A detachable rotor unmanned aerial vehicle frame, a detachable method and an unmanned aerial vehicle

Abstract

The application discloses a detachable rotor unmanned aerial vehicle frame, a dismounting method and an unmanned aerial vehicle, and solves the problem of inconvenient dismounting of a large-volume unmanned aerial vehicle. The detachable rotor unmanned aerial vehicle frame comprises a guide rail, a wedge block, a landing gear and a rotor. A sliding groove is formed in the guide rail, the width of the bottom of the sliding groove is greater than the opening of the sliding groove, and one end of the sliding groove is closed and the other end is open. The wedge block is provided with a first strip-shaped protrusion which is the same in shape as the cross section of the sliding groove. The wedge block is slidably connected with the sliding groove of the guide rail through the first strip-shaped protrusion. The rotor is fixedly arranged on the side of the wedge block away from the first strip-shaped protrusion. The landing gear is fixedly arranged on the side of the guide rail away from the sliding groove. The application ensures safe and reliable flight of the unmanned aerial vehicle in high altitude, and can also realize quick dismounting and flexible transportation of a large-volume multi-rotor unmanned aerial vehicle platform in the wild.

Description

Technical Field

[0001] This application relates to the field of multi-rotor unmanned aerial vehicle (UAV) structural technology, and in particular to an easily detachable rotor UAV frame, a disassembly and assembly method, and the UAV itself. Background Technology

[0002] Traditional rotary-wing drones have light payloads, short flight times, and low flight altitudes, making it difficult to carry high-payload radio equipment for extended periods. However, advancements in semiconductor chips and radio detection technology have significantly improved the transmission power, detection range, and anti-jamming capabilities of onboard radio equipment. As drone payloads increase in weight, flight time, and altitude, traditional rotary-wing drones can no longer meet the demands of carrying high-power, high-payload radio equipment for extended periods. Multi-rotor drones based on lightweight, high-strength carbon fiber, with their advantages of large payload capacity, long flight time, and high flight altitude, have been widely adopted in the design of multi-rotor drones.

[0003] However, large-volume multi-rotor carbon fiber drones have poor maneuverability in the field, and are difficult to assemble, disassemble, and transport. Therefore, a drone frame structure that can be flexibly assembled, disassembled, and transported, while ensuring its safety after installation, is needed. Summary of the Invention

[0004] This application provides an easily detachable rotorcraft drone frame, a disassembly and assembly method, and the drone itself, solving the problem of inconvenient disassembly and assembly of large-volume drones.

[0005] This application provides a detachable rotorcraft unmanned aerial vehicle (UAV) frame, comprising a guide rail, a wedge, a landing gear, and a rotor. The guide rail has a groove, the bottom width of which is greater than the opening, with one end closed and the other open. The wedge has a first strip-shaped protrusion with the same cross-sectional shape as the groove. The wedge is slidably connected to the groove of the guide rail via the first strip-shaped protrusion. The rotor is fixedly mounted on the side of the wedge away from the first strip-shaped protrusion. The landing gear is fixedly mounted on the side of the guide rail away from the groove.

[0006] Furthermore, it also includes a locking pin. The guide rail has a through hole. The through hole extends from the side of the guide rail perpendicular to the length of the slide groove into the slide groove. The wedge has a locking pin groove. The locking pin passes through the through hole and inserts into the locking pin groove on the wedge to lock the wedge and the guide rail.

[0007] Furthermore, it also includes a center plate. The rotor is disposed on the side edge of the center plate. The wedge is fixed to the bottom surface of the center plate.

[0008] Furthermore, it also includes a first connecting member. A groove parallel to the length direction of the guide rail groove is provided on the opposite side. The first connecting member is a strip-shaped structure perpendicular to the length direction of the groove. The first connecting member has a first recess facing the groove. When the first connecting member is fixedly connected to the guide rail, the first recess and the groove cooperate to form a through cavity. A rod structure on the landing gear passes through the through cavity, fixing the landing gear to the guide rail.

[0009] More preferably, the locking pin is a plate-like structure, with serrations parallel to the plate surface at one end and an ear plate perpendicularly disposed at the other end. The ear plate has threaded holes parallel to the plate surface. The guide rail has screw holes, and the plate-like structure is inserted into the through hole and the locking pin groove, with the threaded hole and screw hole aligned. The shapes of the through hole and the locking pin groove are adapted to the plate-like structure of the locking pin.

[0010] Furthermore, it also includes a second connecting member. The wedge block has a second strip-shaped protrusion parallel to the length direction of the first strip-shaped protrusion on the side facing away from the first strip-shaped protrusion. Fixing wings are provided on both sides of the wedge block perpendicular to the first and second strip-shaped protrusions. The second connecting member is a strip-shaped structure perpendicular to the length direction of the second strip-shaped protrusion. A center plate is fixedly connected to one side of the second connecting member, and a second recess is provided on the other side to fit snugly against the second strip-shaped protrusion. When the second strip-shaped protrusion fits into the second recess, its side abuts against and fixes the fixing wings.

[0011] Furthermore, two wedges are fixedly connected to the bottom surface of the center plate, with their first strip-shaped protrusions parallel to each other. The landing gear has two horizontally arranged rod sections. These two rod sections are at the same horizontal height and parallel to each other. Each of the two rod sections has a guide rail that corresponds to and engages with the two wedges.

[0012] Furthermore, the second connector has a threaded hole, and the fixed wing has a countersunk screw threaded through hole opposite to the threaded hole. The fixed wing and the second connector are connected by screws that are recessed into the wedge.

[0013] This application also provides a rotary-wing unmanned aerial vehicle (UAV) using the easily detachable rotary-wing UAV frame described in any of the above embodiments, and further includes a fuselage. The fuselage is fixedly connected to the opposite side of the recessed side of the first connector.

[0014] This application also provides a method for disassembling and assembling an easily detachable rotorcraft drone frame, using the easily detachable rotorcraft drone frame described in any of the above embodiments, comprising the following steps:

[0015] Slide the wedge into the guide rail from one end of the guide rail opening, so that the through hole on the guide rail is aligned with the locking pin groove on the wedge.

[0016] Insert the locking pin into the through hole and the locking pin groove;

[0017] Tighten the wedge block by screwing it into the threaded hole on the locking pin lug and the screw hole on the guide rail.

[0018] The above-described technical solutions adopted in the embodiments of this application can achieve the following beneficial effects:

[0019] This application completes the disassembly and assembly of the flight control cabin, payload cabin, and landing gear of a large-volume multi-rotor UAV platform. Utilizing guide rails and locking pins, the disassembly and assembly method ensures safe and reliable high-altitude flight of the UAV while enabling rapid disassembly and assembly of the large-volume multi-rotor UAV platform in the field, facilitating flexible transportation. Attached Figure Description

[0020] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0021] Figure 1 This is a structural diagram of an easily detachable rotorcraft unmanned aerial vehicle (UAV) according to this application;

[0022] Figure 2 This is a flowchart illustrating a method for disassembling and assembling an easily detachable rotorcraft frame, as described in an embodiment of this application. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0024] The technical solutions provided by the various embodiments of this application are described in detail below with reference to the accompanying drawings.

[0025] Figure 1 This is a structural diagram of an easily detachable rotorcraft drone according to this application.

[0026] This application provides an easily detachable rotorcraft frame, comprising a guide rail 1, a wedge block 2, a landing gear 3, and a rotor 4.

[0027] The guide rail has a groove 11, the bottom width of which is greater than the opening of the groove, and one end of the groove is closed while the other end is open.

[0028] The wedge has a first strip-shaped protrusion 21 with the same cross-sectional shape as the groove.

[0029] The wedge is slidably connected to the guide rail through the first strip-shaped protrusion.

[0030] The rotor is fixedly mounted on the side of the wedge block away from the first strip-shaped protrusion.

[0031] The rotor can be directly fixed to the wedge block, or multiple rotors can be set on a central plate and then fixedly connected to the wedge block through the central plate.

[0032] For example, it further includes a center plate 6.

[0033] The rotor is mounted on the side edge of the center plate. The wedge is fixed to the bottom surface of the center plate.

[0034] Furthermore, it also includes a second connector 5.

[0035] The wedge has a second strip-shaped protrusion parallel to the length direction of the first strip-shaped protrusion on the side facing away from the first strip-shaped protrusion, and fixed wings are provided on both sides of the wedge perpendicular to the first and second strip-shaped protrusions.

[0036] The second connector is a strip-shaped structure that is perpendicular to the length direction of the second strip-shaped protrusion.

[0037] The second connector has a fixed connection to the center plate on one side and a second recess 51 on the other side that fits snugly against the second strip-shaped protrusion.

[0038] When the second strip-shaped protrusion fits into the second recess, its side abuts against and securely connects to the fixed wing.

[0039] For example, the second connector is a rectangular strip structure with a semi-circular notch on one side. The second strip-shaped protrusion on the wedge is semi-cylindrical. The semi-circular notch on the second connector matches the second strip-shaped protrusion; during installation, the semi-circular notch on the second connector fits snugly against the second strip-shaped protrusion, and the side with the semi-circular notch fits against the fixing wing. The fixing wing and the second connector are fixedly connected by screws. The center plate is a rectangular plate structure, and multiple rotors are respectively arranged on the side edges around the center plate. The opposite side of the semi-circular notch of the second connector is fixedly connected to the bottom surface of the center plate.

[0040] Furthermore, the second connector has a threaded hole, and the fixed wing has a countersunk screw threaded through hole opposite to the threaded hole. The fixed wing and the second connector are connected by screws that are recessed into the wedge.

[0041] The landing gear is fixedly mounted on the side of the guide rail away from the slide.

[0042] Furthermore, it also includes a first connector 7.

[0043] The guide rail groove is provided with a groove 12 parallel to the length direction of the groove on the opposite side.

[0044] The first connector is a strip structure that is perpendicular to the length direction of the groove.

[0045] The first connector has a first recess 71 facing the groove direction.

[0046] When the first connector is fixedly connected to the guide rail, the first recess and the groove cooperate to form a through cavity.

[0047] The landing gear has a rod structure that passes through the through cavity, so that the landing gear is fixedly connected to the guide rail.

[0048] For example, the landing gear is a structure formed by a rigid round rod, and the part connecting the landing gear to the guide rail is also a rod. Therefore, the first recess is a semi-circular recess adapted to the shape of the rod, and the groove is also a semi-circular groove. When the guide rail and the first connecting piece are fixedly connected, the first recess and the groove form a cylindrical through cavity. The cross-sectional radius of the through cavity is slightly larger than the radius of the landing gear rod. By placing the landing gear rod in the through cavity, the fixed connection between the landing gear and the guide rail is achieved.

[0049] It should be noted that the first connector and the second connector can be one or multiple parallel connections; no further limitations are made here.

[0050] Furthermore, it also includes a locking pin 8.

[0051] The guide rail has a through hole.

[0052] The through hole extends from the side of the guide rail perpendicular to the length of the slide groove into the slide groove.

[0053] The wedge has a locking pin groove.

[0054] The locking pin passes through the through hole and is inserted into the locking pin groove on the wedge to lock the wedge and the guide rail.

[0055] Furthermore, the locking pin is a plate-like structure 81. One end of the plate-like structure has serrations parallel to the plate surface, and the other end has a vertically arranged ear plate 82. The ear plate has a threaded hole 83 parallel to the plate surface. The guide rail has screw holes, and the plate-like structure is inserted into the through hole and the locking pin groove, with the threaded hole and screw hole facing each other. The shapes of the through hole and the locking pin groove are adapted to the plate-like structure of the locking pin.

[0056] For example, the entire disassembly and assembly structure is divided into two parts: one part is the connection structure between the center plate and the wedge block, and the other part is the connection structure between the landing gear and the guide rail.

[0057] Connection structure between the center plate and the wedge: The second connector has a threaded hole. The wedge is installed on the second connector and directly fixed with the screw. The screw is recessed into the wedge workpiece through the countersunk screw hole inside the wedge.

[0058] Landing gear and guide rail connection structure: The wedge block guide rail and the landing gear are fixed together by a first connector. The mounting hole of the first connector is designed as a through hole. The wedge block guide rail and the landing gear connecting block are fixed by countersunk screws and nuts. The through hole is set outward perpendicular to the length direction of the guide rail groove.

[0059] The easily detachable rotorcraft frame described in this application can be fixed with one wedge and one guide rail, or multiple wedges and guide rails can be fixed together. However, fixing with only one wedge results in poor stability, while an excessive number increases cost. Therefore, preferably, two wedges are fixedly connected to the bottom surface of the center plate, with their first strip-shaped protrusions parallel to each other. The landing gear has two horizontally arranged rod sections. The two rod sections are at the same horizontal height and parallel to each other. Each of the two rod sections is provided with a guide rail that corresponds to and engages with the two wedges.

[0060] This application also provides a rotary-wing unmanned aerial vehicle (UAV) using the easily detachable rotary-wing UAV frame described in any of the above embodiments, and further includes a fuselage. The fuselage is fixedly connected to the opposite side of the recessed side of the first connector.

[0061] Figure 2 This is a flowchart illustrating a method for disassembling and assembling an easily detachable rotorcraft frame, as described in an embodiment of this application.

[0062] This application also provides a method for disassembling and assembling an easily detachable rotorcraft drone frame, using the easily detachable rotorcraft drone frame described in any of the above embodiments, comprising the following steps:

[0063] Step 101: Slide the wedge into the guide rail from one end opening, so that the through hole on the guide rail is aligned with the locking pin groove on the wedge.

[0064] For example, the length of the wedge is the same as the groove of the guide rail. The wedge is slid into the guide rail until it abuts against the top of the guide rail, aligning the notch on the guide rail with the notch on the slider. At the same time, the through hole on the guide rail is aligned with the locking pin groove on the wedge.

[0065] Step 102: Insert the locking pin into the through hole and the locking pin groove;

[0066] Insert the locking pin into the locking pin groove, aligning the serrated structure on the locking pin with the serrated structure of the through hole on the guide rail. It also engages with the serrated structure of the locking pin groove on the wedge. By inserting the locking pin into the through hole and the locking pin itself, movement between the wedge and the guide rail along the length of the groove is prevented.

[0067] Step 103: Screw the wing screws into the threaded holes on the locking pin lugs and the screw holes on the guide rail to lock the wedge block to the guide rail.

[0068] Tighten the locking pin by screwing in the wing screw to ensure that the locking pin will not come off the guide rail and wedge, thus ensuring that the guide rail and wedge are locked.

[0069] This application addresses the structural design technology of rotary-wing unmanned aerial vehicles (UAVs) and proposes a method for disassembling and assembling multi-rotor UAV structures. Inside a large-volume UAV with a high payload capacity, portable disassembly of the flight control cabin, payload bay, and landing gear is achieved using structural components such as guide rails and anti-loosening nuts. Locking pins and butterfly screws enable rapid disassembly and assembly of large-volume multi-rotor UAV platforms with payloads exceeding 50kg and a maximum endurance of 30 minutes, facilitating flexible transportation. This ensures reliable flight operation of the UAV after installation.

[0070] To address the poor field maneuverability of large-volume multi-rotor carbon fiber UAVs, this invention involves disassembling and assembling the UAV structure. A closed guide rail method is used to facilitate the removal and installation of the landing gear, payload bay, and flight control bay. Locking pins and butterfly screws are then used to secure the connections, ensuring reliable flight after installation. This method can be used for the portable assembly, disassembly, and flexible transport of large-volume multi-rotor UAV platforms in the field, and has significant military implications.

[0071] The above description is merely an embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of this application should be included within the scope of the claims of this application.

Claims

1. A detachable rotorcraft drone frame, characterized in that, Includes guide rails, wedges, landing gear, and rotor; The guide rail has a groove, the bottom width of which is greater than the opening of the groove, and one end of the groove is closed while the other end is open. The wedge has a first strip-shaped protrusion with the same cross-sectional shape as the groove. The wedge is slidably connected to the guide rail through the first strip-shaped protrusion; The rotor is fixedly mounted on the side of the wedge block away from the first strip-shaped protrusion; The landing gear is fixedly mounted on the side of the guide rail away from the slide rail; It also includes the center plate; The rotor is mounted on the side edge of the center plate; The wedge is fixed to the bottom surface of the center plate; It also includes a second connector; The wedge has a second strip-shaped protrusion parallel to the length direction of the first strip-shaped protrusion on the side facing away from the first strip-shaped protrusion, and fixed wings are provided on both sides of the wedge perpendicular to the first and second strip-shaped protrusions. The second connector is a strip-shaped structure that is perpendicular to the length direction of the second strip-shaped protrusion; The second connector has a fixed connection center plate on one side and a second recess on the other side that fits tightly against the second strip-shaped protrusion. When the second strip-shaped protrusion fits into the second recess, its side abuts against and secures the connecting fixed wing. The second connector has a threaded hole, and the fixed wing has a countersunk screw threaded through hole opposite to the threaded hole; The fixed wing and the second connector are connected by screws driven into the wedge block; The second connector is multiple and is arranged at intervals along the length direction of the second strip-shaped protrusion of the wedge.

2. The easily detachable rotorcraft drone frame according to claim 1, characterized in that, It also includes a locking pin; The guide rail has a through hole; The through hole extends from the side of the guide rail perpendicular to the length of the slide groove into the slide groove; The wedge has a locking pin groove; The locking pin passes through the through hole and is inserted into the locking pin groove on the wedge to lock the wedge and the guide rail.

3. The easily detachable rotorcraft drone frame according to claim 1, characterized in that, It also includes a first connector; The guide rail groove is provided with a groove parallel to the length direction of the groove on the opposite side; The first connector is a strip structure arranged perpendicular to the length direction of the groove; The first connector has a first recess facing the groove direction; When the first connector is fixedly connected to the guide rail, the first recess and the groove cooperate to form a through cavity; The landing gear has a rod structure that passes through the through cavity, so that the landing gear is fixedly connected to the guide rail.

4. The easily detachable rotorcraft drone frame according to claim 2, characterized in that, The locking pin is a plate-shaped structure. One end of the plate-shaped structure is provided with serrations parallel to the plate surface, and the other end of the plate-shaped structure is provided with an ear plate perpendicularly. The ear plate has a threaded hole parallel to the plate surface of the plate-shaped structure. The guide rail is provided with screw holes, the plate-like structure is inserted into the through hole and the locking pin groove, and the threaded hole and screw hole are aligned. The through hole and the groove of the locking pin are adapted to the plate-like structure of the locking pin.

5. The easily detachable rotorcraft drone frame according to claim 1, characterized in that, Two wedges are fixedly connected to the bottom surface of the center plate, and their first strip-shaped protrusions are parallel to each other. The landing gear has two horizontally mounted rod sections; The two sections of the rod are at the same horizontal height and are parallel to each other; Each of the two rod sections is equipped with a guide rail that corresponds to and engages with two wedge blocks.

6. A rotary-wing unmanned aerial vehicle, characterized in that, The frame of the easily detachable rotary-wing UAV as described in any one of claims 1-5 also includes a fuselage; The fuselage is fixedly connected to the opposite side of the first recessed side of the first connector.

7. A method for disassembling and assembling an easily detachable rotorcraft drone frame, characterized in that, Using the easily detachable rotorcraft drone frame according to any one of claims 1-5, the steps include: Slide the wedge into the guide rail from one end of the guide rail opening, so that the through hole on the guide rail is aligned with the locking pin groove on the wedge. Insert the locking pin into the through hole and the locking pin groove; Tighten the wedge block by screwing it into the threaded hole on the locking pin lug and the screw hole on the guide rail.

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