Two-in-one convertible unmanned aerial vehicle

Abstract

The present invention belongs to the technical field of unmanned aerial vehicles. Disclosed is a two-in-one convertible unmanned aerial vehicle, comprising a fuselage and fixed wings. The two sides of the fuselage are each provided with a wing mounting part having adjustable orientation, and the wing mounting part is provided with two rotor arms with rotors and a fixed wing connecting part for mounting a fixed wing; the two rotor arms are arranged in a splayed shape, and the fixed wing connecting part is located between the two rotor arms; the coplanar arrangement of the two rotor arms is on an orientation adjustment path of the wing mounting part, and can be perpendicular to the length direction of the fuselage or parallel to the length direction of the fuselage.

Description

A two-in-one convertible drone Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a two-in-one convertible UAV. Background Art

[0002] Existing aircraft can be divided into helicopters and fixed-wing aircraft based on their flight principles. The former includes multi-rotor helicopters, coaxial twin-propeller helicopters, and cross-propeller helicopters, while the latter includes tilt-rotor aircraft, composite wing aircraft capable of vertical take-off and landing, and tail-seat vertical take-off and landing aircraft. Each type of aircraft operates in a different manner. Drones are also generally categorized into these two types. Helicopter-type drones can take off and land vertically and hover, but rely entirely on their rotors for lift, resulting in high energy consumption and short flight time. Fixed-wing drones offer high speeds and relatively low energy consumption, but cannot hover (composite wing aircraft) or can only hover briefly (tilt-rotor / composite wing aircraft). Due to their large size, fixed-wing aircraft have poor wind resistance.

[0003] As drones face increasingly diverse flight scenarios, some scenarios, such as logistics, emergency rescue, and security management, sometimes require helicopter hovering mode for better imaging, detailed on-site information, or precise material delivery. Other times, fixed-wing aircraft flight mode is needed to reach more distant target areas or fly longer to continuously capture continuous on-site images. This necessitates deploying both helicopters and fixed-wing aircraft to address the varying needs of the same scenario, which is costly, takes up a lot of space, and is difficult to deploy and carry. Summary of the Invention

[0004] The purpose of the present invention is to solve the above technical problems and provide a two-in-one convertible drone. By changing the orientation of the wing mounting portion and coordinating the disassembly and assembly of the fixed wing, the two modes of helicopter mode and fixed-wing mode can be switched on the same drone. There is no need to carry two different types of drones, which reduces equipment costs and space occupancy and facilitates deployment and carrying.

[0005] To achieve the above-mentioned objectives, the present invention provides the following solution: The present invention discloses a two-in-one convertible drone, comprising a fuselage and fixed wings, wherein wing mounting parts with variable orientation are provided on both sides of the fuselage, and the wing mounting parts are provided with two rotor rods with built-in rotors and a fixed wing connecting part for detachable installation of the fixed wings, the two rotor rods are arranged in an eight-shaped shape, the coplanarity of the rotors on the two rotor rods is parallel to the coplanarity of the two rotor rods, the fixed wing connecting part is located between the two rotor rods, the wing surface of the fixed wing mounted on the fixed wing connecting part is perpendicular to the coplanarity of the two rotor rods, and the coplanarity of the two rotor rods can be perpendicular to the length direction of the fuselage or parallel to the length direction of the fuselage on the direction change path of the wing mounting part. BRIEF DESCRIPTION OF THE DRAWINGS

[0006] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0007] FIG1 is a schematic diagram of a two-in-one convertible drone (helicopter mode, circular mount) according to one or more embodiments;

[0008] FIG2 is a schematic diagram of a two-in-one convertible drone (fixed-wing mode, circular mount) according to one or more embodiments;

[0009] FIG3 is a schematic diagram of a two-in-one convertible drone (fixed-wing mode, circular mount, tail wing) according to one or more embodiments;

[0010] FIG4 is a schematic perspective structural diagram of a fuselage (circular mounting groove) according to one or more embodiments;

[0011] FIG5 is a schematic structural diagram of a circular mounting base according to one or more embodiments;

[0012] FIG6 is a schematic diagram of the structure of a two-in-one convertible drone (fixed-wing mode, without fixed wings or tail wings) according to one or more embodiments;

[0013] FIG7 is a schematic structural diagram of a fixed wing root according to one or more embodiments;

[0014] FIG8 is a schematic cross-sectional structural diagram of a fuselage according to one or more embodiments;

[0015] FIG9 is a schematic structural diagram of a tail wing according to one or more embodiments;

[0016] FIG10 is a partial enlarged structural schematic diagram of FIG8;

[0017] FIG11 is a partial enlarged structural schematic diagram of FIG9;

[0018] FIG12 is a schematic diagram of a two-in-one convertible drone (helicopter mode, rectangular mounting base) according to one or more embodiments;

[0019] FIG13 is a schematic perspective structural diagram of a fuselage (vertical rectangular slots and horizontal rectangular slots) according to one or more embodiments;

[0020] FIG14 is a bottom perspective structural diagram of a rectangular mounting base according to one or more embodiments;

[0021] FIG15 is a top perspective structural diagram of a rectangular mounting base according to one or more embodiments;

[0022] FIG16 is a schematic structural diagram of a fixed wing root (including a wing slot) according to one or more embodiments;

[0023] FIG17 is a diagram illustrating a rotor status detection circuit connection according to one or more embodiments;

[0024] FIG18 is a diagram illustrating circuit connections for detecting tail status according to one or more embodiments;

[0025] FIG19 is a control flow diagram of a drone control system according to one or more embodiments.

[0026] Explanation of the accompanying symbols: 1. Fuselage; 2. Fixed wing; 3. Circular mounting seat; 4. Rectangular mounting seat; 5. Rotor; 6. Tail; 101. Circular mounting slot; 102. Circular mounting slot screw hole; 103. Circular mounting slot A contact; 104. Circular mounting slot B contact; 105. Vertical rectangular slot; 106. Horizontal rectangular slot; 107. Rectangular slot A screw hole; 108. Rectangular slot B screw hole; 109. Rectangular slot A contact; 110. Rectangular slot B contact; 111. Plane area; 112. Tail mounting head; 113. Positioning rib; 114. Mounting head contact; 201. Rectangular plug; 202. Wing mounting screw hole; 203. Folding wing; 204. Wing slot; 205. Wing detection contact; 302. Circular mounting seat A screw hole; 303. Circular mounting seat B screw hole; 304. Rectangular slot; 305, circular mount C screw hole; 306, circular mount A contact; 307, wing rod connecting tube; 308, circular mount B contact; 401, rectangular mount A screw hole; 402, rectangular mount B screw hole; 403, rectangular mount contact; 404, control circuit hole; 501, rotor rod; 502, rotor motor; 601, tail plug; 602, positioning groove; 603, tail contact. DETAILED DESCRIPTION

[0027] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0028] This embodiment provides a two-in-one convertible drone, as shown in Figures 1 to 19 , comprising a fuselage 1 and fixed wings 2. Wing mounting sections are provided on both sides of the fuselage 1. These wing mounting sections are equipped with fixed wing connectors and two rotor rods 501, each of which is equipped with rotors 5. The two rotor rods 501 are arranged in a figure-eight pattern, with the coplanarity of the rotors 5 on the two rotor rods 501 parallel to the coplanarity of the two rotor rods 501. The fixed wing connectors are used for removable mounting of the fixed wings 2. The fixed wing connectors are located between the two rotor rods 501, with the wing surfaces of the fixed wings 2 mounted on the fixed wing connectors perpendicular to the coplanarity of the two rotor rods 501. The orientation of the wing mounting sections can be changed, with the coplanarity of the two rotor rods 501 being able to be perpendicular or parallel to the length of the fuselage 1 along the path of the wing mounting sections' change in orientation, thereby enabling both fixed wing and helicopter modes.

[0029] Helicopter mode: As shown in Figures 1 and 12, this is the first form of change in the orientation of the wing mounting portion. When the coplanarity of the two rotor rods 501 is parallel to the length direction of the fuselage 1, the rotors 5 on the two rotor rods 501 are set horizontally upward (towards the top of the machine), which can generate upward lift. The fixed wings 2 are not installed or are removed. At this time, the UAV is in helicopter mode and can have the flight characteristics of a helicopter UAV, can take off and land vertically, and can hover for a long time.

[0030] Fixed-wing mode: As shown in Figures 2, 3 and 6, this is the second form of changing the orientation of the wing mounting portion. When the coplanarity of the two rotor rods 501 is perpendicular to the length direction of the fuselage 1, the rotors 5 on the two rotor rods 501 are arranged vertically forward (toward the nose), which can generate backward (toward the tail) propulsion force. The fixed wing 2 is installed on the fixed-wing connection part. At this time, the UAV is in fixed-wing mode, which can have the flight characteristics of a fixed-wing and rotor composite UAV, with a fast flight speed, relatively low energy consumption, and high wind resistance.

[0031] According to different needs, by changing the direction of the wing mounting part and coordinating with the disassembly and assembly of the fixed wing 2, the two modes can be switched on the same drone. There is no need to carry two different types of drones, which reduces equipment costs and space occupancy, and is convenient for deployment and carrying.

[0032] In one embodiment, as shown in Figures 1 to 19 , the wing mounting portion is a circular mounting base 3. The rotor rod 501 and the fixed wing connection portion are located on the circular surface of the circular mounting base 3. Circular mounting base 3 is provided with screw holes 302 for circular mounting base A and screw holes 303 for circular mounting base B. The line connecting the center of circular mounting base A 302 and circular mounting base 3 is perpendicular to the coplanarity of the two rotor rods 501. Circular mounting base A screw hole 302 is located on the dorsal side of the rotor 5. The line connecting the center of circular mounting base B screw hole 303 and circular mounting base 3 is coplanar with the two rotor rods 501. Circular mounting grooves 101 are provided on both sides of the fuselage 1. These grooves 101 mate with the circular mounting base 3 and facilitate its installation. A circular mounting slot screw hole 102 is provided on the side wall of the circular mounting slot 101 , and the circular mounting slot screw hole 102 passes through the bottom of the fuselage 1 . The line connecting the circular mounting slot screw hole 102 and the center of the circular mounting slot 101 is perpendicular to the length direction of the fuselage 1 .

[0033] Installation Principle: After inserting the circular mounting base 3 into the circular mounting slot 101, aligning the screw holes 302 of the circular mounting base A with the screw holes 102 of the circular mounting slot and screwing in the screws, the coplanarity of the two rotor rods 501 will be parallel to the length of the fuselage 1. (See Figure 1.) Without or without the fixed wing 2, the drone will be in helicopter mode. However, aligning the screw holes 303 of the circular mounting base B with the screw holes 102 of the circular mounting slot and screwing in the screws will cause the coplanarity of the two rotor rods 501 to be perpendicular to the length of the fuselage 1. (See Figure 6.) Installing the fixed wing 2 will put the drone in fixed-wing mode. (See Figures 2 and 3.)

[0034] In one embodiment, as shown in Figures 1 to 19 , the fixed wing connection portion is a rectangular slot 304 provided on the circular mounting base 3. The rectangular slot 304 is located between the two rotor rods 501, with its length perpendicular to the coplanar plane of the two rotor rods 501. A screw hole 303 for circular mounting base B is located at one end of the rectangular slot 304, while a screw hole 305 for circular mounting base C is provided at the other end. A rectangular plug 201 is provided at the base of the fixed wing 2, which mates with and is inserted into the rectangular slot 304. Wing mounting screw holes 202 are provided on the rectangular plug 201. With the wing mounting screw holes 202 oriented toward the circular mounting base C screw holes 305, the rectangular plug 201 is inserted into the rectangular slot 304. The wing mounting screw holes 202 align with the circular mounting base C screw holes 305. The screws are then tightened, completing the installation of the fixed wing 2 and the circular mounting base 3.

[0035] To detect whether the circular mounting base 3 and the fixed wing 2 are properly installed, in one embodiment, as shown in Figures 1 to 19, circular mounting base A contacts 306 are provided on the circumference of the circular mounting base 3. Circular mounting base A contacts 103 and circular mounting base B contacts 104 are provided within the circular mounting groove 101. Circular mounting base A contacts 103 must be positioned to ensure that when the circular mounting base A screw holes 302 and the circular mounting groove screw holes 102 are aligned, circular mounting base A contacts 306 and circular mounting groove A contacts 103 are in contact and conductive contact, allowing the UAV control system to detect the state of the rotor 5 later, as shown in Figure 19. Circular mounting groove B contacts 104 must be positioned to ensure that when the circular mounting base B screw holes 303 and the circular mounting groove screw holes 102 are aligned, circular mounting base A contacts 306 and circular mounting groove B contacts 104 are in contact and conductive contact, allowing the UAV control system to detect the state of the rotor 5 later, as shown in Figure 19.

[0036] A circular mounting base B contact 308 is located within the rectangular slot 304. Wing detection contacts 205 are located on the rectangular plug 201. When the circular mounting base B contact 308 and wing detection contacts 205 are aligned, and the circular mounting base C screw hole 305 aligns with the wing mounting screw hole 202, the wing detection contacts 205 and circular mounting base B contact 308 are in contact and conductive, allowing the drone control system to detect whether a fixed wing is installed, as shown in Figure 19.

[0037] Furthermore, in one embodiment, as shown in Figures 1 to 19 , the wing mounting portion can also be a rectangular mounting base 4. A rotor rod 501 is located on the front of the rectangular mounting base 4, with the width of the rectangular mounting base 4 perpendicular and coplanar with the two rotor rods 501. The area between the two rotor rods 501 on the rectangular mounting base 4 serves as the fixed wing connection portion. Screw holes 401 for rectangular mounting base A and 402 for rectangular mounting base B are provided on the side and bottom surfaces of the rectangular mounting base 4, respectively.

[0038] The fuselage 1 is provided with vertical rectangular slots 105 and horizontal rectangular slots 106 on both sides, both of which mate with the rectangular mounting base 4. The length of the vertical rectangular slot 105 is perpendicular to the length of the fuselage 1, while the length of the horizontal rectangular slot 106 is in the same direction as the length of the fuselage 1. The vertical and horizontal rectangular slots 105 and 106 intersect, and the intersection of the vertical and horizontal rectangular slots 105 and 106 corresponds to the fixed wing connection. The vertical rectangular slots 105 are provided with Rectangular Slot A screw holes 107, which mate with Rectangular Slot A screw holes 401 of the rectangular mounting base 4. The horizontal rectangular slots 106 are provided with Rectangular Slot B screw holes 108, which mate with Rectangular Slot B screw holes 402 of the rectangular mounting base 4. Both Rectangular Slot A screw holes 107 and Rectangular Slot B screw holes 108 run through the bottom of the fuselage 1.

[0039] The base of the fixed wing 2 is equipped with a rectangular plug 201, which mates with both the vertical rectangular slot 105 and the horizontal rectangular slot 106. It also has a wing slot 204, which is designed to be inserted into the fixed wing connection portion of the fixed wing 2. Rectangular plug 201 has wing mounting screw holes 202. With the wing mounting screw holes 202 of rectangular plug 201 facing the screw holes 108 of rectangular slot B, insert rectangular plug 201 into horizontal rectangular slot 106. Wing mounting screw holes 202 will align with the screw holes 108 of rectangular slot B. Tighten the screws, and the fixed wing 2 and rectangular mounting base 4 are installed.

[0040] Installation Principle: If the rectangular mount 4 is inserted into the horizontal rectangular slot 106, the screw holes 401 of the rectangular mount A are aligned with the screw holes 107 of the rectangular slot A, and the screws are screwed in, the rectangular mount 4 is installed. If the fixed wing 2 is not installed or the fixed wing 2 is removed, the rotor 5 is now facing horizontally upward, and the UAV is in helicopter mode. If the rectangular mount 4 is inserted into the vertical rectangular slot 105, the screw holes 401 of the rectangular mount A are aligned with the screw holes 107 of the rectangular slot A, and the screws are screwed in, the rectangular mount 4 is installed. Insert the wing slot 204 of the rectangular plug 201 into the fixed wing connection portion of the fixed wing 2, and insert the rectangular plug 201 into the horizontal rectangular slot 106. At this time, the rotor 5 is facing horizontally forward, the fixed wing 2 is set horizontally, and the UAV is in fixed wing mode.

[0041] Furthermore, in one embodiment, as shown in Figures 1 to 19 , rectangular mounting seat contacts 403 are provided on rectangular mounting seat 4. Rectangular slot A contacts 109 are provided within vertical rectangular slot 105. When rectangular slot A contacts 109 are positioned such that rectangular mounting seat A screw holes 401 and 107 are aligned, rectangular slot A contacts 109 and rectangular mounting seat contacts 403 are in contact and conduction, allowing the UAV control system to detect the state of rotor 5, as shown in Figure 19 . Rectangular slot B contacts 110 are provided within horizontal rectangular slot 106. When rectangular slot B contacts 110 are positioned such that rectangular mounting seat B screw holes 402 and 108 are aligned, rectangular slot B contacts 110 and rectangular mounting seat contacts 403 are in contact and conduction, allowing the UAV control system to detect the state of rotor 5, as shown in Figure 19 . The rectangular plug 201 is provided with a wing detection contact 205. After the rectangular plug 201 is inserted into the horizontal rectangular slot 106, the wing detection contact 205 is in contact with the rectangular slot B contact 110 and is connected, so that the UAV control system can detect whether the fixed wing 2 is installed in the later stage, as shown in Figure 19.

[0042] In one embodiment, as shown in Figures 1 to 19 , regardless of whether the wing mounting portion is a rectangular mounting base 4 or a circular mounting base 3, the rotor rod 501 and the wing mounting portion are connected via a wing rod connecting tube 307. The wing rod connecting tube 307 is pre-installed on the rectangular mounting base 4 or the circular mounting base 3, and then the rotor rod 501 is inserted into the wing rod connecting tube 307 and fixedly connected, completing the installation of the rotor rod 501. The fixing method includes, but is not limited to, welding, threading, and screwing.

[0043] In one embodiment, as shown in Figures 1 to 19 , a rotor motor 502 is provided at the end of a rotor rod 501, and rotor 5 is mounted on rotor motor 502 to drive the rotation of rotor 5. If the wing mounting portion is a rectangular mounting seat 4, a control line hole 404 is also provided, through which control cables and power cables are connected to rotor motor 502. If the wing mounting portion is a circular mounting seat 3, a cable hole is also provided for connecting control cables and power cables to rotor motor 502. Preferably, rotor rod 501 is a hollow rod for routing cables.

[0044] In one embodiment, as shown in FIG. 1 to FIG. 19 , the fuselage 1 is streamlined as a whole, such as being configured as an ellipsoid, with the two tips of the ellipsoid being the nose and the tail, respectively, which can effectively reduce wind resistance.

[0045] Furthermore, in one embodiment, as shown in Figures 1 to 19 , both sides and the bottom of the fuselage 1 are provided with flat areas 111. The flat areas 111 on both sides facilitate the installation of circular mounting slots 101 or vertical rectangular slots 105 and horizontal rectangular slots 106. The flat area 111 on the bottom facilitates the installation of structures such as landing gear.

[0046] In one embodiment, as shown in Figures 1 to 19 , the tail portion of the fuselage 1 is provided with an empennage mounting head 112 for mounting an empennage 6. If the fixed wing 2 is of the type with a flap 203 at the tip, the empennage 6 is not required. However, if the fixed wing 2 is of the type without a flap 203 at the tip, the empennage 6 is required.

[0047] Furthermore, in one embodiment, as shown in Figures 1 to 19, the tail wing mounting head 112 is a tubular structure, and the tail wing 6 is provided with a tail wing plug 601 for inserting into the tail wing mounting head 112. The inner wall of the tail wing mounting head 112 is provided with a positioning ridge 113, and the tail wing plug 601 is provided with a positioning groove 602. The positioning groove 602 cooperates with the positioning ridge 113 to guide the insertion of the tail wing plug 601 into the tail wing mounting head 112, so that the tail wing plug 601 can only move along the axial direction of the tail wing mounting head 112 and cannot rotate. After the tail wing plug 601 is inserted into the tail wing mounting head 112, it can be fixed with screws, that is, corresponding screw holes are provided on the tail wing plug 601 and the tail wing mounting head 112. A mounting head contact 114 is provided in the tail wing mounting head 112, and a tail wing contact 603 is provided on the tail wing plug 601. When the screw holes of the tail wing plug 601 and the tail wing mounting head 112 are aligned, the mounting head contact 114 and the tail wing contact 603 are in contact and conductive, so that the UAV control system can detect whether the tail wing 6 is installed in the later stage, as shown in Figure 19.

[0048] In one embodiment, as shown in Figures 1 to 19, the drone is equipped with a drone control system that cooperates with various circuit contacts for detecting modes and states, and executes a control logic algorithm adapted to the model based on the detected information.

[0049] After the drone control system is powered on, it first checks whether rotor 5 is installed horizontally. If so, the drone is controlled using the multi-rotor drone control algorithm. If not, it checks whether rotor 5 is installed vertically. If not, an abnormality warning is issued. If so, it checks whether fixed-wing 2 is installed. If not, an abnormality warning is issued. If fixed-wing 2 is installed, it checks whether tail 6 is installed. If tail 6 is not installed, the drone is controlled using the tailless fixed-wing drone control algorithm. If tail 6 is installed, the drone is controlled using the tail-supported fixed-wing drone control algorithm.

[0050] The rotor status detection information circuit connection is shown in Figure 17. Information is sent from interface I, passing through circular mounting base contact A 306. If circular mounting base contact A 306 connects to circular mounting slot contact A 103, interface A receives the information, indicating that rotor 5 is installed horizontally. If circular mounting base contact A 306 connects to circular mounting slot contact B 104, interface B receives the information. If received at interface B, it indicates that rotor 5 is installed vertically. For rectangular mounting base 4, if rectangular mounting base contact 403 connects to rectangular slot contact B 110, interface A receives the information, indicating that rotor 5 is installed horizontally. If rectangular mounting base contact 403 connects to rectangular slot contact A 109, interface B receives the information. If received at interface B, it indicates that rotor 5 is installed vertically.

[0051] The tail 6 detection connection is shown in Figure 18. The information is sent by the T interface. If the installation head contact 114 is connected to the tail contact 603, the R interface receives the information. If the signal is connected, it means that the tail 6 has been installed. If it is not connected, it means that it has not been installed.

[0052] The fixed wing 2 can be set up with reference to Figure 18. The information is sent by the T interface. If the rectangular slot B contact 110 is connected to the wing detection contact 205, the R interface receives the information. If the signal is conductive, it means that the fixed wing 2 has been installed. If it is not conductive, it means that it has not been installed.

[0053] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only intended to help understand the method and core concept of the present invention. At the same time, those skilled in the art will find that the specific implementation methods and application scopes may vary based on the concept of the present invention. In summary, the contents of this specification should not be construed as limiting the present invention.

Claims

1. A two-in-one convertible drone, characterized in that, It includes a fuselage and a fixed wing. On both sides of the fuselage, there are wing mounting parts with variable orientations. On the wing mounting parts, there are two rotor rods with built-in rotors and a fixed wing connection part for detachably mounting the fixed wing. The two rotor rods are arranged in a figure-eight pattern, and the coplanar plane of the rotors on the two rotor rods is parallel to the coplanar plane of the two rotor rods. The fixed wing connection part is located between the two rotor rods, and the wing surface of the fixed wing mounted on the fixed wing connection part is perpendicular to the coplanar plane of the two rotor rods. The coplanar plane of the two rotor rods is on the path of the orientation change of the wing mounting part and can be perpendicular to the length direction of the fuselage or parallel to the length direction of the fuselage.

2. The two-in-one convertible drone according to claim 1, wherein, The wing mounting part is a circular mounting seat. The rotor rods and the fixed wing connection part are located on the circular surface of the circular mounting seat. On the circumference of the circular mounting seat, there are circular mounting seat A screw holes and circular mounting seat B screw holes. The line connecting the circular mounting seat A screw hole and the center of the circular mounting seat is perpendicular to the coplanar plane of the two rotor rods. The circular mounting seat A screw hole is located on the back side of the orientation of the rotor. The line connecting the circular mounting seat B screw hole and the center of the circular mounting seat is on the coplanar plane of the two rotor rods. On both sides of the fuselage, there are circular mounting grooves matching the circular mounting seat. On the side wall of the circular mounting groove, there are circular mounting groove screw holes penetrating the bottom of the fuselage. The line connecting the circular mounting groove screw hole and the center of the circular mounting groove is perpendicular to the length direction of the fuselage.

3. The two-in-one convertible drone according to claim 2, characterized in that, The fixed wing connection part is a rectangular slot provided on the circular mounting seat. The length direction of the rectangular slot is perpendicular to the coplanar plane of the two rotor rods. The circular mounting seat B screw hole is located at one end of the rectangular slot, and at the other end of the rectangular slot, there is a circular mounting seat C screw hole. At the root of the fixed wing, there is a rectangular plug matching the rectangular slot, and on the rectangular plug, there are wing mounting screw holes matching the circular mounting seat C screw hole.

4. The two-in-one convertible drone according to claim 3, characterized in that, On the circumference of the circular mounting seat, there are circular mounting seat A contacts. In the circular mounting groove, there are circular mounting groove A contacts and circular mounting groove B contacts. When the circular mounting seat A screw hole and the circular mounting groove screw hole are aligned, the circular mounting seat A contact and the circular mounting groove A contact are in contact. When the circular mounting seat B screw hole and the circular mounting groove screw hole are aligned, the circular mounting seat A contact and the circular mounting groove B contact are in contact. In the rectangular slot, there are wing detection contacts, and on the rectangular plug, there are wing detection contacts. When the circular mounting seat C screw hole and the wing mounting screw hole are aligned, the wing detection contacts and the circular mounting seat B contact are in contact.

5. The two-in-one convertible drone according to claim 1, characterized in that, The wing mounting part is a rectangular mounting base. The rotor rod is located on the front surface of the rectangular mounting base. The width direction of the rectangular mounting base is perpendicular to the coplanar plane where the two rotor rods are located. The area of the rectangular mounting base between the two rotor rods is the fixed-wing connection part. The side surface and the bottom surface of the rectangular mounting base are respectively provided with a rectangular mounting base A screw hole and a rectangular mounting base B screw hole. On both sides of the fuselage, there are vertical rectangular grooves and horizontal rectangular grooves that match the rectangular mounting base. The length direction of the vertical rectangular groove is perpendicular to the length direction of the fuselage. The length direction of the horizontal rectangular groove is the same as the length direction of the fuselage. The vertical rectangular groove and the horizontal rectangular groove intersect. The intersection area of the vertical rectangular groove and the horizontal rectangular groove corresponds to the fixed-wing connection part. The vertical rectangular groove is provided with a rectangular groove A screw hole that matches the rectangular mounting base A screw hole. The horizontal rectangular groove is provided with a rectangular groove B screw hole that matches the rectangular mounting base B screw hole. Both the rectangular groove A screw hole and the rectangular groove B screw hole penetrate through the bottom of the fuselage. The root of the fixed wing is provided with a rectangular plug that matches the vertical rectangular groove and the horizontal rectangular groove. The rectangular plug is provided with a wing slot for inserting on the fixed-wing connection part. The rectangular plug is provided with a wing mounting screw hole that matches the rectangular groove B screw hole.

6. The two-in-one convertible drone according to claim 5, characterized in that, The rectangular mounting base is provided with a rectangular mounting base contact. The vertical rectangular groove and the horizontal rectangular groove are respectively provided with a rectangular groove A contact and a rectangular groove B contact. The rectangular plug is provided with a wing detection contact.

7. The two-in-one convertible drone according to claim 2 or 5, characterized in that, The rotor rod is connected to the wing mounting part through a wing rod connecting pipe.

8. The two-in-one convertible drone according to claim 2 or 5, characterized in that, The fuselage is ellipsoidal, and the two tips of the ellipsoid are the nose and the tail respectively.

9. The two-in-one convertible drone according to claim 8, wherein, Both sides and the bottom of the fuselage are provided with flat areas.

10. The two-in-one convertible drone according to claim 8, characterized in that, The tail of the fuselage is provided with a tail fin mounting head for mounting a tail fin.

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