Variable-load multi-rotor unmanned aerial vehicle stabilizing mechanism
By designing variable load stabilization mechanisms on multi-rotor drones, and using embedded slots, electric push rods and other components to achieve dynamic adjustment of the wing limbs, the problem of stable flight of multi-rotor drones at different altitudes and load conditions is solved, and the flight stability and adaptability are significantly improved.
Patent Information
- Application Number
- CN202422059625.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-23
- Publication Date
- 2025-06-10
- Estimated Expiration
- 2034-08-23
AI Technical Summary
Multi-rotor UAVs are difficult to maintain stable flight under different altitudes and load conditions, and the prior art has limited effects in the face of complex and changing meteorological conditions and load changes.
A variable load multi-rotor drone stabilization mechanism is designed. By setting components such as embedded grooves, stabilization rods, electric push rods, linkage coils, telescopic rods and other components on the wing limbs, dynamic adjustment of the wing limbs is achieved and adapted to different heights and air volume conditions.
It significantly improves the flight stability of the multi-rotor drone, can automatically adjust the wing limb distance according to changes in air volume, enhance dynamic stability, and further improve stability through the elastic design of the sealed chamber and the optimization of the air flow of the drainage push plate.
Smart Images
Figure CN222960077U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of multi-rotor unmanned aerial vehicles, and more particularly to a variable-load multi-rotor unmanned aerial vehicle stabilizing mechanism. Background Art
[0002] With the rapid development of unmanned aerial vehicle technology, multi-rotor unmanned aerial vehicles have been widely used in various fields due to their flexibility, ease of operation, and strong adaptability. However, multi-rotor unmanned aerial vehicles face various challenges during flight, especially how to maintain a stable flight state under different environmental and load conditions. Traditional multi-rotor unmanned aerial vehicle stabilization systems often rely on electronic control systems, such as gyroscopes and accelerometers, to sense the flight attitude and make corresponding adjustments. Although these systems can provide stability to a certain extent, their effects may be limited when facing complex and changeable weather conditions and load changes.
[0003] In the prior art, during the use of multi-rotor unmanned aerial vehicles, they often need to perform tasks at different altitudes, and these different altitudes will cause significant changes in environmental factors such as wind speed, wind direction, and atmospheric density. For example, as the altitude increases, the atmospheric pressure decreases, and the wind speed may increase, which poses a challenge to the stable flight of the unmanned aerial vehicle. In addition, when the multi-rotor unmanned aerial vehicle carries different weights or performs specific tasks, its power requirements and flight characteristics will also change, which requires the unmanned aerial vehicle to be able to quickly adapt to the load changes; therefore, we make improvements and propose a variable-load multi-rotor unmanned aerial vehicle stabilizing mechanism. Summary of the Utility Model
[0004] The purpose of the present utility model is to address the problem that the current design of multi-rotor unmanned aerial vehicles cannot adjust the direction and distance of the wing limbs according to the influence of wind resistance at various different altitudes.
[0005] To achieve the above utility model purpose, the present utility model provides the following technical solutions:
[0006] A variable-load multi-rotor unmanned aerial vehicle stabilizing mechanism to improve the above problems.
[0007] Specifically, this application is as follows:
[0008] A variable-load multi-rotor UAV stabilization mechanism, including a multi-wing UAV. Embedding grooves are provided on the wing limbs of the multi-wing UAV. A stabilizing rod is provided at the inner end of the embedding groove. An electric push rod is provided between the stabilizing rods. A linkage ring is provided at the outer end of the electric push rod. A telescopic rod is provided at the outer end of the linkage ring. A ring groove is provided at the tail end of the telescopic rod. A linkage ring block is provided at the inner end of the ring groove. An embedded plate is provided at the outer end of the linkage ring block. An embedded groove is provided at the outer end of the embedded plate. An airtight chamber is provided at the inner end of the embedded groove. A drainage push plate is provided at the outer end of the airtight chamber. An embedded slider is provided at the outer end of the drainage push plate. An embedded chute is provided at the outer end of the embedded slider. A drainage plate is provided at the outer end of the embedded chute.
[0009] As a preferred technical solution of the present application, the embedding grooves are embedded and installed on the four sides of the multi-wing UAV. The number of the embedding grooves is set to four. Two of the embedding grooves are paired for use, and the other two embedding grooves are also paired for use.
[0010] As a preferred technical solution of the present application, the embedding grooves are movably connected to the electric push rods. The center of the electric push rod is movably connected to the linkage ring. The outer end of the linkage ring is fixedly connected to the movable end of the telescopic rod. The fixed end of the telescopic rod is fixedly installed at the inner end of the ring groove. The ring groove is embedded and installed at the inner end of the multi-wing UAV.
[0011] As a preferred technical solution of the present application, the linkage ring block is fixedly connected to the wing limb of the multi-wing UAV. The linkage ring block rotates along the ring groove. The rear end of the linkage ring block is fixedly connected to the embedded plate. The embedded plate slides along the inner end of the embedded groove. The two embedded plates are fixedly connected to the two ends of the airtight chamber.
[0012] As a preferred technical solution of the present application, the airtight chamber is made of an elastic material. The outer end of the airtight chamber is fixedly connected to the tail end of the drainage push plate. The upper and lower ends of the drainage push plate are both fixedly connected to the embedded slider.
[0013] As a preferred technical solution of the present application, the outer end of the embedded slider is slidably connected to the embedded chute. The embedded chute is embedded and installed on the inner surfaces of the upper and lower ends of the drainage plate.
[0014] Compared with the prior art, the beneficial effects of the present utility model are:
[0015] In the solution of the present application:
[0016] The variable-load multi-rotor UAV stabilization mechanism proposed in this embodiment realizes a significant improvement in the flight stability of the UAV through a series of innovative designs and mechanical structures. Especially under different heights and air volume conditions, through the telescopic movement of the electric push rod, it is convenient to adjust the angle of the wing limb, facilitating the adaptability and dynamic adjustment of the variable-load multi-rotor UAV stabilization mechanism under different heights and conditions;
[0017] Variable Load Adaptation Mechanism: The stabilization mechanism proposed in this embodiment can automatically adjust the distance between the wing limbs of the multi-rotor UAV according to the change in air volume at different heights to adapt to different flight environments and improve flight stability;
[0018] Enhanced Dynamic Stability: Through the coordinated operation of components such as electric push rods, linkage rings, and telescopic rods, dynamic adjustment of the wing limbs is achieved, effectively coping with wind changes and ensuring the stable flight of the UAV in various wind conditions;
[0019] Elastic Design of the Sealed Chamber: The sealed chamber is made of elastic material, which can provide buffering during the adjustment of the wing limbs. At the same time, through the action of the drainage push plate, the air flow path is optimized to further enhance stability;
[0020] Modular Design: Each component such as the embedding groove, stabilizing rod, and electric push rod adopts a modular design, which is convenient for installation, maintenance, and upgrading. Description of the Drawings
[0021] Figure 1 It is a schematic diagram of the overall structure of the variable load multi-rotor UAV stabilization mechanism provided by this application;
[0022] Figure 2 It is a bottom-up structural view of the cross-section of the electric push rod of the variable load multi-rotor UAV stabilization mechanism provided by this application;
[0023] Figure 3 It is the Figure 2 magnified structural schematic diagram of A in the variable load multi-rotor UAV stabilization mechanism provided by this application;
[0024] Figure 4 It is the Figure 2 magnified structural schematic diagram of B in the variable load multi-rotor UAV stabilization mechanism provided by this application;
[0025] Figure 5 It is a side-sectional structural schematic diagram of the linkage ring block of the variable load multi-rotor UAV stabilization mechanism provided by this application;
[0026] Figure 6 It is a bottom-up cross-sectional view of the ring groove of the variable load multi-rotor UAV stabilization mechanism provided by this application.
[0027] Labels in the figure:
[0028] 1. Multi-wing UAV; 2. Stabilizing rod; 3. Electric push rod; 4. Linkage ring; 5. Telescopic rod; 6. Ring groove; 7. Linkage ring block; 8. Embedded plate; 9. Embedding groove; 10. Sealed chamber; 11. Drainage plate; 12. Drainage push plate; 13. Embedded slider; 14. Embedding chute. Detailed Implementation Manner
[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present utility model clearer, the technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some, but not all, of the embodiments of the present utility model.
[0030] Therefore, the following detailed description of the embodiments of the present utility model is not intended to limit the scope of the present utility model claimed, but merely represents some embodiments of the present utility model. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts fall within the scope of protection of the present utility model. It should be noted that, without conflict, the embodiments in the present utility model and the features and technical solutions in the embodiments may be combined with each other.
[0031] It should be noted that similar reference numerals and letters denote similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.
[0032] As Figure 1-6 shown, this embodiment provides a variable-load multi-rotor UAV stabilization mechanism, including a multi-wing UAV 1. Embedding grooves are provided on the wing limbs of the multi-wing UAV 1. Stabilizing rods 2 are provided at the inner ends of the embedding grooves. Electric push rods 3 are provided between the stabilizing rods 2. A linkage ring 4 is provided at the outer end of the electric push rod 3. A telescopic rod 5 is provided at the outer end of the linkage ring 4. A ring groove 6 is provided at the tail end of the telescopic rod 5. A linkage ring block 7 is provided at the inner end of the ring groove 6. An embedded plate 8 is provided at the outer end of the linkage ring block 7. An embedded groove 9 is provided at the outer end of the embedded plate 8. An airtight chamber 10 is provided at the inner end of the embedded groove 9. A drainage push plate 12 is provided at the outer end of the airtight chamber 10. An embedded slider 13 is provided at the outer end of the drainage push plate 12. An embedded chute 14 is provided at the outer end of the embedded slider 13. A drainage plate 11 is provided at the outer end of the embedded chute 14.
[0033] It can automatically adjust the distance between the wing limbs of the multi-rotor UAV according to the change in the air volume at different heights to adapt to different flight environments and improve flight stability.
[0034] Through the coordinated work of components such as the electric push rod 3, the linkage ring 4, and the telescopic rod 5, dynamic adjustment of the wing limbs is achieved, effectively coping with wind changes and ensuring stable flight of the UAV under various wind conditions.
[0035] Elastic design of the airtight chamber 10: The airtight chamber 10 is made of an elastic material, which can provide buffering during the adjustment of the wing limbs. At the same time, through the action of the drainage push plate 12, the air flow path is optimized to further enhance stability.
[0036] Modular design: Each component such as the embedding groove, the stabilizing rod 2, and the electric push rod 3 adopts a modular design, which is convenient for installation, maintenance, and upgrade.
[0037] The embedding slots are embedded and installed on the four sides of the multi-wing unmanned aerial vehicle 1. The number of embedding slots is set to four, with two of them paired for use and the other two also paired for use.
[0038] Embedding slots and stabilizing rods 2: By setting embedding slots and stabilizing rods 2 on the wing limbs of the multi-wing unmanned aerial vehicle 1, the adjustability of the wing limbs is achieved, providing a basis for subsequent dynamic adjustment.
[0039] The embedding slots are movably connected to the electric push rods 3. The center of the electric push rods 3 is movably connected to the linkage ring 4. The outer end of the linkage ring 4 is fixedly connected to the movable end of the telescopic rod 5. The fixed end of the telescopic rod 5 is fixedly installed at the inner end of the ring groove 6, and the ring groove 6 is embedded and installed at the inner end of the multi-wing unmanned aerial vehicle 1.
[0040] Electric push rods 3 and linkage ring 4: The design of the electric push rods 3 enables the distance between the wing limbs to be precisely adjusted according to the wind volume, while the linkage ring 4 ensures the synchronization during the adjustment process.
[0041] Telescopic rod 5 and ring groove 6: The coordinated use of the telescopic rod 5 and the ring groove 6 enables the wing limbs to move smoothly during the adjustment process, reducing mechanical shock.
[0042] The linkage ring block 7 is fixedly connected to the wing limb of the multi-wing unmanned aerial vehicle 1. The linkage ring block 7 rotates along the ring groove 6. The rear end of the linkage ring block 7 is fixedly connected to the inner embedding plate 8. The inner embedding plate 8 slides along the inner end of the inner embedding groove 9. The two inner embedding plates 8 are fixedly connected to the two ends of the sealed chamber 10.
[0043] Linkage ring block 7 and inner embedding plate 8: The design of the linkage ring block 7 and the inner embedding plate 8 makes the movement of the wing limb more flexible and also enhances the structural stability.
[0044] The sealed chamber 10 is made of elastic material. The outer end of the sealed chamber 10 is fixedly connected to the tail end of the drainage push plate 12. The upper and lower ends of the drainage push plate 12 are both fixedly connected to the embedding sliders 13.
[0045] Sealed chamber 10 and drainage push plate 12: The elastic material of the sealed chamber 10 and the design of the drainage push plate 12 can not only absorb shock but also guide air flow, reduce wind resistance, and improve flight efficiency.
[0046] The outer end of the embedding slider 13 is slidably connected to the embedding chute 14. The embedding chute 14 is embedded and installed on the inner surfaces of the upper and lower ends of the drainage plate 11.
[0047] Embedded slider 13 and embedded chute 14: The sliding connection between the embedded slider 13 and the embedded chute 14 ensures the smoothness of the drainage push plate 12 during movement, thereby improving the response speed and accuracy of the entire stabilization mechanism.
[0048] Air volume is usually used to describe the volume of air passing through a certain cross-section per unit time. The commonly used units are cubic meters per hour or cubic feet per minute.
[0049] The description of air volume at different heights usually involves changes in wind speed and wind pressure. Since atmospheric pressure decreases with increasing height, this will affect the performance of the fan or ventilation system.
[0050] A specific embodiment:
[0051] (1) Startup preparation:
[0052] Before the multi-rotor UAV 1 takes off, check whether all mechanical components are intact, especially key components such as the embedded groove, stabilizing rod 2, electric push rod 3, linkage ring 4, telescopic rod 5, sealed chamber 10, drainage push plate 12, and embedded slider 13;
[0053] Confirm that the battery of the multi-rotor UAV 1 has sufficient power and all electronic control systems are working properly.
[0054] (2) Initial setting:
[0055] According to the predetermined flight mission and target altitude, set the initial position of the electric push rod 3 through the ground control station or remote controller to determine the initial distance between the wing limbs. This distance should be suitable for the expected load and flight environment.
[0056] (3) Takeoff:
[0057] Start the multi-rotor UAV 1 and make it vertically ascend to the predetermined altitude. During the ascent, the electronic control system of the multi-rotor UAV 1 will continuously monitor the flight attitude and environmental parameters.
[0058] (4) Environmental monitoring and adjustment:
[0059] Once the target altitude is reached, the sensors on the multi-rotor UAV 1 will start to monitor environmental factors such as wind speed, wind direction, and atmospheric density;
[0060] If the detected air volume exceeds the preset safety range, the electronic control system will send a command to the electric push rod 3 to activate the automatic adjustment function of the stabilization mechanism.
[0061] (5) Stabilization mechanism action:
[0062] After receiving the instruction, the electric push rod 3 will adjust the distance between the wing limbs according to the size of the air volume. If the air volume is too large, the electric push rod 3 will contract, bringing the wing limbs closer and reducing the windward area; conversely, if the air volume is small, the electric push rod 3 will extend, increasing the distance between the wing limbs to optimize the flight efficiency;
[0063] The linkage ring 4 rotates accordingly, driving the telescopic rod 5 to move. The contraction or extension of the telescopic rod 5 will be transmitted to the wing limbs through the annular groove 6, enabling them to move back and forth;
[0064] The movement of the wing limbs will act on the sealed chamber 10 through the linkage ring block 7 and the embedded plate 8. The elastic deformation of the sealed chamber 10 pushes the drainage push plate 12 to move along the drainage plate 11, changing the air flow path, thereby enhancing the stability of the multi-wing unmanned aerial vehicle 1.
[0065] (6) Continuous monitoring and fine-tuning:
[0066] During the flight, the multi-wing unmanned aerial vehicle 1 will continuously monitor the environmental changes and make fine-tuning as needed. The design of the stabilization mechanism allows the multi-wing unmanned aerial vehicle 1 to maintain a stable flight state under different wind force and load conditions.
[0067] (7) Landing:
[0068] After completing the task, the multi-wing unmanned aerial vehicle 1 will return to the takeoff and landing point and gradually reduce its altitude to prepare for landing. During this process, the stabilization mechanism will continue to work until the multi-wing unmanned aerial vehicle 1 lands safely.
[0069] (8) Shutdown and inspection:
[0070] After landing, turn off the power of the multi-wing unmanned aerial vehicle 1 and conduct a detailed inspection of the entire stabilization mechanism to ensure that there are no damaged or abnormally worn components. If necessary, perform cleaning and maintenance for the next use;
[0071] Through the above operation process, the variable-load multi-rotor unmanned aerial vehicle stabilization mechanism based on the actual situation can effectively improve the flight stability and safety of the multi-wing unmanned aerial vehicle 1 in complex environments.
[0072] When this application is in use: When a multi-rotor unmanned aerial vehicle (UAV) is flying, according to the volume of air passing through the multi-rotor UAV per unit time at different heights, when the volume of air passing through the multi-rotor UAV per unit time at different heights is too large, the distance between the front wing limbs is reduced; when the volume of air passing through the multi-rotor UAV per unit time at different heights is relatively small, the distance between the front wing limbs is increased. Control the telescopic movement of the electric push rod 3. When the electric push rod 3 expands outwards, the telescopic rod 5 connected through the linkage ring 4 contracts. When the telescopic rod 5 contracts, the wing limbs of the multi-wing UAV 1 move forward and backward in pairs through the linkage ring block 7 and the embedded plate 8, and squeeze the corresponding sealed chamber 10 forward or backward, pushing the corresponding drainage push plate 12 to be pushed outwards along the drainage plate 11. When the drainage plate 11 is pushed outwards, it can facilitate the flow of air during flight to both ends, ensuring the stability of the multi-rotor UAV during flight.
[0073] The above embodiments are only used to illustrate the present invention and do not limit the technical solutions described in the present invention. Although this specification has described the present invention in detail with reference to the above respective embodiments, the present invention is not limited to the above specific embodiments. Therefore, any modification or equivalent replacement to the present invention; and all technical solutions and their improvements that do not depart from the spirit and scope of the present invention are covered by the scope of the claims of the present invention.
Claims
1. A variable load multi-rotor UAV stabilization mechanism, comprising a multi-rotor UAV (1), characterized in that: The wing limbs of the multi-wing UAV (1) are all provided with an embedding groove, the inner end of the embedding groove is provided with a stabilizing rod (2), an electric push rod (3) is provided between the stabilizing rods (2), the outer end of the electric push rod (3) is provided with a linkage ring (4), the outer end of the linkage ring (4) is provided with a telescopic rod (5), the tail end of the telescopic rod (5) is provided with an annular groove (6), the inner end of the annular groove (6) is provided with a linkage ring block (7), the outer end of the linkage ring block (7) is provided with an inner embedded plate (8), the outer end of the inner embedded plate (8) is provided with an inner embedded groove (9), the inner end of the inner embedded groove (9) is provided with a closed chamber (10), the outer end of the closed chamber (10) is provided with a drainage push plate (12), the outer end of the drainage push plate (12) is provided with an embedded slider (13), the outer end of the embedded slider (13) is provided with an embedded slide groove (14), and the outer end of the embedded slide groove (14) is provided with a drainage plate (11).
2. The variable load multi-rotor UAV stabilization mechanism according to claim 1, characterized in that: The embedding slots are embedded and installed on four sides of the multi-wing UAV (1), and the number of the embedding slots is set to four, two of which are used in pairs, and the other two are also used in pairs.
3. The variable load multi-rotor UAV stabilization mechanism according to claim 2, characterized in that: The embedding grooves are movably connected to the electric push rod (3), the center of the electric push rod (3) is movably connected to the linkage ring (4), the outer end of the linkage ring (4) is fixedly connected to the movable end of the telescopic rod (5), the fixed end of the telescopic rod (5) is fixedly installed on the inner end of the annular groove (6), and the annular groove (6) is embedded and installed on the inner end of the multi-wing UAV (1).
4. The variable load multi-rotor UAV stabilization mechanism according to claim 3, characterized in that: The linkage ring block (7) is fixedly connected to the wing limb of the multi-wing UAV (1); the linkage ring block (7) rotates along the ring groove (6); the rear end of the linkage ring block (7) is fixedly connected to the inner panel (8); the inner panel (8) slides along the inner end of the inner groove (9); and the two inner panels (8) are fixedly connected to the two ends of the sealed chamber (10).
5. The variable load multi-rotor UAV stabilization mechanism according to claim 4, characterized in that: The sealed chamber (10) is made of elastic material, the outer end of the sealed chamber (10) is fixedly connected to the rear end of the drainage push plate (12), and the upper and lower ends of the drainage push plate (12) are fixedly connected to the embedded slider (13).
6. The variable load multi-rotor UAV stabilization mechanism according to claim 5, characterized in that: The outer end of the embedded sliding block (13) is slidably connected to the embedded sliding groove (14), and the embedded sliding groove (14) is embedded and installed on the inner surfaces of the upper and lower ends of the guide plate (11).