Multi-rotor lifting structure with buffer platform
By designing a multi-rotor lifting structure with a buffer platform, the problem of unstable take-off and landing of existing drones in low altitudes, narrow spaces and complex terrain is solved, rapid movement and flexible handling are achieved, and the smoothness and safety of flight are enhanced through buffer devices.
Patent Information
- Application Number
- CN202421035350.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-13
- Publication Date
- 2025-03-14
- Estimated Expiration
- 2034-05-13
AI Technical Summary
The existing drone lifting structure has high requirements for take-off and landing sites, limited adaptability, and problems with the support and protection at the bottom, making it difficult to take-off and land stably in environments such as low altitude, narrow space and complex terrain.
A multi-rotor lifting structure with a buffering platform is designed, including a multi-rotor bracket, a rotor, a telescopic rod, a cargo box, a pad and a buffer device. Through the coordinated work of these components, the effects of rapid movement, flexible handling and cushioning are achieved.
This structure can achieve stable take-off and landing and rapid movement in environments such as narrow spaces, low altitudes and complex terrain, and absorb vibration and impact through pads and buffer devices, enhancing flight stability and safety.
Smart Images
Figure CN222611397U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of rotor lifting, in particular to a multi-rotor lifting structure with a buffer platform. Background Art
[0002] The multi-rotor lifting structure plays a vital role in drones. This device enables drones to have vertical take-off and landing, hover, move forward, backward, turn left and right, and other maneuverability, allowing drones to take off and land stably in a small space and adapt to application requirements in various complex environments.
[0003] However, the existing drone lifting structure has high requirements for the take-off and landing site. For example, fixed-wing drones require a long take-off and landing runway, which has high requirements for the site. In addition, the adaptability of the existing drone lifting structure is limited. Fixed-wing drones are difficult to adapt to certain special environments, such as low altitude, small space, complex terrain, etc. In addition, the existing drone lifting structure has problems with support and protection at the bottom. For example, the existing drone lifting structure may be deformed or damaged due to uneven force. Therefore, the utility model provides a multi-rotor lifting structure with a buffer platform. Utility Model Content
[0004] 1. Technical issues to be resolved
[0005] In view of the shortcomings of the prior art, the utility model provides a multi-rotor lifting structure with a buffer platform, which has the advantages of flexible mobility, strong adaptability and high stability, and solves the problems of high requirements for take-off and landing sites, limited adaptability and insufficient stability.
[0006] (II) Technical solution
[0007] In order to achieve the above-mentioned purpose of flexible movement, strong adaptability and high stability, the utility model provides the following technical solutions:
[0008] A multi-rotor lifting structure with a buffer platform comprises a multi-rotor lifting structure, wherein a multi-rotor buffer structure is arranged inside the multi-rotor lifting structure;
[0009] The multi-rotor lifting structure comprises a fuselage, a multi-rotor bracket is arranged on the top of the fuselage, six windproof slots are opened inside the multi-rotor bracket, rotors are arranged inside the windproof slots, a telescopic rod is arranged at the bottom of the fuselage, a cargo box is arranged at the bottom of the telescopic rod, brackets are arranged on the left and right sides of the bottom of the fuselage, and pads are arranged at the bottom of the brackets;
[0010] The multi-rotor buffer structure comprises a buffer platform located on the top of the cushion block, a buffer device is provided at the bottom of the buffer platform, and a supporting platform is provided at the bottom of the buffer device.
[0011] As an optimal technical solution of the utility model, a piston rod is provided at the top of the buffer device, a buffer piston is provided at the bottom of the piston rod, a pressure chamber is provided at the bottom of the buffer piston, energy accumulators are provided on the left and right sides of the piston rod, and a flow hole is provided on the left side of the buffer device.
[0012] As a preferred technical solution of the utility model, a control shaft is provided inside the fuselage, six control arms are distributed circumferentially on the control shaft, a motor is provided at the other end of the control arm, and the motor is located inside the windproof slot.
[0013] As a preferred technical solution of the utility model, the multi-rotor bracket is connected to the fuselage by a threaded connection, the telescopic rod is connected to the fuselage by a threaded connection, and the cargo box is connected to the telescopic rod by a card connection. A card block is provided at the bottom of the telescopic rod, and a card slot corresponding to the card block is provided at the top of the cargo box. The telescopic rod is carded in the card slot through the card block to achieve card connection with the cargo box.
[0014] As a preferred technical solution of the utility model, a cargo box door is provided directly in front of the cargo box, a door shaft is provided at the connection between the cargo box and the cargo box door on the left side, the door shaft is connected to the cargo box by a rotating connection, and a card interface is provided at the connection between the cargo box door and the cargo box on the right side, and the cargo box door connects to the cargo box through the card interface.
[0015] As a preferred technical solution of the utility model, the cushion block is connected to the bracket by a threaded connection, one end of the bottom of the piston rod is connected to the buffer piston, and the other end of the piston rod is connected to the buffer platform. The buffer piston can slide in the pressure chamber, and the buffer piston forms an oil circuit with the pressure chamber and the flow hole.
[0016] As a preferred technical solution of the utility model, the control shaft is connected to the inside of the fuselage by a threaded connection, the control arm is connected to the control shaft by a threaded connection, the motor is connected to the control arm by a threaded connection, the top of the motor is rotatably connected to the rotor, and the rotor is located inside the windproof groove.
[0017] (III) Beneficial effects
[0018] Compared with the prior art, the utility model provides a multi-rotor lifting structure with a buffer platform, which has the following beneficial effects:
[0019] The multi-rotor lifting structure with a buffer platform, through the use of a multi-rotor bracket and rotors, enables the device to quickly change the flight attitude and position, achieve rapid movement and flexible control, and enable the device to have better applicability in certain environments, such as in small spaces, low altitudes, complex terrain and the like. In addition, through the use of pads, it can better absorb and buffer the vibrations and impacts generated during the flight, further enhancing the stability and safety of the flight. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] Figure 1 It is a schematic diagram of the structure of the utility model;
[0021] Figure 2 It is a schematic diagram of the top of the structure of the utility model;
[0022] Figure 3 This is a schematic diagram of the cushion block structure of the utility model.
[0023] In the figure: 1. Fuselage; 2. Multi-rotor bracket; 3. Windproof slot; 4. Rotor; 5. Telescopic rod; 6. Cargo box; 7. Bracket; 8. Pad; 9. Buffer platform; 10. Buffer device; 11. Support platform; 12. Piston rod; 13. Buffer piston; 14. Pressure chamber; 15. Energy accumulator; 16. Flow hole; 17. Control shaft; 18. Control arm; 19. Motor. DETAILED DESCRIPTION
[0024] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0025] In the description of the present invention, it should be understood that the terms "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as a limitation on the present invention.
[0026] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0027] See also Figure 1-3 , a multi-rotor lifting structure with a buffer platform, comprising a multi-rotor lifting structure, wherein a multi-rotor buffer structure is arranged inside the multi-rotor lifting structure;
[0028] Embodiment 1, a multi-rotor lifting structure includes a fuselage 1, a multi-rotor bracket 2 is provided on the top of the fuselage 1, six windproof grooves 3 are opened inside the multi-rotor bracket 2, rotors 4 are provided inside the windproof grooves 3, a telescopic rod 5 is provided at the bottom of the fuselage 1, a cargo box 6 is provided at the bottom of the telescopic rod 5, brackets 7 are provided on the left and right sides of the bottom of the fuselage 1, and pads 8 are provided at the bottom of the brackets 7, wherein the fuselage 1 is the main body of the entire multi-rotor lifting structure, which is used to provide support and protection for other components; the multi-rotor bracket 2 is used to fix and support the structure of the rotor; the windproof grooves 3 are located inside the multi-rotor bracket 2, which can reduce wind resistance and the impact of wind on the rotor and improve flight stability; the rotor 4 is a component for generating lift, which is driven to rotate by a motor; the telescopic rod 5 is a structure for adjusting the height of the cargo box 6, which can be extended or retracted as needed; the cargo box 6 is a container for storing goods or equipment, which can be easily installed or disassembled at the bottom of the telescopic rod; the bracket 7 is used to support and fix the structure of other components; the pad 8 provides a component for buffering and supporting.
[0029] It should be noted that: the multi-rotor bracket 2 is connected to the fuselage 1 by a threaded connection, the telescopic rod 5 is connected to the fuselage 1 by a threaded connection, and the cargo box 6 is connected to the telescopic rod 5 by a card connection. A card block is provided at the bottom of the telescopic rod 5, and a card slot corresponding to the card block is provided at the top of the cargo box 6. The telescopic rod 5 is carded in the card slot through the card block to achieve card connection with the cargo box 6.
[0030] In this embodiment, a cargo box door is provided in front of the cargo box 6, and a door rotating shaft is provided at the connection between the cargo box 6 and the cargo box door on the left side. The door rotating shaft is connected to the cargo box 6 in a rotating connection manner. A card interface is provided at the connection between the cargo box door and the cargo box 6 on the right side, and the cargo box door is connected to the cargo box 6 through the card interface. Among them, the cargo box 6 is the main part of the whole system, which is used to store, transport and protect goods. Its structural design is to maximize space utilization and protect the safety of goods; the cargo box door is used to close the cargo box to prevent the goods from falling or being damaged by the external environment during transportation. At the same time, the door can also be easily opened. In order to facilitate loading and unloading of goods; the door shaft is a component connecting the cargo box and the door, which allows the door to be opened and closed in a rotating manner; the card interface is located at the right side of the cargo box door and the connection with the cargo box, and its main function is to fix the door to ensure that the door can fit the cargo box tightly when closed to prevent the goods from falling or external damage; in the entire cargo box 6, through the rotation connection of the door shaft, the door can be easily opened and closed, and when the goods need to be loaded or unloaded, the door is opened; when the goods are loaded or need to be transported, the door is closed and fixed to the cargo box through the card interface to form a closed space to protect the goods inside. This design not only ensures the safety of the goods, but also facilitates the loading and unloading operations of the goods.
[0031] In this embodiment, a control shaft 17 is provided inside the fuselage 1, and six control arms 18 are distributed around the circumference of the control shaft 17. A motor 19 is provided at the other end of the control arm 18, and the motor 19 is located inside the windproof slot 3. The control shaft 17 is a shaft used to connect and transmit control signals or power, and can control the movement of the multi-rotor lifting structure; the control arm 18 is a component connecting the control shaft 17 and the motor 19, and realizes the transmission of control signals or power; the motor 19 is a component that drives the rotor 4 to rotate, and is connected to the control shaft 17 through the control arm 18 to realize the movement control of the multi-rotor lifting structure.
[0032] It should be noted that: the control shaft 17 is connected to the inside of the fuselage 1 by a threaded connection, the control arm 18 is connected to the control shaft 17 by a threaded connection, the motor 19 is connected to the control arm 18 by a threaded connection, the top of the motor 19 is rotatably connected to the rotor 4, and the rotor 4 is located inside the windproof groove 3.
[0033] In the second embodiment, the multi-rotor buffer structure also includes a buffer platform 9 located on the top of the pad 8, a buffer device 10 is provided at the bottom of the buffer platform 9, and a support platform 11 is provided at the bottom of the buffer device 10, wherein the buffer platform 9 provides a platform for buffering and can absorb part of the impact and vibration; the buffer device 10 is a device for absorbing impact and vibration, which can further enhance the stability of flight; the support platform 11 supports the structure of the pad 8.
[0034] In this embodiment, a piston rod 12 is provided at the top of the buffer device 10, a buffer piston 13 is provided at the bottom of the piston rod 12, a pressure chamber 14 is provided at the bottom of the buffer piston 13, energy accumulators 15 are provided on the left and right sides of the piston rod 12, and a flow hole 16 is provided on the left side of the buffer device 10, wherein the piston rod 12 plays a key connecting and buffering role inside; the buffer piston 13 can move inside the pressure chamber, and when external vibration acts on the buffer piston 13, the buffer piston 13 can move relative to the piston rod 12 to absorb vibration energy; the pressure chamber 14 provides space for the buffer piston 13 and the buffer medium, and under the action of external vibration, allows the buffer piston to move and compress the buffer medium; the energy accumulator 15 is an energy storage device, which can absorb and store energy from external vibration and release it when needed to provide stable support; the flow hole 16 is a hole or channel for controlling fluid flow.
[0035] It should be noted that: the pad 8 is connected to the bracket 7 by a threaded connection, one end of the bottom of the piston rod 12 is connected to the buffer piston 13, and the other end of the piston rod 12 is connected to the buffer platform 9. The buffer piston 13 can slide in the pressure chamber 14, and the buffer piston 13 forms an oil circuit with the pressure chamber 14 and the flow hole 16.
[0036] The working principle of the above embodiment is:
[0037] See also Figure 1-3 When the utility model is in use, first, the telescopic rod 5 is extended and retracted to put the cargo box 6 to a suitable position, and then the required cargo is loaded into the cargo box 6. After the cargo is loaded, the device starts the rotor 4 through the control shaft 17 and the motor 19 to make it reach a preset speed. Under the action of the rotor, the fuselage 1 and the multi-rotor lifting structure begin to rise or fall to achieve vertical take-off and landing. When it is necessary to change the attitude and position, the lift of the rotor 4 can be changed by changing the speed of the motor 19, thereby controlling the attitude and position of the aircraft. For example, increasing the lift on one side can make the aircraft tilt, and vice versa, it can maintain balance. During the flight, the device will be subjected to external impact or vibration, and the pad 8 can control the buffer device 10 to start working, and the buffer piston 13 slides in the pressure chamber 14 to absorb impact and vibration, making the flight more stable; when the aircraft needs to land, the speed of the motor 19 gradually decreases, and the aircraft slowly lands on the ground, and the pad 8 will also start the buffering effect at the same time.
[0038] Beneficial effects of the above embodiments:
[0039] The multi-rotor lifting structure with a buffer platform, through the use of a multi-rotor bracket 2 and a rotor 4, enables the device to quickly change its flight attitude and position, achieve rapid movement and flexible control, and enable the device to have better applicability in certain environments, such as in narrow spaces, low altitudes, complex terrains, etc. In addition, through the use of pads 8, it can better absorb and buffer the vibrations and impacts generated during the flight, further enhancing the stability and safety of the flight.
[0040] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A multi-rotor lifting structure with a buffer platform, comprising a multi-rotor lifting structure, and a multi-rotor buffer structure is arranged at the bottom of the multi-rotor lifting structure; Features: The multi-rotor lifting structure comprises a fuselage (1), a multi-rotor bracket (2) is provided on the top of the fuselage (1), six windproof grooves (3) are provided inside the multi-rotor bracket (2), rotors (4) are provided inside the windproof grooves (3), a telescopic rod (5) is provided at the bottom of the fuselage (1), a cargo box (6) is provided at the bottom of the telescopic rod (5), brackets (7) are provided on the left and right sides of the bottom of the fuselage (1), and a cushion block (8) is provided at the bottom of the bracket (7); The multi-rotor buffer structure comprises a buffer platform (9) located on the top of a cushion block (8), a buffer device (10) is provided at the bottom of the buffer platform (9), and a support platform (11) is provided at the bottom of the buffer device (10).
2. The multi-rotor lifting structure with a buffer platform according to claim 1, characterized in that: The buffer device (10) has a piston rod (12) at the top, a buffer piston (13) at the bottom of the piston rod (12), a pressure chamber (14) at the bottom of the buffer piston (13), energy accumulators (15) at the left and right sides of the piston rod (12), and a flow hole (16) at the left side of the buffer device (10).
3. The multi-rotor lifting structure with a buffer platform according to claim 1, characterized in that: A control shaft (17) is provided inside the fuselage (1), and six control arms (18) are distributed around the circumference of the control shaft (17). A motor (19) is provided at the other end of the control arm (18), and the motor (19) is located inside the windproof slot (3).
4. The multi-rotor lifting structure with a buffer platform according to claim 1, characterized in that: The multi-rotor bracket (2) is connected to the fuselage (1) by means of a threaded connection, the telescopic rod (5) is connected to the fuselage (1) by means of a threaded connection, the cargo box (6) is connected to the telescopic rod (5) by means of a snap connection, a snap block is provided at the bottom of the telescopic rod (5), a snap slot corresponding to the snap block is provided at the top of the cargo box (6), and the telescopic rod (5) is snap-connected to the cargo box (6) by snapping the snap block into the inside of the snap slot.
5. The multi-rotor lifting structure with a buffer platform according to claim 1, characterized in that: A cargo box door is provided in front of the cargo box (6); a door rotating shaft is provided at the connection between the cargo box (6) and the cargo box door on the left side; the door rotating shaft is connected to the cargo box (6) in a rotating connection manner; a card interface is provided at the connection between the cargo box door and the cargo box (6) on the right side; the cargo box door is connected to the cargo box (6) via the card interface.
6. The multi-rotor lifting structure with a buffer platform according to claim 2, characterized in that: The cushion block (8) is connected to the bracket (7) by threaded connection, one end of the bottom of the piston rod (12) is connected to the buffer piston (13), and the other end of the piston rod (12) is connected to the buffer platform (9). The buffer piston (13) can slide in the pressure chamber (14), and the buffer piston (13) forms an oil circuit with the pressure chamber (14) and the flow hole (16).
7. The multi-rotor lifting structure with a buffer platform according to claim 3, characterized in that: The control shaft (17) is connected to the inside of the fuselage (1) by means of a threaded connection, the control arm (18) is connected to the control shaft (17) by means of a threaded connection, the motor (19) is connected to the control arm (18) by means of a threaded connection, the top of the motor (19) is rotatably connected to the rotor (4), and the rotor (4) is located inside the windproof groove (3).