Damping fixing structure for unmanned aerial vehicle flight controller
Patent Information
- Application Number
- CN202620159710.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2026-02-03
- Publication Date
- 2026-10-23
- Estimated Expiration
- 2036-02-03
AI Technical Summary
[0004]然而，无人机机身的振动主要来自飞行过程中的气动干扰，这类振动若直接传递至飞行控制器，振动会破坏飞行控制器内部电子元件的工作稳定性，导致控制精度下降，无人机姿态控制出现偏差，严重时甚至引发飞行失控
（1）本申请由于采用了一级减震机构，解决了无人机自身动力系统与飞行气动干扰导致机身振动过大的问题，通过一级减震机构的柔性连接设计，有效阻断了振动传递路径，避免振动直接传递至飞行控制器，保障了飞行控制器的控制精度，提升了无人机姿态控制的稳定性，延长了飞行控制器的使用寿命。
Smart Images
Figure CN224882280U_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a shock-absorbing fixing structure for a UAV flight controller. Background Technology
[0002] Unmanned aerial vehicles (UAVs), also known as drones, are aircraft that do not require a human pilot to operate and complete flight missions through remote control or autonomous flight control systems. With the development of electronic technology, navigation systems, artificial intelligence, and materials science, UAVs have been widely used in military, civilian, and commercial fields.
[0003] The drone flight controller is the core brain of the drone, responsible for sensing the flight status, processing data, executing control algorithms, and sending instructions to the power system and actuators to achieve stable, safe, and precise flight.
[0004] However, the vibration of the drone's fuselage mainly comes from aerodynamic interference during flight. If such vibration is directly transmitted to the flight controller, it will disrupt the working stability of the electronic components inside the flight controller, leading to a decrease in control accuracy, deviation in the drone's attitude control, and in severe cases, even loss of flight control.
[0005] In view of this, we propose a shock-absorbing fixing structure for UAV flight controllers. Summary of the Invention
[0006] To overcome the shortcomings of the prior art and solve at least one of the technical problems mentioned in the background art, this application proposes a shock-absorbing fixing structure for a drone flight controller.
[0007] This application provides a shock-absorbing and fixing structure for a drone flight controller, comprising: Flight controller; A controller mounting base is positioned directly above the flight controller. A base is located at the bottom of the controller mounting base, and multiple support columns are fixed to the top of the base. The base and the controller mounting base are connected by multiple screws, and the screws are threaded to the support columns. The primary shock absorption mechanism is located at the connection between the flight controller and the controller mount, and is used to flexibly connect the flight controller and the controller mount.
[0008] As an optional solution to the technical solution of this application, the primary shock absorption mechanism includes multiple first mounting slots opened on the controller mounting base, and multiple second mounting slots opened in the middle of the flight controller. Rubber columns are provided in the middle of the first and second mounting slots, and shock-absorbing balls are fixedly connected to both ends of the rubber columns. Both shock-absorbing balls are plugged into the first and second mounting slots.
[0009] As an optional solution to the technical solution of this application, the flight controller is provided with a secondary shock absorption mechanism on the top. The secondary shock absorption mechanism includes a shock absorption groove opened in the middle of the controller mounting base. A shock absorption sponge is fixed to the top of the flight controller. An IMU element is installed on the top of the shock absorption sponge. The IMU element is electrically connected to the flight controller.
[0010] As an optional solution to the technical solution of this application, the top of the controller mounting base is fixed with two connecting cloths, the ends of the connecting cloths are fixed with hook and loop fasteners, and the bottom of the flight controller is fixed with two hook and loop fasteners, the hook and loop fasteners being adhesively joined.
[0011] As an optional solution to the technical solution in this application, the top of the controller mounting base has two cable grooves for connecting and routing the flight controller cables.
[0012] As an optional solution to the technical solution in this application, the top of the controller mounting base is provided with multiple battery strap slots.
[0013] One or more technical solutions provided in the embodiments of this application have at least the following technical effects or advantages: (1) This application uses a primary damping mechanism, which solves the problem of excessive vibration of the fuselage caused by the interference of the UAV’s own power system and flight aerodynamics. Through the flexible connection design of the primary damping mechanism, the vibration transmission path is effectively blocked, and the vibration is prevented from being directly transmitted to the flight controller, thus ensuring the control accuracy of the flight controller, improving the stability of the UAV’s attitude control, and extending the service life of the flight controller.
[0014] (2) This application solves the problem that the IMU element is sensitive to vibration and is easily affected by residual vibration. Through the buffering effect of the shock-absorbing sponge, the small vibrations that still exist after the first-level shock absorption are further filtered out, avoiding the data acquisition deviation of the IMU element due to vibration, ensuring the measurement accuracy of the IMU element, and thus ensuring the control response accuracy of the flight controller, providing a key guarantee for the stable flight of the UAV. Attached Figure Description
[0015] Figure 1 This is a schematic diagram of the overall structure of a shock-absorbing fixing structure for a drone flight controller disclosed in a preferred embodiment of this application; Figure 2 for Figure 1 Enlarged view of point A; Figure 3 This is a schematic diagram of the planar structure of a shock-absorbing fixing structure for a drone flight controller disclosed in a preferred embodiment of this application; Figure 4This is a schematic diagram of the connecting fabric structure of the shock-absorbing fixing structure for a drone flight controller disclosed in a preferred embodiment of this application; Figure 5 This is a schematic diagram of a flight controller structure for a shock-absorbing fixing structure for a drone flight controller, as disclosed in a preferred embodiment of this application.
[0016] The following are the labels in the diagram: 1. Flight controller; 2. Controller mount; 21. Base; 22. Screw; 23. Support column; 24. Cable tray; 25. Battery strap tray; 3. Primary shock absorption mechanism; 31. First mounting slot; 32. Second mounting slot; 33. Rubber post; 34. Shock-absorbing ball; 4. Secondary shock absorption mechanism; 41. Shock-absorbing groove; 42. Shock-absorbing foam; 43. IMU element; 5. Connecting cloth; 51. Velcro loop side; 52. Velcro hook side. Detailed Implementation
[0017] The present application will be further described in detail below with reference to the accompanying drawings.
[0018] Reference Figures 1-5This application discloses a shock-absorbing and fixing structure for a drone flight controller, comprising a flight controller 1, a controller mounting base 2, and a primary shock-absorbing mechanism 3, which is positioned directly above the flight controller 1. The controller mounting base 2 has a base 21 at its bottom, located at the bottom of the flight controller 1. Multiple support columns 23 are fixedly connected to the top of the base 21. The base 21 and the controller mounting base 2 are fixedly connected by multiple screws 22, and the screws 22 are threaded to the support columns 23. The support columns 23 are located at the connection between the flight controller 1 and the controller mounting base 2, and are used to flexibly connect the flight controller 1 and the controller mounting base 2. The primary shock absorption mechanism 3 includes multiple first mounting slots 31 formed on the controller mounting base 2, and multiple second mounting slots 32 formed in the middle of the flight controller 1. Rubber posts 33 are provided in the middle of the first mounting slots 31 and second mounting slots 32, and shock-absorbing balls 34 are fixedly connected to both ends of the rubber posts 33. Both shock-absorbing balls 34 are inserted into the first mounting slots 31 and second mounting slots 32. First, the base 21 is placed at the bottom of the flight controller 1, and the base 21 is fixedly connected to the controller mounting base 2 using multiple screws 22. The screws 22 are threadedly connected to multiple support pillars 23 fixed to the top of the base 21, thus achieving... After the controller mounting base 2 is securely assembled with the base 21, a primary shock absorption mechanism 3 is installed between the multiple first mounting slots 31 of the controller mounting base 2 and the multiple second mounting slots 32 in the middle of the flight controller 1. Specifically, rubber posts 33 with shock-absorbing balls 34 fixedly connected to both ends are placed in the middle of the first mounting slots 31 and the second mounting slots 32, so that the two shock-absorbing balls 34 are respectively inserted into the first mounting slots 31 and the second mounting slots 32. Through the four-point suspension structure formed by the four sets of rubber posts 33 and shock-absorbing balls 34, a non-rigid flexible connection is achieved between the flight controller 1 and the controller mounting base 2. When the UAV fuselage vibrates... During operation, vibrations are transmitted through the frame to the controller mounting base 2. At this time, the rubber column 33 and the shock-absorbing ball 34 undergo elastic deformation, converting vibration energy into heat energy for consumption. Simultaneously, the flight controller 1 is allowed to perform low-frequency movements to synchronize with the fuselage. This step solves the problem of excessive fuselage vibration caused by interference from the UAV's own power system and flight aerodynamics. Through the flexible connection design of the primary shock-absorbing mechanism 3, the vibration transmission path is effectively blocked, preventing vibration from being directly transmitted to the flight controller 1. This ensures the control accuracy of the flight controller 1, improves the stability of the UAV's attitude control, and extends the service life of the flight controller 1.
[0019] Reference Figures 1-5The flight controller 1 is equipped with a secondary shock absorption mechanism 4 on its top. The secondary shock absorption mechanism 4 includes a shock absorption groove 41 opened in the middle of the controller mounting base 2. A shock absorption foam 42 is fixed to the top of the flight controller 1. An IMU element 43 is installed on the top of the shock absorption foam 42. The IMU element 43 is electrically connected to the flight controller 1. The secondary shock absorption mechanism 4 is installed on the top of the flight controller 1. The shock absorption groove 41 opened in the middle of the controller mounting base 2 provides installation and movement space for the IMU element 43. The shock absorption foam 42 is fixed to the top of the flight controller 1. Then the IMU element 43 is installed on the top of the shock absorption foam 42, and the IMU element 43 is electrically connected to the flight controller 1. When the flight controller 1 is subjected to vibration, the residual vibration, after being attenuated by the primary damping mechanism 3, is transmitted to the top of the flight controller 1. The damping sponge 42 further absorbs the vibration energy through its own elastic deformation, forming a secondary damping protection for the IMU element 43. This step solves the problem that the IMU element 43 is sensitive to vibration and easily interfered with by residual vibration. Through the buffering effect of the damping sponge 42, the small vibrations that still exist after the primary damping are further filtered out, avoiding data acquisition deviation of the IMU element 43 due to vibration, ensuring the measurement accuracy of the IMU element 43, and thus ensuring the control response accuracy of the flight controller 1, providing a key guarantee for the stable flight of the UAV.
[0020] Reference Figures 1-5 Two connecting fabrics 5 are fixed to the top of the controller mounting base 2, and hook and loop fasteners 51 are fixed to the ends of the connecting fabrics 5. Two hook and loop fasteners 52 are fixed to the bottom of the flight controller 1. The hook and loop fasteners 52 are bonded together. After the flight controller 1 is installed in place by the first-stage shock absorption mechanism 3, the connecting fabrics 5 are flipped downwards so that the hook and loop fasteners 51 bond with the hook and loop fasteners 52 at the bottom of the flight controller 1. Through the binding effect of the two connecting fabrics 5, a two-way fixation is formed from the top and bottom of the flight controller 1. This step solves the problem that the flight controller 1 may shake or shift when the UAV moves violently or encounters strong airflow when connected only by the first-stage shock absorption mechanism 3. The bonding operation of the hook and loop fasteners 51 and hook and loop fasteners 52 is simple and can quickly reinforce the flight controller 1.
[0021] Reference Figures 1-5Two cable trays 24 are provided on the top of the controller mounting base 2 for connecting and routing the flight controller 1. With these cable trays 24, various electrical wires required for the operation of the flight controller 1 can be routed within them according to a preset path, preventing haphazard tangling or exposure of the wires. This step solves the problems of messy, easily tangled, and potentially interfering electrical wiring of the flight controller 1 with other structures. Reference Figures 1-5 The top of the controller mounting base 2 has multiple battery strap slots 25. When it is necessary to fix the flight battery, the external battery straps are passed through the battery strap slots 25 and wrapped around the flight battery and the controller mounting base 2 for binding. This step solves the problems of inconvenient flight battery fixing operation and easy loosening after fixing. The battery strap slots 25 provide a stable passage for the battery straps, making the force on the straps more even and improving the firmness of the flight battery fixing.
[0022] In summary, when using the shock-absorbing fixing structure for the UAV flight controller disclosed in this application embodiment, firstly, the base 21 is placed at the bottom of the flight controller 1, and the base 21 is fixedly connected to the controller mounting base 2 by multiple screws 22. The screws 22 and multiple support pillars 23 fixed to the top of the base 21 form a threaded connection, achieving a stable assembly between the controller mounting base 2 and the base 21. Subsequently, a primary shock-absorbing mechanism 3 is installed between the multiple first mounting slots 31 of the controller mounting base 2 and the multiple second mounting slots 32 in the middle of the flight controller 1. Specifically, rubber pillars 33 with shock-absorbing balls 34 fixedly connected to both ends are placed in the middle of the first mounting slots 31 and the second mounting slots 32, so that the two shock-absorbing balls 34 respectively engage with the first mounting slots 31 and the second mounting slots 32. A four-point suspension structure consisting of four sets of rubber pillars 33 and shock-absorbing balls 34 is used to achieve a non-rigid flexible connection between the flight controller 1 and the controller mounting base 2. When the UAV fuselage vibrates, the vibration is transmitted to the controller mounting base 2 through the frame. At this time, the rubber pillars 33 and shock-absorbing balls 34 will undergo elastic deformation, converting the vibration energy into heat energy for consumption. At the same time, the flight controller 1 is allowed to perform low-frequency movements to synchronize with the fuselage. A secondary shock absorption mechanism 4 is installed on the top of the flight controller 1. The shock absorption groove 41 opened in the middle of the controller mounting base 2 provides installation and movement space for the IMU element 43. The shock absorption foam 42 is fixed to the top of the flight controller 1, and then the IMU element 43 is installed on the top of the shock absorption foam 42, and the electrical connection between the IMU element 43 and the flight controller 1 is achieved. When the flight controller 1 is subjected to vibration, the residual vibration, after being attenuated by the primary damping mechanism 3, is transmitted to the top of the flight controller 1. The damping sponge 42 further absorbs the vibration energy through its own elastic deformation, forming a secondary damping protection for the IMU element 43. Two connecting cloths 5 are fixed to the top of the controller mounting base 2, and hook and loop fasteners 51 are provided at the ends of the connecting cloths 5. At the same time, two hook and loop fasteners 52 are fixed to the bottom of the flight controller 1. After the flight controller 1 is installed in place by the primary damping mechanism 3, the connecting cloths 5 are flipped downwards so that the hook and loop fasteners 51 are connected to the flight controller 1. The bottom Velcro hook 52 is attached and secured by the binding effect of two connecting cloths 5, forming a two-way fixation from the top and bottom of the flight controller 1. Two wire grooves 24 are opened on the top of the controller mounting base 2. Various electrical wires required for the operation of the flight controller 1 can be embedded in the wire grooves 24 according to the preset path for wiring arrangement, avoiding the wires from being randomly tangled or exposed. Multiple battery strap slots 25 are opened on the top of the controller mounting base 2. When it is necessary to fix the flight battery, the external battery straps are passed through the battery strap slots 25 and wrapped around the flight battery and the controller mounting base 2 for binding.
Claims
1. A shock-absorbing and fixing structure for a drone flight controller, characterized in that, Include: Flight controller (1); The controller mounting base (2) is located directly above the flight controller (1). The bottom of the controller mounting base (2) is provided with a base (21). The base (21) is located at the bottom of the flight controller (1). Multiple support columns (23) are fixedly connected to the top of the base (21). The base (21) and the controller mounting base (2) are fixedly connected by multiple screws (22). The screws (22) and the support columns (23) are threadedly connected. The primary shock absorption mechanism (3) is set at the connection between the flight controller (1) and the controller mounting base (2) to flexibly connect the flight controller (1) and the controller mounting base (2).
2. The shock-absorbing and fixing structure for a UAV flight controller according to claim 1, characterized in that: The primary shock absorption mechanism (3) includes multiple first mounting slots (31) on the controller mounting base (2), and multiple second mounting slots (32) in the middle of the flight controller (1). Rubber posts (33) are provided in the middle of the first mounting slots (31) and the second mounting slots (32). Shock-absorbing balls (34) are fixedly connected to both ends of the rubber posts (33). Both shock-absorbing balls (34) are plugged into the first mounting slots (31) and the second mounting slots (32).
3. The shock-absorbing and fixing structure for a UAV flight controller according to claim 1, characterized in that: The flight controller (1) is provided with a secondary shock absorption mechanism (4) on the top. The secondary shock absorption mechanism (4) includes a shock absorption groove (41) opened in the middle of the controller mounting base (2). A shock absorption sponge (42) is fixed to the top of the flight controller (1). An IMU element (43) is installed on the top of the shock absorption sponge (42). The IMU element (43) is electrically connected to the flight controller (1).
4. The shock-absorbing and fixing structure for a UAV flight controller according to claim 1, characterized in that: The top of the controller mounting base (2) is fixed with two connecting cloths (5), and the ends of the connecting cloths (5) are fixed with hook and loop fasteners (51). The bottom of the flight controller (1) is fixed with two hook and loop fasteners (52), and the hook and loop fasteners (52) are bonded together.
5. The shock-absorbing and fixing structure for a UAV flight controller according to claim 1, characterized in that: The top of the controller mounting base (2) has two wire grooves (24) for connecting the flight controller (1) to the wiring.
6. The shock-absorbing fixing structure for a UAV flight controller according to claim 1, characterized in that: The top of the controller mounting base (2) has multiple battery strap slots (25).