A rack structure of a drone and a drone

Abstract

The utility model provides a kind of rack structure and unmanned aerial vehicle of unmanned aerial vehicle, it is related to unmanned aerial vehicle technical field, comprising: one middle frame and two end frames, two end frames are connected in the opposite two ends of middle frame respectively, middle frame and end frame are first material and second material respectively, the density of first material is less than the density of second material, the rigidity of second material is greater than the rigidity of first material, end frame is used to install the power system and transmission system of unmanned aerial vehicle;Solve the problem that oil-driven multi-rotor unmanned aerial vehicle lacks typical rack structure.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and more specifically, relates to a UAV frame structure and the UAV itself. Background Technology

[0002] Unmanned aerial vehicles (UAVs), as unmanned and reusable aircraft, can generally be divided into fixed-wing UAVs and rotary-wing UAVs according to their structural form. Currently, rotary-wing UAVs mainly include single-rotor with tail rotor layouts and coaxial dual-rotor layouts. These two types of unmanned helicopters are technologically mature and have a high market share. Next are cross-rotor and tilt-rotor UAVs, but their numbers are smaller, especially the latter, which is technically complex, has high development costs, and is difficult to put into practical use.

[0003] In recent years, multi-rotor drones have developed rapidly, but due to limitations in battery capacity, electric multi-rotor drones have very short payloads, flight times, and ranges. To improve flight time and range, hybrid electric multi-rotor drones and gasoline-powered multi-rotor drones have emerged, especially gasoline-powered multi-rotor drones, which have the ability to carry large payloads and have long flight times.

[0004] Generally, fixed-wing UAVs and unmanned helicopters use a frame and beam combination as their airframe structure, while multi-rotor UAVs are typically manufactured using carbon fiber rods through integral molding. However, for gasoline-powered multi-rotor UAVs, a typical structural form has not yet been observed. To meet their structural requirements and reduce costs, it is necessary to design a lightweight, high-strength, and high-rigidity airframe structure for gasoline-powered multi-rotor UAVs. This has become a crucial technical problem that must be solved in the development of large-scale gasoline-powered multi-rotor UAVs. Utility Model Content

[0005] The purpose of this invention is to provide a frame structure and an unmanned aerial vehicle (UAV) to solve the problem of the lack of a typical frame structure for gasoline-powered multi-rotor UAVs.

[0006] To achieve the above objectives, this utility model provides a frame structure for a drone, comprising:

[0007] The device comprises a central frame and two end frames, the two end frames being connected to opposite ends of the central frame. The central frame and the end frames are made of a first material and a second material, respectively. The density of the first material is less than that of the second material, and the stiffness of the second material is greater than that of the first material. The end frames are used to mount the power system and transmission system of the drone.

[0008] Optionally, the end frame is connected to the middle frame by bolts.

[0009] Optionally, the first material is aluminum or an aluminum alloy.

[0010] Optionally, the second material is steel.

[0011] Optionally, the central frame includes a plurality of first rectangular tubular components, which are welded together to form a cuboid frame.

[0012] Optionally, the two end frames are respectively connected to the two short sides of the cuboid frame.

[0013] Optionally, the end frame includes a plurality of second rectangular tubular components, which are welded together to form a rectangular frame.

[0014] Optionally, it also includes a first lug and a second lug, the first lug and the second lug being welded to one side of the end frame, the first lug being used to mount the landing gear, the second lug being used to connect to the middle frame, and a reinforcing member connecting the first lug and the second lug.

[0015] Optionally, the end frame is provided with a transmission system mounting hole and a power system mounting hole, and the middle frame is used to install the UAV's flight control system and fuel tank, and the middle frame is provided with a flight control system mounting hole and a fuel tank mounting hole.

[0016] This utility model also provides an unmanned aerial vehicle (UAV), including the aforementioned UAV frame structure and a power system, transmission system, flight control system, and fuel tank mounted thereon, wherein the transmission system is connected to a rotor system.

[0017] This utility model provides a frame structure for a drone and the drone itself. Its advantages are as follows: the frame structure of the drone adopts a modular design, which is easy to process and produce. It has a middle frame and end frames connected to opposite ends of the middle frame. The power system and transmission system of the drone are installed using the end frames with better rigidity, ensuring the installation strength and rigidity requirements. The middle frame is made of a lighter material, realizing a lightweight design.

[0018] Other features and advantages of this invention will be described in detail in the following detailed description section. Attached Figure Description

[0019] The above and other objects, features and advantages of the present invention will become more apparent from the accompanying drawings, in which like reference numerals generally represent like parts.

[0020] Figure 1 A modular front view schematic diagram of the frame structure of a drone according to an embodiment of the present invention is shown.

[0021] Figure 2 A modular side view schematic diagram of the frame structure of a drone according to an embodiment of the present invention is shown.

[0022] Figure 3 A front view schematic diagram of the frame structure of a drone according to an embodiment of the present invention is shown.

[0023] Figure 4 A side view of the frame structure of a drone according to an embodiment of the present invention is shown.

[0024] Figure 5 A schematic diagram of the structure of a drone according to an embodiment of the present invention is shown.

[0025] Explanation of reference numerals in the attached figures:

[0026] 1. Mid-frame; 2. End-frame; 3. Bolt; 4. First lug; 5. Second lug; 6. Reinforcing component; 7. First steel pipe fitting; 8. Second steel pipe fitting; 9. Third steel pipe fitting; 10. Fourth steel pipe fitting; 11. Fifth steel pipe fitting; 12. First aluminum pipe fitting; 13. Second aluminum pipe fitting; 14. Third aluminum pipe fitting; 15. Fourth aluminum pipe fitting; 16. Fifth aluminum pipe fitting; 17. Power system; 18. Transmission system; 19. Flight control system; 20. Rotor system. Detailed Implementation

[0027] Preferred embodiments of the present invention will now be described in more detail. While preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0028] like Figure 1 and Figure 2 As shown, this utility model provides a frame structure for a drone, comprising:

[0029] A central frame 1 and two end frames 2 are connected to opposite ends of the central frame 1. The central frame 1 and the end frames 2 are made of a first material and a second material, respectively. The density of the first material is less than that of the second material, and the stiffness of the second material is greater than that of the first material. The end frames 2 are used to install the power system 17 and the transmission system 18 of the UAV.

[0030] Specifically, to address the lack of a typical frame structure for gasoline-powered multi-rotor drones, the frame structure of the drone provided by this utility model adopts a modular design, which is easy to process and produce. It has a middle frame 1 and end frames 2 connected to opposite ends of the middle frame 1. The drone's power system 17 and transmission system 18 are installed using the end frames 2, which have better rigidity, to ensure the installation strength and rigidity requirements. The middle frame 1 is made of a lighter material to achieve a lightweight design.

[0031] Optionally, the end frame 2 is connected to the middle frame 1 by bolts 3.

[0032] Specifically, the end frame 2 and the middle frame 1 form an independent modular structure and are connected by bolts 3 for easy installation and disassembly.

[0033] Optionally, the first material is aluminum or an aluminum alloy.

[0034] Specifically, the central frame 1 is made of aluminum, which has sufficient strength while also being lightweight.

[0035] Alternatively, the second material is steel.

[0036] Specifically, the end frame 2 is a steel frame, which has sufficient strength and better rigidity, and is suitable for mounting the power system 17 and transmission system 18 of the UAV.

[0037] Optionally, the central frame 1 includes a plurality of first rectangular tubular components, which are welded together to form a cuboid frame.

[0038] Specifically, the rectangular frame design ensures better strength while maintaining the lightweight nature of the aluminum frame, resulting in structural reinforcement and improved stability.

[0039] In this embodiment, the aluminum frame is welded from rectangular aluminum tubes. In addition to machining the mounting holes, the internal support components have weight-reducing holes according to the actual situation to reduce the structural weight.

[0040] Optionally, the two end frames 2 are respectively connected to the two short sides of the cuboid frame.

[0041] Specifically, the aluminum frame is a cuboid truss welded from seamless rectangular aluminum tubes. The main rectangular aluminum tubes of the truss have longer sides and shorter sides. The aluminum tubes with longer sides are connected together to form a whole truss.

[0042] Optionally, the end frame 2 includes a plurality of second rectangular tubular components, which are welded together to form a rectangular frame.

[0043] Specifically, the steel frame is welded from rectangular steel tubes and has mounting holes for installing the transmission and power system 17 of the UAV. At the same time, the non-load-bearing parts of the steel frame have weight-reducing holes to reduce the structural weight.

[0044] Optionally, it also includes a first lug 4 and a second lug 5, which are welded to one side of the end frame 2. The first lug 4 is used to mount the landing gear, and the second lug 5 is used to connect to the middle frame 1. A reinforcing member 6 is connected between the first lug 4 and the second lug 5.

[0045] Specifically, a first lug 4 and a second lug 5 are welded to one side of the steel frame. The second lug 5 is used to connect with the aluminum frame and is fastened with bolts 3. The first lug 4 is used to connect with the landing gear.

[0046] Furthermore, bolt 3 is a high-strength bolt used to secure the second lug 5 to the aluminum frame, so that the steel frame and the aluminum frame form a whole, thus forming the main structure of the UAV.

[0047] In this embodiment, the first lug 4 and the second lug 5 are box-shaped lugs. The steel frame is connected to one side of the aluminum frame, forming an L-shaped connection structure on the short side of the aluminum frame. The second lug 5 is fastened to the aluminum frame by bolts 3. The first lug 4 is used to install the landing gear. The first lug 4 and the second lug 5 are connected by a rod-shaped reinforcing member 6 to increase the overall rigidity.

[0048] Optionally, the end frame 2 is provided with a transmission system 18 mounting hole and a power system 17 mounting hole, and the middle frame 1 is used to install the flight control system 19 and fuel tank of the UAV, and the middle frame 1 is provided with a flight control system 19 mounting hole and a fuel tank mounting hole.

[0049] Specifically, the drone's flight control system 19 and fuel tank can be mounted on an aluminum frame.

[0050] This utility model provides a frame structure that is simple in structure, high in strength, high in rigidity, and low in cost, suitable for gasoline-powered multi-rotor UAVs; in this embodiment, such as Figure 3 and Figure 4As shown, the end frame 2 is formed by welding together a first steel pipe 7, a second steel pipe 8, a third steel pipe 9, a fourth steel pipe 10, and a fifth steel pipe 11. The first steel pipe 7 is a three-section welded structure, while the others are formed by directly cutting steel pipes to specified dimensions. After welding, the first, second, third, fourth, and fifth steel pipes are annealed to eliminate welding stress. Furthermore, weight-reducing holes can be added as needed to reduce structural weight. The elongated holes on the first and fourth steel pipes 7 and 10, located away from the middle frame 1, are mounting holes for the transmission system 18. The holes on the first steel pipe 7 near the middle frame 1 and on the third steel pipe 9 are used to install pulleys and clutches. The fourth steel pipe 10... The holes near the central frame 1 are for mounting the engine, serving as mounting holes for the power system 17. The central frame 1 is formed by welding together a first aluminum tube 12, a second aluminum tube 13, a third aluminum tube 14, a fourth aluminum tube 15, and a fifth aluminum tube 16. The first aluminum tube 12 and the third aluminum tube 14 are seamless rectangular aluminum tubes with larger cross-sectional dimensions and are the main structural components. The second aluminum tube 13, the third aluminum tube 14, and the fifth aluminum tube 16 are seamless rectangular aluminum tubes with slightly smaller cross-sectional dimensions and are welded together with the first aluminum tube 12 and the third aluminum tube 14 to form a whole. Lightening holes can be made on the second aluminum tube 13, the third aluminum tube 14, and the fifth aluminum tube 16 as appropriate to reduce structural weight. After welding, the whole structure is annealed to eliminate welding stress.

[0051] like Figure 5 As shown, this utility model also provides a drone, including the above-mentioned drone frame structure and a power system 17, a transmission system 18, a flight control system 19 and a fuel tank installed thereon, with the transmission system 18 connected to a rotor system 20.

[0052] Specifically, this UAV is a gasoline-powered multi-rotor UAV, comprising a rotor system 20, a transmission system 18, a power system 17, the aforementioned UAV frame structure, and a flight control system 19. The power system 17 is connected to the transmission system 18 via a belt to provide flight power. The transmission system 18 is connected to the left and right rotor systems 20 to transmit engine power. The rotor systems 20 serve as the lifting, control, and thrust surfaces of the aircraft, providing the forces and torques required for flight and control. The flight control system 19 includes a programmable logic controller (PLC), attitude sensors, and control signal receiving devices. The rotor system 20, transmission system 18, power system 17, and flight control system 19 are rationally arranged on the aforementioned UAV frame structure, forming a configuration as described above. Figure 5 The image shows a new type of gasoline-powered quadcopter unmanned aerial vehicle.

[0053] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A frame structure for an unmanned aerial vehicle (UAV), characterized in that, include: The device comprises a central frame and two end frames, the two end frames being connected to opposite ends of the central frame. The central frame and the end frames are made of a first material and a second material, respectively. The density of the first material is less than that of the second material, and the stiffness of the second material is greater than that of the first material. The end frames are used to mount the power system and transmission system of the drone.

2. The frame structure of the UAV according to claim 1, characterized in that, The end frame is connected to the middle frame by bolts.

3. The frame structure of the UAV according to claim 1, characterized in that, The first material is aluminum or an aluminum alloy.

4. The frame structure of the UAV according to claim 1, characterized in that, The second material is steel.

5. The frame structure of the UAV according to claim 1, characterized in that, The central frame includes multiple first rectangular tubular components, which are welded together to form a cuboid frame.

6. The frame structure of the UAV according to claim 5, characterized in that, The two end frames are respectively connected to the two short sides of the cuboid frame.

7. The frame structure of the UAV according to claim 5, characterized in that, The end frame includes a plurality of second rectangular tubular components, which are welded together to form a rectangular frame.

8. The frame structure of the UAV according to claim 7, characterized in that, It also includes a first lug and a second lug, which are welded to one side of the end frame. The first lug is used to mount the landing gear, and the second lug is used to connect to the middle frame. A reinforcing member is connected between the first lug and the second lug.

9. The frame structure of the UAV according to claim 1, characterized in that, The end frame is provided with transmission system mounting holes and power system mounting holes. The middle frame is used to install the UAV's flight control system and fuel tank, and the middle frame is provided with flight control system mounting holes and fuel tank mounting holes.

10. A drone, characterized in that, The unmanned aerial vehicle (UAV) includes the frame structure of any one of claims 1-9, and the power system, transmission system, flight control system, and fuel tank mounted thereon, wherein the transmission system is connected to a rotor system.

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