Universal take-off and landing rotor module device for fixed-wing and four-rotor unmanned aerial vehicles
The modular design of the universal take-off and landing rotor module device for fixed-wing and quad-rotor drones solves the problem of poor applicability of drone kits and enables flexible combination of different types of drones and efficient and stable flight.
Patent Information
- Application Number
- CN202422886864.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-26
- Publication Date
- 2025-10-21
- Estimated Expiration
- 2034-11-26
AI Technical Summary
The lack of a universal kit on the market that can be used for both fixed-wing drone vertical take-off and landing and quadcopter drones has limited the use of drones.
A modular and standardized universal take-off and landing rotor module device for fixed-wing and quadrotor UAVs is designed. It adopts an H-shaped quadrotor architecture with large-size blades and a quick-release structure, including the first and second take-off and landing rotor modules. It uses high-strength lightweight materials and intelligent functions to achieve rapid disassembly and assembly.
The drone kit has achieved wide applicability among different types of drones and efficient and stable power output, reducing operational difficulty and failure rate, and improving user experience and efficiency.
Smart Images
Figure CN223457130U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to unmanned plane technical field especially relates to fixed wing and four rotor unmanned plane general take -off rotor module device. BACKGROUND
[0002] With the rapid development of unmanned plane technology, the application of unmanned plane in various fields is increasingly widespread, and its types are various, including fixed wing unmanned plane and four rotor unmanned plane etc., in fine operation, rotor unmanned plane is more suitable for the scene with flexible operation demand because of its flexible, easy operation, hovering and photographing etc.
[0003] The unmanned plane kit on the market can only be applied to specific types of unmanned plane at present, and there is a lack of a general kit that can be applied to fixed wing unmanned plane vertical take-off and four rotor unmanned plane.
[0004] Based on the above background, the utility model patent aims to provide an unmanned plane kit, which uses "H" shaped four rotor frame, matches large size paddle and adopts quick release structure, can be quickly disassembled and assembled under different conditions, meets different needs of fixed wing unmanned plane vertical take-off and four rotor unmanned plane, through optimization design and material selection, the kit can meet the performance requirements of different unmanned planes, improve the use efficiency and flexibility of unmanned plane, and provide strong support for the wide application of unmanned plane. UTILITY MODEL CONTENT
[0005] In order to overcome the problem that the unmanned plane kit on the market can only be applied to specific types of unmanned plane at present, and there is a lack of a general kit that can be applied to fixed wing unmanned plane vertical take-off and four rotor unmanned plane.
[0006] The technical scheme of the utility model is: the general take-off rotor module device for fixed wing and four rotor unmanned plane, including first take-off rotor module and second take-off rotor module, the first take-off rotor module includes frame main rod and arm, the arm is provided with two groups, the two groups of arms are connected to the two ends of the frame main rod respectively, the ends of the two groups of arms away from the frame main rod are provided with motor seat, the upper parts of the motor seat are provided with propeller, the lower parts of the two ends of the frame main rod are provided with two groups of carbon take-off support, the lower ends of the frame main rod are provided with reserved installation groove, the first take-off rotor module is matched with the second take-off rotor module, and the second take-off rotor module is arranged in the same way as the first take-off rotor module.
[0007] The unmanned aerial vehicle kit has the advantages that the kit is suitable for vertical take-off and landing fixed-wing unmanned aerial vehicles and four-rotor unmanned aerial vehicles, the kit has wide market applicability and high competitiveness due to the modular and standardized design concept, and key components such as a main frame rod, a propeller and landing legs in the kit can be combined and replaced flexibly according to the requirements of different unmanned aerial vehicles.
[0008] As preferred, the inside of the motor seat is fixedly provided with a servo motor, and the outer end of the servo motor is fixedly provided with an electronic speed regulator, and the electronic speed regulator is electrically connected with the servo motor.
[0009] As preferred, the upper end of the servo motor is provided with a quick-connection slot, the center of the propeller is provided with a connecting seat, and the lower end of the connecting seat is provided with a quick-connection buckle corresponding to the quick-connection slot.
[0010] As preferred, the first and second landing rotor modules are matched with a four-rotor fuselage, and a connecting piece is arranged between the wing mounting position of the four-rotor fuselage and the reserved mounting slot of the main frame rod.
[0011] As preferred, the first and second landing rotor modules are matched with a fixed-wing fuselage, and the two sides of the fixed-wing fuselage are respectively provided with a right wing and a left wing.
[0012] As preferred, the middle section of the right wing and the left wing is provided with an installation support block, and the installation support block is matched with the reserved mounting slot of the main frame rod.
[0013] As preferred, the upper end of the two groups of carbon landing legs is fixedly connected with the two ends of the main frame rod, and the lower end of the two groups of carbon landing legs is sleeved with a rubber buffer sleeve.
[0014] The utility model discloses the beneficial effects that:
[0015] 1. The unmanned aerial vehicle kit of the utility model has unique design, can be suitable for vertical take-off and landing fixed wing unmanned aerial vehicle and four rotor unmanned aerial vehicle simultaneously, this is due to its modularization, standardization design concept, so that the key components such as main frame pole, propeller, take-off and landing support leg in the kit can be combined and replaced flexibly according to the needs of different unmanned aerial vehicles, this feature makes the kit have wide applicability and high competitiveness in the market, the brushless motor and electronic speed controller in the first take-off and landing rotor module and the second take-off and landing rotor module are carefully designed and optimized, can provide efficient and stable power output for unmanned aerial vehicle, the brushless motor has high efficiency, low noise and long service life, and the electronic speed controller can realize accurate speed control, ensure that the unmanned aerial vehicle can maintain stability in various flight states, the unmanned aerial vehicle kit of the utility model also integrates intelligent functions, such as automatic identification and adaptation of different unmanned aerial vehicle types, flight state real-time monitoring, fault warning, etc., the introduction of these functions makes the unmanned aerial vehicle kit more convenient and intelligent, not only improves the user experience, but also reduces the operation difficulty and failure rate, the electronic speed controller intelligently identifies different models and has overload protection function, which can effectively prevent motor overload damage. Meanwhile, each component in the kit is strictly controlled and tested in quality, to ensure that it can maintain stable performance in various harsh environments. BRIEF DESCRIPTION OF DRAWINGS
[0016] Figure 1 The overall structure schematic diagram of the general take-off and landing rotor module device of the utility model is shown.
[0017] Figure 2 The four rotor unmanned aerial vehicle assembly structure schematic diagram of the general take-off and landing rotor module device of the utility model is shown.
[0018] Figure 3 The fixed wing unmanned aerial vehicle structure schematic diagram of the general take-off and landing rotor module device of the utility model is shown.
[0019] Figure 4 The fixed wing unmanned aerial vehicle assembly structure schematic diagram of the general take-off and landing rotor module device of the utility model is shown.
[0020] Mark explanation: 1, the first take-off and landing rotor module;2, the second take-off and landing rotor module;3, main frame pole;4, arm;5, motor seat;6, servo motor;7, quick connection slot;8, propeller;9, connecting seat;10, quick connection buckle;11, electronic speed controller;12, carbon take-off and landing support leg;13, rubber buffer sleeve;14, reserved mounting groove;15, four rotor fuselage;16, fixed wing fuselage;17, right wing;18, left wing. DETAILED DESCRIPTION
[0021] The utility model will be further explained in connection with the drawings and examples.
[0022] Please refer to Figures 1-4 The utility model provides a kind of embodiment: general take-off and landing rotor module device for fixed wing and quadcopter, comprising first take-off and landing rotor module 1, second take-off and landing rotor module 2;First take-off and landing rotor module 1 includes frame main rod 3 and arm 4, arm 4 is equipped with two groups, two groups The arm 4 is respectively connected at the two ends of the frame main rod 3, the end of two groups of arm 4 away from frame main rod 3 is equipped with motor seat 5, the top of motor seat 5 is equipped with propeller 8, the lower two ends of frame main rod 3 are respectively two groups of carbon take-off and landing leg 12, the lower end of frame main rod 3 is all provided with reserved mounting groove 14, first take-off and landing rotor module 1 is matched with second take-off and landing rotor module 2, and second take-off and landing rotor module 2 is arranged the same as first take-off and landing rotor module 1.
[0023] Please refer to Figures 1-3 In the embodiment, servo motor 6 is fixedly installed inside motor seat 5, electronic speed controller 11 is fixedly installed at the outer end of servo motor 6, electronic speed controller 11 is electrically connected with servo motor 6, quick connection slot 7 is formed in the upper end of servo motor 6, connecting seat 9 is provided at the center of propeller 8, quick connection buckle 10 corresponding to quick connection slot 7 is provided at the lower end of connecting seat 9, the upper end of two groups of carbon take-off and landing leg 12 is fixedly connected with the two ends of frame main rod 3, the lower end of two groups of carbon take-off and landing leg 12 is all provided with rubber buffer sleeve 13, through the combination of electronic speed controller 11 and servo motor 6, the brushless motor and electronic speed controller 11 are carefully designed and optimized, can provide efficient, stable power output for unmanned aerial vehicle, the brushless motor has high efficiency, low noise, long service life and other characteristics, and electronic speed controller 11 can realize accurate speed control, ensure that unmanned aerial vehicle can maintain stability in various flight states, electronic speed controller 11 intelligently identifies different models, has overload protection function, can effectively prevent motor overload damage, through the combination of carbon take-off and landing leg 12 and rubber buffer sleeve 13, carbon take-off and landing leg 12 can play a certain supporting role when fixed wing unmanned aerial vehicle and quadcopter take off and land, and rubber buffer sleeve 13 can reduce the impact force of fixed wing unmanned aerial vehicle and quadcopter at the moment of landing, through the combination of quick connection buckle 10 and quick connection slot 7, propeller 8 and brushless motor can be quickly connected and installed and disassembled, so as to facilitate user to quickly replace and maintain.
[0024] Please refer to Figures 2-4In the embodiment, the first and second VTOL rotor modules 1 and 2 are matched with the quadcopter fuselage 15, the connecting pieces are arranged between the wing mounting positions of the quadcopter fuselage 15 and the reserved mounting slots 14 of the main frame 3, the first and second VTOL rotor modules 1 and 2 are matched with the fixed-wing fuselage 16, the right wing 17 and the left wing 18 are arranged at the two sides of the fixed-wing fuselage 16 respectively, the mounting support blocks are arranged below the middle sections of the right wing 17 and the left wing 18 respectively, the mounting support blocks are matched and connected with the reserved mounting slots 14 of the main frame 3, and through the reserved mounting slots 14, the left wing 18 and the right wing 17 of the fixed-wing UAV and the wing mounting positions of the quadcopter fuselage 15 can be clamped and installed together.
[0025] In the working process, the worker ensures that the quadcopter kit, the fixed-wing UAV body, the connecting pieces, the fixing screws, the wrench and other tools are prepared before starting the conversion process, and ensures that the operation environment is flat to ensure the smooth conversion process. First, the first and second VTOL rotor modules 1 and 2 of the quadcopter are disassembled from the original structure, and attention should be paid to not damaging the modules and other parts of the UAV during the disassembly process, and the disassembled kit is properly stored for subsequent installation and use.
[0026] Then, the integrity and normality of the key components such as the motor, the electronic speed controller 11 and the propeller 8 are checked, the motor rotation smoothness and the coil integrity are checked, and the kit connection terminal integrity is checked.
[0027] Next, the appearance and structural integrity of the fixed-wing UAV are checked, including whether the fixed-wing fuselage 16, the left wing 18 and the right wing 17 and other components are intact, and whether the connection components are fastened to ensure the stability of the UAV in flight.
[0028] The first and second VTOL rotor modules 1 and 2 of the disassembled quadcopter are installed on the fixed-wing UAV, the first and second VTOL rotor modules 1 and 2 and the reserved connecting parts below the left wing 18 and the right wing 17 of the fixed-wing UAV are installed, and in the installation process, it should be ensured that the first and second VTOL rotor modules 1 and 2 are stably and reliably connected with the fixed-wing UAV to ensure the normal play of the vertical take-off and landing function.
[0029] After installation is completed, the first and second lift rotor modules 1 and 2 need to be debugged and tested, first, check whether the connection of the first and second lift rotor modules 1 and 2 and the fixed-wing unmanned aerial vehicle is fastened, and there is no loosening phenomenon, then, test the vertical take-off and landing function, observe whether the fixed-wing unmanned aerial vehicle can normally take off and land vertically, and during the test process, attention should be paid to observe the stability and safety of the unmanned aerial vehicle to ensure that no abnormal situation occurs.
[0030] Through the above steps, the structure of the utility model adopts modular design, and standard interfaces are adopted between structures, so that different components can be flexibly combined to adapt to the different structural characteristics of the vertical take-off and landing fixed-wing unmanned aerial vehicle and the quadcopter unmanned aerial vehicle. The arm 4 is made of high-strength, lightweight carbon fiber and aluminum alloy material to ensure that the unmanned aerial vehicle remains lightweight and flexible while bearing heavy load, to ensure the stability and durability of the unmanned aerial vehicle in complex environments. In order to meet the flight needs of different types of unmanned aerial vehicles, considering the coordination and balance between components, the application provides a plurality of specifications of propellers 8 and brushless motors for selection after accurate calculation, the propeller 8 adopts high-efficiency design to optimize flight efficiency, and the brushless motor provides stable and reliable power output for the unmanned aerial vehicle to ensure that the unmanned aerial vehicle has sufficient thrust and stability during flight. In addition, the connection part of the propeller 8 and the brushless motor also adopts quick release design, which is convenient for users to quickly replace and maintain. The first and second lift rotor modules 1 and 2 are not only suitable for vertical take-off and landing fixed-wing unmanned aerial vehicles and quadcopter unmanned aerial vehicles, but also can be expanded to other types of unmanned aerial vehicles by replacing some components. In addition, the kit also supports integrated external devices such as auxiliary positioning downward-looking vision camera, sensors, etc. to meet the diversified needs of users. The unmanned aerial vehicle kit also integrates intelligent functions such as automatic identification and adaptation to different unmanned aerial vehicle types, flight state real-time monitoring, fault warning, etc. The introduction of these functions makes the unmanned aerial vehicle kit more convenient and intelligent, improves the user experience, and the first and second lift rotor modules 1 and 2 realize the wide applicability of vertical take-off and landing fixed-wing unmanned aerial vehicles and quadcopter unmanned aerial vehicles through modular design, high-efficiency component configuration, intelligent integration, and good compatibility and expandability. The implementation of the utility model will effectively solve the problem of single function and poor applicability of unmanned aerial vehicle kits on the market at present, and provide strong support for the wide application and development of unmanned aerial vehicles.
Claims
1. A general take-off and landing rotor module device for fixed-wing and quadcopter unmanned aerial vehicles, comprising a first take-off and landing rotor module (1); characterized in that: Still include the second take-off and landing rotor module (2); The first take-off and landing rotor module (1) includes frame main rod (3) and machine arm (4), machine arm (4) is equipped with two groups, two groups the machine arm (4) is connected respectively at two ends of the frame main rod (3), and the two groups of machine arms (4) are provided with motor seat (5) at the end away from the frame main rod (3), and the upper portion of motor seat (5) is provided with propeller (8), and the lower portion of the two ends of frame main rod (3) is provided with two groups of carbon take-off and landing support (12), and the lower end of frame main rod (3) is provided with the reserved installation groove (14), and the first take-off and landing rotor module (1) is matched with the second take-off and landing rotor module (2), and the second take-off and landing rotor module (2) is arranged the same as the first take-off and landing rotor module (1). 2.The universal take-off and landing rotor module device for fixed-wing and quad-rotor UAVs according to claim 1, characterized in that: The inside of motor seat (5) is fixedly installed with servo motor (6), and the outer end of servo motor (6) is fixedly installed with electronic speed regulator (11), and electronic speed regulator (11) is electrically connected with servo motor (6). 3.The universal take-off and landing rotor module device for fixed-wing and quad-rotor UAVs according to claim 2, characterized in that: The upper end of servo motor (6) is provided with quick connection slot (7), and the center of propeller (8) is provided with connecting seat (9), and the lower end of connecting seat (9) is provided with quick connection buckle (10) corresponding to quick connection slot (7). 4.The device according to claim 1, characterized in that: The first take-off and landing rotor module (1) and the second take-off and landing rotor module (2) are matched with four-rotor fuselage (15), and the wing mounting position of four-rotor fuselage (15) is provided with connecting piece between the reserved installation groove (14) of frame main rod (3). 5.The device according to claim 1, characterized in that: The first take-off and landing rotor module (1) and the second take-off and landing rotor module (2) are matched with fixed-wing fuselage (16), and the two sides of fixed-wing fuselage (16) are provided with right wing (17) and left wing (18) respectively. 6.The device according to claim 5, characterized in that: The middle section of right wing (17) and left wing (18) is provided with mounting support block below, and the mounting support block is matched with the reserved installation groove (14) of frame main rod (3) and is connected. 7.The device according to claim 1, characterized in that: The upper end of two groups of carbon take-off and landing support (12) is fixedly connected with the two ends of frame main rod (3), and the lower end of two groups of carbon take-off and landing support (12) is provided with rubber buffer sleeve (13).