting shaft sleeve (13) comprises a first circular sleeve and a second circular sleeve, the diameter of the first circular sleeve is larger than the diameter of the second circular sleeve, the bearing (12) is sleeved on the outside of the first circular sleeve, and a hinge seat is provided on the outer wall of the second circular sleeve on the limiting shaft sleeve (13).

9. The UAV with fixed-wing and multi-rotor switching function as claimed in claim 8, characterized in that: The auxiliary wings (8) are both articulatedly connected to linkage rods (9) on the surfaces of both sides of the drone fuselage (1) in the direction in which they face. One end of the two linkage rods (9) passes through the connection point between the V-field and the first field on the carrier (3), passes through the interior of the first field on the carrier (3), and is articulatedly connected to a hinge seat on the outer wall of the limiting shaft sleeve (13).

10. The UAV with fixed-wing and multi-rotor switching function as claimed in claim 9, characterized in that: The auxiliary wing (8) is hingedly connected to the inner wall of the V-shaped field on the carrier (3) at the center of one side of the drone fuselage (1), and the hinge points of the two linkage rods (9) and the auxiliary wing (8) are arranged up and down in the vertical direction, and the two hinge points are symmetrical about the origin.

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