Variable lift structure hydraulic multi-rotor drone

Abstract

To provide a variable lift structure oil-driven multi-rotor drone with an improved fuselage support structure that ensures compactness and reliability of the structure. [Solution] The variable-lift hydraulic multi-rotor drone has an oil tank fixedly connected to a protective shell, the oil tank connected to a gasoline engine via piping, a driving gear connected to the oil tank's output shaft, a passive gear rotatably connected to the middle layer, the passive gear and the driving gear meshing, a transmission gear fixedly connected to the passive gear's rotating shaft, a support rod fixedly connected to the outside of the fixed block, the outer end of the support rod fixedly connected to a case, and another transmission wheel rotatably connected to the case. This device uses a gasoline engine as its power mechanism, adopts an oil tank top mode, and designs a multi-rotor synchronous transmission structure. In addition, this device adds an angle adjustment mechanism to the swivel wings to adjust the lift output direction and achieve flight functions such as steering.

Description

[Technical Field]

[0001] The present invention relates to the field of drone technology, and more particularly to a variable lift structure oil-powered multi-rotor drone. [Background technology]

[0002] Drones are mainly used in the power industry for tasks such as line inspection, equipment inspection, and emergency response assessment, significantly improving efficiency and safety. Core application scenarios include power line inspection, substation equipment inspection, emergency response, and disaster assessment.

[0003] Equipped with high-resolution cameras, laser radar, and other equipment, drones can rapidly capture high-definition images and 3D point cloud data of power lines, automatically identifying defects such as broken insulation and broken conductors. This method is two to three times more efficient than manual inspections, making it particularly suitable for complex terrain such as mountainous areas and rivers. Equipped with infrared thermography or X-ray equipment, drones can non-contactly detect issues such as overheating and internal structural abnormalities in equipment. Furthermore, after natural disasters, drones can quickly assess the damage to power facilities. For example, heavy-duty drones can participate in damage assessments, shortening the time required for emergency repairs. Conventional drones are often electrically powered, powered by onboard batteries. While this model is clean and environmentally friendly, it has limited range and is difficult to perform long-term tasks. Summary of the Invention [Means for solving the problem]

[0004] The technical problem this invention aims to solve is how to design an oil-powered drone with adjustable power output.

[0005] In order to achieve the objectives of the present invention, the present invention is realized by the following technical solutions: A variable lift structure oil-powered multi-rotor drone, comprising an airframe, a holder, a fixing block, an intermediate layer, a protective shell, a gasoline engine, an oil tank, piping, a driving gear, a passive gear, a transmission wheel, a support rod, a case, a transmission belt, a rotating shaft, and a blade, wherein the holder is fixedly connected to the airframe, several fixing blocks are fixedly connected to the top of the airframe, and protective shells are fixedly connected to the fixing blocks, an intermediate layer is formed between the protective shell and the airframe, the gasoline engine is fixedly connected to the protective shell, and the oil tank is fixed to the protective shell. The oil tank is connected to a gasoline engine via piping, a drive gear is connected to the output shaft of the oil tank, a passive gear is rotatably connected to the intermediate layer, the passive gear and the drive gear are fitted together, a transmission gear is fixedly connected to the rotating shaft of the passive gear, a support rod is fixedly connected to the outside of the fixed block, a case is fixedly connected to the outer end of the support rod, another transmission wheel is rotatably connected to the case, a transmission belt is rotatably connected between the other transmission wheels, a rotating shaft is connected to the other transmission wheel, and a blade is connected to the rotating shaft.

[0006] Preferably, the transmission wheel is a pulley and the transmission belt is a leather belt.

[0007] Preferably, the transmission wheel is a timing belt wheel, and the transmission belt is a timing belt.

[0008] Preferably, an adjustment motor is fixedly connected to the support rod, the center of the Y-shaped frame is rotatably connected to the rotating shaft, both blades are fixedly connected to both arms of the Y-shaped frame, respectively, and a dial lever is connected to the output shaft of the adjustment motor, and the dial lever is connected to the connecting shaft between the Y-shaped frame and the rotating shaft via a transmission lever.

[0009] Preferably, the holder comprises an enclosure fixedly connected to the periphery of the fuselage.

[0010] Preferably, the enclosure has several upwardly extending top bars, the tips of which are fixedly connected to the support rods.

[0011] Preferably, the enclosure has several bottom bars extending downwardly, with support bars fixedly connected between the bottom bars and the support bars.

[0012] Preferably, a connecting rod is connected between adjacent support rods.

[0013] Preferably, a reinforcing bar is connected between the support bar and the top bar.

[0014] Preferably, the antenna is mounted on the support rod.

[0015]

[0003] In the above technical solution, the aircraft body is the main structure of the invention and is used to perform functions such as load-bearing and accommodation. The support rod is used to perform a supporting function, supporting the aircraft during landing and at the same time providing auxiliary support to the support rod. The fixed block is used to form an intermediate layer on the one hand and to support the support rod on the other hand. The intermediate layer is used to accommodate the driving gear and the passive gear and is a protective shell for mounting the gasoline engine. The gasoline engine is used to provide rotational power for the driving gear. The tank supplies fuel to the gasoline engine through a pipe. When the driving gear rotates, it drives the passive gear to rotate, and since the passive gear and the driving gear are coaxial, it also drives the rotation of the driving gear. The above-mentioned driving gear and the separate driving gear in the invention are respectively wrapped around both ends of the transmission belt and can drive the rotation of the separate driving gear. The support rod is used to support the case, and the case is used to accommodate the other driving wheel. A rotating shaft is connected to the other driving wheel, so that the rotating shaft can rotate. The blade is connected to the rotating shaft, so that the blade can rotate, providing flight power for the invention.

[0016] In a preferred embodiment, the two blades are connected to both ends of a Y-shaped frame, and the center of the Y-shaped frame is rotatably connected to the top of the rotating shaft. Therefore, when controlling the rotation angle of the horizontal shaft between the Y-shaped frame and the rotating shaft, the inclination angle of the rotation planes of the two blades can be adjusted, thereby realizing the change and adjustment of the lift output direction and further functions such as steering. The rotation of the horizontal shaft is controlled by an adjustment motor, a dial lever, and a transmission lever.

[0017] In another preferred technical solution, the frame is used to connect the aircraft, the top rod is used to build a support structure between the frame and the support rod, the bottom rod can support the device when descending, the support rod can build another level of support structure between the bottom rod and the support rod, and the connecting rod and reinforcing rod can play a reinforcing role on the support rod. The antenna can be used to transmit control commands.

[0018] This invention provides a variable-lift hydraulic multi-rotor drone. This technical proposal uses a gasoline engine as its power mechanism, adopts an oil tank top mounting mode, and designs a multi-rotor synchronous transmission structure. Furthermore, this invention adds an angle adjustment mechanism to the rotor blades to adjust the direction of lift output and achieve flight functions such as steering. Furthermore, this invention improves the aircraft support structure, ensuring the compactness and reliability of the structure. [Brief explanation of the drawings]

[0019] [Figure 1] FIG. 1 is a perspective view of the present invention. [Figure 2] This is the second perspective view of the present invention. [Figure 3] FIG. 3 is a third perspective view of the present invention. [Figure 4] FIG. 1 is a plan view of the present invention. [Figure 5] 1 is a structural diagram of a holder according to the present invention; [Figure 6] FIG. 2 is a partial view of the passive gear position of the present invention. [Figure 7] FIG. 2 is a partial view of the oil tank location of the present invention. [Figure 8] FIG. 2 is a partial view of the support rod position of the present invention. [Figure 9] FIG. 2 is a partial view of the rotation axis position of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0020] Specific embodiments of the present invention will be described in detail below. In order to avoid excessive details, well-known structures or functions will not be described in detail in the following embodiments. Approximate language used in the following embodiments can be used to quantitatively express that a certain amount of variation is allowed without changing the basic function. In addition to definitions, technical and scientific terms used in the following examples have the same meaning as commonly understood by those skilled in the art to which the present invention pertains.

[0021] The variable lift structure oil-powered multi-rotor drone includes, as shown in Figures 1 to 9, an airframe 1, a holder 2, a fixed block 3, an intermediate layer 4, a protective shell 5, a gasoline engine 6, an oil tank 7, piping 8, a driving gear 9, a passive gear 10, a transmission wheel 11, a support rod 12, a case 13, a transmission belt 14, a rotating shaft 15, and a blade 16, wherein the holder 2 is fixedly connected to the airframe 1, several fixed blocks 3 are fixedly connected to the top of the airframe 1, and the protective shells 5 are fixedly connected to the fixed blocks 3, and an intermediate layer 4 is formed between the protective shells 5 and the airframe 1, and the gasoline engine 6 is fixedly connected to the protective shell 5, and the protective shell 5 is fixedly connected to the oil tank 7. A tank 7 is fixedly connected, and the oil tank 7 is connected to a gasoline engine 6 via piping 8. A drive gear 9 is connected to the output shaft of the oil tank 7. A passive gear 10 is rotatably connected to the intermediate layer 4. The passive gear 10 and the drive gear 9 are engaged with each other. A transmission gear 11 is fixedly connected to the rotating shaft of the passive gear 10. A support rod 12 is fixedly connected to the outside of the fixed block 3. A case 13 is fixedly connected to the outer end of the support rod 12. Another transmission wheel is rotatably connected to the case 13. A transmission belt 14 is rotatably connected between the other transmission wheel and the transmission wheel 11. A rotating shaft 15 is connected to the other transmission wheel, and a blade 16 is connected to the rotating shaft 15.

[0022] In the above technical solution, the fuselage 1 is the main structure of the utility model and is used to fulfill the roles of load bearing, storage, etc.; the holder 2 is used to support the fuselage 1 during landing and also to auxiliary support the holder 12; the fixed block 3 is used to form the intermediate layer 4 on the one hand and to support the support rod 12 on the other hand; the intermediate layer 4 is used to accommodate the driving gear 9 and the passive gear 10; the protective shell 5 is used to mount the gasoline engine 6; the gasoline engine 6 is used to provide rotational power to the driving gear 9; and the oil tank 7 supplies oil to the gasoline engine 6 through a pipe 8. When the driving gear 9 rotates, the passive gear 10 rotates. Since the passive gear 10 is coaxial with the transmission wheel 11, the transmission wheel 11 rotates. The transmission wheel 11 and the other transmission wheel in this utility model are respectively wrapped around both ends of the transmission belt 14, so that the other transmission wheel can rotate. The support rod 12 is for supporting the case 13, and the case 13 is for accommodating the other transmission wheel. The rotating shaft 15 is connected to the other driving wheel, so that the rotating shaft 15 can rotate. The blade 16 is connected to the rotating shaft 15, so that the blade 16 can rotate, providing the flying power of this utility model.

[0023] Example 2 The variable lift structure oil-powered multi-rotor drone includes, as shown in Figures 1 to 9, an airframe 1, a holder 2, a fixed block 3, an intermediate layer 4, a protective shell 5, a gasoline engine 6, an oil tank 7, piping 8, a driving gear 9, a passive gear 10, a transmission wheel 11, a support rod 12, a case 13, a transmission belt 14, a rotating shaft 15, and a blade 16, wherein the holder 2 is fixedly connected to the airframe 1, several fixed blocks 3 are fixedly connected to the top of the airframe 1, and the protective shells 5 are fixedly connected to the fixed blocks 3, and an intermediate layer 4 is formed between the protective shells 5 and the airframe 1, and the gasoline engine 6 is fixedly connected to the protective shell 5, and the protective shell 5 is fixedly connected to the oil tank 7. A tank 7 is fixedly connected, and the oil tank 7 is connected to a gasoline engine 6 via piping 8. A drive gear 9 is connected to the output shaft of the oil tank 7. A passive gear 10 is rotatably connected to the intermediate layer 4. The passive gear 10 and the drive gear 9 are engaged with each other. A transmission gear 11 is fixedly connected to the rotating shaft of the passive gear 10. A support rod 12 is fixedly connected to the outside of the fixed block 3. A case 13 is fixedly connected to the outer end of the support rod 12. Another transmission wheel is rotatably connected to the case 13. A transmission belt 14 is rotatably connected between the other transmission wheel and the transmission wheel 11. A rotating shaft 15 is connected to the other transmission wheel, and a blade 16 is connected to the rotating shaft 15.

[0024] Here, the transmission wheel 11 is a pulley, and the transmission belt 14 is a leather belt. The transmission wheel 11 is a timing belt wheel, and the transmission belt 14 is a timing belt. An adjustment motor 17 is fixedly connected to the support rod 12, the center of a Y-shaped frame 18 is rotatably connected to a rotating shaft 15, and both blades 16 are fixedly connected to both arms of the Y-shaped frame 18, respectively. A dial lever 19 is connected to the output shaft of the adjustment motor 17, and the dial lever 19 is connected to the connecting shaft between the Y-shaped frame 18 and the rotating shaft 15 via a transmission lever 20. The holder 2 includes a frame 21 fixedly connected to the outer periphery of the machine body 1. The frame 21 has several top bars 22 extending upward, and the tips of the top bars 22 are fixedly connected to the support rod 12. The frame 21 has several bottom bars 23 extending downward, and a support bar 24 is fixedly connected between the bottom bars 23 and the support rod 12. A connecting rod 25 is connected between adjacent support rods 24. A reinforcing rod 26 is connected between the support rod 24 and the top bar 22. An antenna 27 is provided on the support rod 12.

[0025] In the above technical solution, both blades 16 are connected to both ends of a Y-shaped frame 18, and the center of the Y-shaped frame 18 is rotatably connected to the top of the rotating shaft 15. Therefore, by controlling the rotation angle of the horizontal shaft between the Y-shaped frame 18 and the rotating shaft 15, the inclination angle of the rotation plane of both blades 16 can be adjusted, thereby realizing change and adjustment of the lift output direction and ultimately realizing functions such as steering. The rotation of the horizontal shaft is controlled by an adjustment motor 17, a dial lever 19, and a transmission lever 20.

[0026] In the above technical solution, the frame 21 is used to connect the fuselage 1, the top bar 22 is used to establish a support structure between the frame 21 and the support rod 12, the bottom rod 23 can support the present utility model during descent, the support rod 24 establishes another level of support structure between the bottom rod 23 and the support rod 12, and the connecting rod 25 and the reinforcing rod 26 can play the role of reinforcing the support rod 24. The antenna 27 can be used to transmit control commands.

[0027] Although the embodiments of the present invention have been described in detail above, the above content is merely a preferred embodiment of the present invention and does not limit the present invention. Any modifications, equivalent replacements and improvements made within the scope of the present invention shall be included in the protection scope of the present invention. [Explanation of symbols]

[0028] 1. Airframe; 2. Holder; 3. Fixed block; 4. Intermediate layer; 5. Protective shell; 6. Gasoline engine; 7. Oil tank; 8. Piping; 9. Drive gear; 10. Passive gear; 11. Transmission wheel; 12. Support rod; 13. Case; 14. Transmission belt; 15. Rotating shaft; 16. Blade; 17. Adjusting motor; 18. Y-shaped frame; 19. Dial lever; 20. Transmission lever; 21. Enclosure; 22. Top bar; 23. Bottom bar; 24. Support rod; 25. Connecting rod; 26. Reinforcement rod; 27. Antenna.

Claims

1. The apparatus includes a body (1), a holder (2), a fixed block (3), an intermediate layer (4), a protective shell (5), a gasoline engine (6), an oil tank (7), piping (8), a driving gear (9), a driven gear (10), a transmission wheel (11), a support rod (12), a case (13), a transmission belt (14), a rotating shaft (15), and a blade (16), wherein the holder (2) is fixedly connected to the body (1), several fixed blocks (3) are fixedly connected to the top of the body (1), and protective shells (5) are fixedly connected to the fixed blocks (3), and an intermediate layer (4) is formed between the protective shells (5) and the body (1), and the gasoline engine (6) is fixedly connected to the protective shell (5), and the oil tank (7) is fixedly connected to the protective shell (5), and the oil tank (7) is fixedly connected to the protective shell (5). ) is connected to a gasoline engine (6) via a pipe (8), a drive gear (9) is connected to the output shaft of the oil tank (7), a passive gear (10) is rotatably connected to the intermediate layer (4), the passive gear (10) and the drive gear (9) are engaged with each other, a transmission gear (11) is fixedly connected to the rotation shaft of the passive gear (10), a support rod (12) is fixedly connected to the outside of the fixed block (3), a case (13) is fixedly connected to the outer end of the support rod (12), another transmission wheel is rotatably connected to the case (13), a transmission belt (14) is rotatably connected between the another transmission wheel and the transmission wheel (11), a rotating shaft (15) is connected to the another transmission wheel, and a blade (16) is connected to the rotating shaft (15).

2. The variable lift structure oil-powered multi-rotor drone according to claim 1, characterized in that the transmission wheel (11) is a pulley and the transmission belt (14) is a leather belt.

3. The variable lift structure oil-driven multi-rotor drone according to claim 1, characterized in that the transmission wheel (11) is a timing belt wheel, and the transmission belt (14) is a timing belt.

4. The variable lift structure oil-driven multi-rotor drone according to claim 1, characterized in that an adjustment motor (17) is fixedly connected to the support rod (12), a central part of the Y-shaped frame (18) is rotatably connected to the rotation shaft (15), both blades (16) are fixedly connected to both arms of the Y-shaped frame (18), a dial lever (19) is connected to the output shaft of the adjustment motor (17), and the dial lever (19) is connected to the connecting shaft between the Y-shaped frame (18) and the rotation shaft (15) via a transmission lever (20).

5. The variable lift structure oil-powered multi-rotor drone according to claim 1, characterized in that the holder (2) includes an enclosure (21) fixedly connected to the outer periphery of the fuselage (1).

6. The variable lift structure oil-powered multi-rotor drone according to claim 5, characterized in that it has several top bars (22) extending upward on the frame (21), and the tips of the top bars (22) are fixedly connected to the support rods (12).

7. The variable lift structure oil-powered multi-rotor drone according to claim 6, characterized in that the enclosure (21) has several bottom rods (23) extending downward, and support rods (24) are fixedly connected between the bottom rods (23) and the support rods (12).

8. The variable lift structure oil-powered multi-rotor drone according to claim 7, characterized in that a connecting rod (25) is connected between adjacent support rods (24).

9. The variable lift structure oil-powered multi-rotor drone according to claim 8, characterized in that a reinforcing rod (26) is connected between the support rod (24) and the top bar (22).

10. The variable lift structure oil-powered multi-rotor drone according to claim 1, characterized in that an antenna (27) is provided on the support rod (12).

Images