Unmanned aerial vehicle flight controller
By combining airbags and magnetic force for cushioning, the problem of fatigue caused by spring buffers is solved, achieving reliable protection and stable flight of the UAV flight controller and reducing maintenance costs.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-16
- Publication Date
- 2026-04-07
AI Technical Summary
In existing drone flight controllers, the spring buffer structure is prone to fatigue and decreased elasticity during long-term use, leading to the need for frequent inspection and replacement, which increases maintenance costs and workload.
It adopts a buffer method that combines airbags and magnetic force. Through the rapid expansion of the airbags and the magnetic pressure, it provides more reliable protection, avoids damage to internal components, and extends service life.
It significantly extends the service life of the buffer structure, reduces maintenance costs and workload, and improves the reliability and stability of UAVs in complex environments.
Smart Images
Figure CN224090448U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a UAV flight controller. Background Technology
[0002] The drone flight controller is the core control system of a drone, which is equivalent to the "brain" of the drone. The flight controller uses various built-in sensors to perceive the drone's attitude, position, speed and other information in real time. Then, according to the preset flight parameters and flight mission, it precisely controls the drone's motors, control surfaces and other actuators, thereby realizing the drone's stable flight, attitude adjustment and trajectory planning functions. It is a key component that enables drones to fly autonomously.
[0003] The flight controller is the core component of a drone, integrating a large number of sophisticated electronic components and sensors. These components are very sensitive to vibration and shock. Buffering can effectively reduce the damage to these components from external impacts and extend their service life.
[0004] In existing technologies, springs are installed to cushion the impact on the flight controller. Although this method can reduce the impact force to a certain extent, the springs are prone to fatigue during long-term repeated use. As the usage time increases, the elasticity of the springs will gradually decrease, and the cushioning capacity will also weaken. This requires the springs to be inspected and replaced regularly, thereby increasing the maintenance cost and workload of the UAV. Therefore, a UAV flight controller is proposed to address the above problems. Utility Model Content
[0005] The purpose of this invention is to provide a drone flight controller that addresses the problem of springs being used to cushion impacts on the flight controller. Springs are prone to fatigue during long-term, repeated use, and their elasticity gradually decreases with use, weakening their cushioning ability. This necessitates regular inspection and replacement of the springs, increasing the maintenance cost and workload of the drone.
[0006] To achieve the above objectives, this utility model provides the following technical solution:
[0007] A drone flight controller includes a drone component and a flight controller body. A protective shell component is fixedly connected to the inner side of the drone component. The protective shell component is electrically connected to a connecting flexible wire. An airbag buffer component is fixedly connected to the inner side of the protective shell component. The drone component includes a cover. A cover plate is fixedly connected to the top and bottom of the cover. A first permanent magnet block is fixedly connected to one side of the cover plate. A cylindrical airbag is fixedly connected to the inner side of the cover. The airbag buffer component includes an airbag pad. An air vent is opened at one end of the airbag pad. The airbag pad is fixedly connected to a corrugated airbag. An air outlet groove is opened on the inner side of the corrugated airbag. A second permanent magnet block is fixedly connected to the end of the corrugated airbag away from the air vent. The second permanent magnet block slides on the inner side of the anti-detachment sleeve.
[0008] As a further optimization of this utility model, the protective shell assembly includes a fixed shell, a rubber pad is fixedly connected to the inner side of the fixed shell, and mounting bases are fixedly connected to the top and bottom ends of the fixed shell. The inner side of the rubber pad is hollow, and the upper and lower ends of the rubber pad are through structures. The outer side of the fixed shell is fixedly connected to a cylindrical airbag.
[0009] As a further optimization of this utility model, the mounting base has an installation hole on its inner side, which is fixedly connected to the outer side of the anti-detachment sleeve, and the anti-detachment sleeve extends out of the outer side of the mounting base.
[0010] As a further optimization of this utility model, the number of air vents is two, the air vents are fixedly connected to the mounting base, the top and bottom ends of the flight controller body are fixed to the outside of the air vents by adhesive, and a gap is provided between the horizontal outer side of the flight controller body and the inner side of the rubber pad.
[0011] As a further optimization of this utility model, the inner side of the anti-detachment sleeve is hollow, the upper and lower ends of the anti-detachment sleeve are through structures, the corrugated airbag is embedded inside the anti-detachment sleeve, a limit rod is fixed at the bottom of the anti-detachment sleeve, and the limit rod of the anti-detachment sleeve is located at the lower end of the second permanent magnet block.
[0012] As a further optimization of this utility model, the air outlet groove extends through one end of the corrugated airbag, the inner side of the airbag pad is a hollow structure, and the air outlet groove is connected to the inner side of the airbag pad through an air passage.
[0013] As a further optimization of this utility model, the second permanent magnet block is aligned vertically with the first permanent magnet block, the second permanent magnet block and the first permanent magnet block are magnetically repelled, the number of the second permanent magnet blocks is the same as the number of the first permanent magnet blocks, and the diameter of the first permanent magnet block is three times the diameter of the second permanent magnet block.
[0014] Compared with the prior art, the beneficial effects of this utility model are:
[0015] In this invention, the device employs a combination of airbags and magnetic structures to buffer the drone's flight controller. This innovative design significantly extends the lifespan of the buffer structure and reduces the need for frequent inspections and replacements due to spring fatigue, thereby greatly reducing the maintenance costs and workload of the drone. Furthermore, the rapid expansion of the airbags and the active pressurization of the magnetic force enhance the timeliness and effectiveness of the buffer. This design provides more reliable protection for the flight controller in the event of an accidental collision, ensuring that its internal precision electronic components and sensors are not damaged by impact. This, in turn, guarantees the drone's stable and autonomous flight capabilities and improves the reliability and lifespan of the drone in complex environments. Attached Figure Description
[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model;
[0017] Figure 2 This is a cross-sectional structural diagram of the UAV component of this utility model;
[0018] Figure 3 This is an exploded structural diagram of the UAV component of this utility model;
[0019] Figure 4 This is a schematic diagram of the main structure of the flight controller of this utility model;
[0020] Figure 5 This is a cross-sectional structural diagram of the airbag cushion of this utility model;
[0021] Figure 6 This is a cross-sectional structural diagram of the corrugated airbag of this utility model;
[0022] Figure 7 This is a schematic diagram of the anti-detachment sleeve structure of this utility model.
[0023] In the diagram: 1. Unmanned aerial vehicle (UAV) component; 11. Shell; 12. Cover plate; 13. First permanent magnet block; 14. Cylindrical airbag;
[0024] 2. Flight controller body; 3. Connecting cable;
[0025] 4. Protective housing assembly; 41. Fixing housing; 42. Rubber pad; 43. Mounting base;
[0026] 5. Airbag cushioning assembly; 51. Airbag pad; 52. Air vent; 53. Corrugated airbag; 54. Air outlet groove; 55. Second permanent magnet block; 56. Anti-detachment sleeve. Detailed Implementation
[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.
[0028] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.
[0029] Please see Figure 1-7 This utility model provides a technical solution:
[0030] A drone flight controller includes a drone component 1 and a flight controller body 2. A protective shell component 4 is fixedly connected to the inside of the drone component 1. The protective shell component 4 is electrically connected to a connecting cable 3. An airbag buffer component 5 is fixedly connected to the inside of the protective shell component 4. The drone component 1 includes a cover 11. A cover plate 12 is fixedly connected to the top and bottom of the cover 11. A first permanent magnet block 13 is fixedly connected to one side of the cover plate 12. A cylindrical airbag 14 is fixedly connected to the inside of the cover 11. The airbag buffer component 5 includes an airbag pad 51. An air vent 52 is opened at one end of the airbag pad 51. The airbag pad 51 is fixedly connected to a corrugated airbag 53. An air outlet groove 54 is opened on the inside of the corrugated airbag 53. A second permanent magnet block 55 is fixedly connected to the end of the corrugated airbag 53 away from the air vent 52. The second permanent magnet block 55 slides on the inside of an anti-detachment sleeve 56.
[0031] As a further implementation of this solution, the protective shell assembly 4 includes a fixed shell 41, a rubber pad 42 fixedly connected to the inner side of the fixed shell 41, and mounting bases 43 fixedly connected to the top and bottom of the fixed shell 41. The inner side of the rubber pad 42 is hollow, and the upper and lower ends of the rubber pad 42 are through structures. The outer side of the fixed shell 41 is fixedly connected to the cylindrical airbag 14. Through the above settings, the flight controller body 2 and other related components can be firmly installed and fixed, providing a solid foundation for the entire buffer device and ensuring that the components will not loosen or shift during operation, thereby improving the overall stability and reliability of the device.
[0032] As a further implementation of this solution, an installation hole is provided on the inner side of the mounting base 43. The installation hole on the inner side of the mounting base 43 is fixedly connected to the outer side of the anti-detachment sleeve 56. The anti-detachment sleeve 56 extends out of the outer side of the mounting base 43. Through the above-mentioned arrangement, the installation hole is provided on the inner side of the mounting base 43 and fixedly connected to the anti-detachment sleeve 56, so that the anti-detachment sleeve 56 can be stably installed on the mounting base 43. At the same time, the design of the anti-detachment sleeve 56 extending out of the outer side of the mounting base 43 provides space for the deformation of the corrugated airbag 53.
[0033] As a further implementation of this solution, there are two air vents 52. The air vents 52 are fixedly connected to the mounting base 43. The top and bottom ends of the flight controller body 2 are fixed to the outside of the air vents 52 by adhesive. There is a gap between the horizontal outer side of the flight controller body 2 and the inner side of the rubber pad 42. Through the above settings, multi-directional support and limiting of the flight controller body 2 are formed, ensuring that it always maintains a stable position inside the buffer device, thereby improving the protection effect of the flight controller and enhancing the device's protection capability for the flight controller, enabling it to better resist external impacts in complex environments.
[0034] As a further implementation of this solution, the inner side of the anti-detachment sleeve 56 is hollow, and both the upper and lower ends of the anti-detachment sleeve 56 are through structures. The corrugated airbag 53 is embedded inside the anti-detachment sleeve 56, and a limiting rod is fixed at the bottom of the anti-detachment sleeve 56. The limiting rod of the anti-detachment sleeve 56 is located at the lower end of the second permanent magnet block 55. Through the above settings, the airbag can be smoothly inflated and deflated, thereby realizing the buffer function. At the same time, the corrugated airbag 53 embedded inside the anti-detachment sleeve 56 and the setting of the limiting rod can effectively fix and limit the corrugated airbag 53, preventing it from shifting or loosening under the action of airflow, ensuring the structural stability and reliability of the airbag, and further improving the performance and service life of the buffer device.
[0035] As a further implementation of this solution, the air outlet groove 54 penetrates one end of the corrugated airbag 53. The inner side of the airbag pad 51 is a hollow structure. The air outlet groove 54 is connected to the inner side of the airbag pad 51 through the air passage 52. The second permanent magnet block 55 is aligned vertically with the first permanent magnet block 13. The second permanent magnet block 55 and the first permanent magnet block 13 are magnetically repelled. The number of second permanent magnet blocks 55 is the same as the number of first permanent magnet blocks 13. The diameter of the first permanent magnet block 13 is three times the diameter of the second permanent magnet block 55. Through the above arrangement, a strong magnetic repulsive force can be generated. This magnetic repulsive force can quickly generate a reverse force when the flight controller is impacted, further enhancing the buffering effect and preventing the flight controller from directly colliding with the outer shell of the device. This effectively protects the precision components inside the flight controller. At the same time, this combination of magnetic buffering and airbag buffering achieves the dual effects of passive buffering and active pressurization, significantly improving the performance and reliability of the buffering device and extending the service life of the flight controller.
[0036] Workflow: When protecting the flight controller body 2 of the drone, in the event of an accidental collision, the deformation of the cylindrical airbag 14 provides horizontal protection and cushioning for the flight controller body 2 inside the protective shell assembly 4, preventing the protective shell assembly 4 from colliding with the cover 11. Simultaneously, the rubber pad 42 further enhances the protective performance of the flight controller body 2. Since the size of the first permanent magnet block 13 is three times the size of the second permanent magnet block 55, when the protective shell assembly 4 moves, the second permanent magnet block 55 remains magnetically repelled by the first permanent magnet block 13. Multiple first permanent magnet blocks... The cooperation of the first permanent magnet block 13 and the second permanent magnet block 55 allows the protective shell assembly 4 to suspend in the middle of the cover 11. When the protective shell assembly 4 moves up and down, and when the protective shell assembly 4 and the flight controller body 2 move downwards, the second permanent magnet block 55 will compress the corrugated airbag 53 under the magnetic repulsion between the second permanent magnet block 55 and the lower first permanent magnet block 13. This causes the gas inside the exhaust groove 54 to enter the airbag pad 51 through the air vent 52, causing the lower airbag pad 51 to expand. In this way, the expansion of the airbag pad 51 not only improves the stability of the flight controller body 2 inside the rubber pad 42, but also... When the flight controller body 2 moves downward, the inflated airbag 51 at the lower end cushions the flight controller body 2. This ensures that even under pressure from the flight controller body 2, the airbag 51 remains inflated, preventing damage to the flight controller body 2. Conversely, when the flight controller body 2 moves upward, the upper airbag 51 protects the flight controller body 2. When the protective shell assembly 4 moves up and down, the connecting cable 3 bends. The connecting cable 3 is a flexible cable that passes through the fixed shell 41 and the rubber pad 42 and is electrically connected to the flight controller body 2. The connecting cable 3 is then connected to the propeller driven by the UAV assembly 1 via wiring. Electromechanical connections provide a reasonable electrical connection method for the device. After buffering, the airbag cushion 51 recovers its deformation, allowing the gas inside the airbag cushion 51 to refill the air outlet groove 54, preparing for another buffering. Based on the above principles, the device replaces the traditional spring with multiple airbags, which not only provides buffering protection for the flight controller body 2, but also adds active pressurization through the structure of airbags and magnetic force on the basis of airbags as buffers. After the flight controller body 2 is impacted, the airbags expand rapidly, improving the buffering effect. Moreover, the device reduces maintenance costs and improves the timeliness and effectiveness of airbag buffering.
[0037] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.
Claims
1. A drone flight controller, comprising a drone component (1) and a flight controller body (2), characterized in that: The inner side of the drone component (1) is fixedly connected to a protective shell component (4), the protective shell component (4) is electrically connected to a connecting cable (3), and the inner side of the protective shell component (4) is fixedly connected to an airbag buffer component (5). The drone component (1) includes a shell (11), a cover plate (12) is fixedly connected to the top and bottom of the shell (11), a first permanent magnet block (13) is fixedly connected to one side of the cover plate (12), and a cylindrical airbag (14) is fixedly connected to the inside of the shell (11). The airbag cushioning assembly (5) includes an airbag pad (51), one end of which has an air passage hole (52). The airbag pad (51) is fixedly connected to the corrugated airbag (53). An air outlet groove (54) is provided on the inner side of the corrugated airbag (53). A second permanent magnet block (55) is fixedly connected to the end of the corrugated airbag (53) away from the air passage hole (52). The second permanent magnet block (55) slides on the inner side of the anti-detachment sleeve (56).
2. The UAV flight controller according to claim 1, characterized in that: The protective shell assembly (4) includes a fixed shell (41), a rubber pad (42) is fixedly connected to the inner side of the fixed shell (41), and mounting bases (43) are fixedly connected to the top and bottom of the fixed shell (41). The inner side of the rubber pad (42) is hollow, and the upper and lower ends of the rubber pad (42) are through structures. The outer side of the fixed shell (41) is fixedly connected to the cylindrical airbag (14).
3. A UAV flight controller according to claim 2, characterized in that: The mounting base (43) has an installation hole on its inner side. The installation hole on the inner side of the mounting base (43) is fixedly connected to the outer side of the anti-detachment sleeve (56). The anti-detachment sleeve (56) extends out of the outer side of the mounting base (43).
4. A UAV flight controller according to claim 1, characterized in that: There are two air vents (52). The air vents (52) are fixedly connected to the mounting base (43). The top and bottom of the flight controller body (2) are fixed to the outside of the air vents (52) by adhesive. There is a gap between the horizontal outer side of the flight controller body (2) and the inner side of the rubber pad (42).
5. A UAV flight controller according to claim 1, characterized in that: The inner side of the anti-detachment sleeve (56) is hollow. The upper and lower ends of the anti-detachment sleeve (56) are through structures. The corrugated airbag (53) is embedded in the inside of the anti-detachment sleeve (56). The bottom end of the anti-detachment sleeve (56) is fixed with a limiting rod. The limiting rod of the anti-detachment sleeve (56) is located at the lower end of the second permanent magnet block (55).
6. A UAV flight controller according to claim 1, characterized in that: The air outlet groove (54) passes through one end of the corrugated airbag (53), the inner side of the airbag pad (51) is a hollow structure, and the air outlet groove (54) is connected to the inner side of the airbag pad (51) through the air passage hole (52).
7. A UAV flight controller according to claim 1, characterized in that: The second permanent magnet block (55) is aligned vertically with the first permanent magnet block (13). The second permanent magnet block (55) and the first permanent magnet block (13) are magnetically repulsive. The number of the second permanent magnet blocks (55) is the same as the number of the first permanent magnet blocks (13). The diameter of the first permanent magnet block (13) is three times the diameter of the second permanent magnet block (55).