Unmanned aerial vehicle gyroscope damping structure

Abstract

The utility model discloses an unmanned aerial vehicle gyroscope damping structure relates to unmanned aerial vehicle flight control field. This unmanned aerial vehicle gyroscope damping structure, including the damping structure, the bottom of damping structure is provided with unmanned aerial vehicle flight control board, the damping structure is composed by silica gel support and tray, the tray is installed in the top of silica gel support, the outside of silica gel support is equipped with a plurality of damping spring, just the top of tray is equipped with inertia measurement unit, inertia measurement unit and unmanned aerial vehicle flight control board electric connection. This unmanned aerial vehicle gyroscope damping structure, through the damping spring of silica gel support's support leg outside sleeve setting, combine silica gel support's energy attenuation effect with the elastic force buffer of damping spring, effectively filter the high frequency waveform of propeller wind force and fuselage vibration, avoid inertia measurement unit and appear misjudgment because of excessive vibration, the stability of remarkable improvement unmanned aerial vehicle take -off, landing and flight process, guarantee inertial navigation precision.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) flight control technology, specifically to a UAV gyroscope vibration reduction structure. Background Technology

[0002] In the flight control system of unmanned aerial vehicles (UAVs), the inertial measurement unit (IMU) is a core sensing component that needs to collect acceleration, angular velocity and orientation data of the UAV in three-dimensional space in real time. Through electrical connection with the UAV flight control board, it provides key data support for UAV attitude correction, motion trajectory calculation and inertial navigation.

[0003] Currently, existing technologies for inertial measurement units (IMUs) on UAV flight control boards rely solely on silicone brackets for vibration damping. While these brackets can attenuate some energy through elastic deformation, their complex structural design and the relatively low hardness of the silicone, coupled with the need for proper molding, result in weak overall vibration damping and filtering capabilities. Particularly during UAV takeoff and landing, the wind force generated by the propeller rotation and fuselage vibrations can cause excessive deformation of the silicone bracket's support legs due to their fragility. This increases the dynamic range of the IMU, leading to attitude misjudgments and severely impacting the UAV's flight stability and inertial navigation accuracy. Utility Model Content

[0004] To address the shortcomings of existing technologies, this utility model provides a shock absorption structure for a drone gyroscope, solving the problem that existing technologies that rely solely on silicone brackets for shock absorption of the inertial measurement unit suffer from weak shock absorption and filtering due to the fragility of the silicone brackets, which can easily lead to misjudgments by the inertial measurement unit and thus affect the flight stability of the drone.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a shock-absorbing structure for a drone gyroscope, comprising a shock-absorbing structure, a drone flight control board at the bottom of the shock-absorbing structure, the shock-absorbing structure consisting of a silicone bracket and a tray, the tray being mounted on top of the silicone bracket, a plurality of shock-absorbing springs being sleeved on the outer side of the silicone bracket, and an inertial measurement unit being mounted on top of the tray, the inertial measurement unit being electrically connected to the drone flight control board.

[0006] Preferably, the silicone bracket includes a mounting plate and multiple support legs, the tops of the multiple support legs are fixedly connected to the mounting plate, and the bottoms of the support legs are fixedly connected to a fixing block.

[0007] Preferably, the plurality of shock-absorbing springs are respectively sleeved on the outside of the plurality of support legs, and the top of the shock-absorbing springs abuts against the tray and the mounting plate, and the bottom of the shock-absorbing springs abuts against the fixing block.

[0008] Preferably, the mounting plate has multiple through slots, and the bottom of the fixing block is fixedly connected to a threaded post.

[0009] Preferably, the pallet includes a pallet body and a plurality of buckles, the plurality of buckles being fixedly installed on the bottom of the pallet body and respectively engaging in a plurality of slots.

[0010] Preferably, the threaded post extends through the UAV flight control board, and the threaded post is fixedly connected to the UAV flight control board by a nut.

[0011] Preferably, a ribbon cable is provided between the inertial measurement unit and the UAV flight control board, and each end of the ribbon cable is equipped with a connector, and the two connectors are respectively connected to the inertial measurement unit and the UAV flight control board.

[0012] Its beneficial effects are as follows: 1. The gyroscope vibration reduction structure of this UAV effectively filters high-frequency waveforms generated by propeller wind force and fuselage vibration by sleeved with a shock-absorbing spring on the outside of the support leg of the silicone bracket, combined with the energy attenuation effect of the silicone bracket itself and the elastic buffer of the shock-absorbing spring. This avoids misjudgment by the inertial measurement unit due to excessive vibration, significantly improves the stability of the UAV during takeoff, landing and flight, and ensures the accuracy of inertial navigation.

[0013] 2. The gyroscope shock absorption structure of this drone, with its shock absorption springs, can share the pressure borne by the silicone bracket support legs, reduce the deformation loss of the support legs, extend the overall service life of the silicone bracket, and reduce the maintenance and replacement costs of the drone.

[0014] 3. The gyroscope shock absorption structure of this drone features a silicone bracket that can be quickly snapped into place with the tray via the slots in the mounting plate. The threaded post at the bottom of the fixing block can be securely connected to the drone flight control board via a nut. The inertial measurement unit is bonded to the tray with 3M double-sided tape. The overall assembly process is simple and efficient, meeting the needs of mass production. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a schematic diagram of part of the structure of this utility model; Figure 3 This is a schematic diagram of the structure of the silicone support of this utility model; Figure 4 This is a schematic diagram of the structure of the tray and inertial measurement unit of this utility model.

[0017] In the diagram: 1. Shock-absorbing structure; 11. Silicone bracket; 111. Mounting plate; 112. Support leg; 113. Fixing block; 114. Slot; 115. Threaded post; 12. Tray; 121. Tray body; 122. Buckle; 2. UAV flight control board; 3. Inertial measurement unit. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions in the embodiments of this utility model are described clearly and completely. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0019] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0020] This utility model discloses a shock absorption structure for a drone gyroscope, according to the attached... Figure 1 - Appendix Figure 2 As shown, it includes a shock-absorbing structure 1, and a drone flight control board 2 is provided at the bottom of the shock-absorbing structure 1. The shock-absorbing structure 1 is composed of a silicone bracket 11 and a tray 12. The tray 12 is installed on the top of the silicone bracket 11. Multiple shock-absorbing springs 13 are sleeved on the outside of the silicone bracket 11, and an inertial measurement unit 3 is installed on the top of the tray 12. The inertial measurement unit 3 is electrically connected to the drone flight control board 2.

[0021] According to the appendix Figure 2 - Appendix Figure 3 As shown, the silicone bracket 11 further includes a mounting plate 111 and multiple support legs 112. The tops of the multiple support legs 112 are fixedly connected to the mounting plate 111, and the bottoms of the support legs 112 are fixedly connected to a fixing block 113.

[0022] Multiple shock-absorbing springs 13 are respectively sleeved on the outside of multiple support legs 112, and the top of the shock-absorbing springs 13 abuts against the tray 12 and the mounting plate 111, and the bottom of the shock-absorbing springs 13 abuts against the fixing block 113.

[0023] By installing a shock-absorbing spring 13 on the outside of the support leg 112 of the silicone bracket 11, combined with the energy attenuation effect of the silicone bracket 11 itself and the elastic buffer of the shock-absorbing spring 13, the high-frequency waveforms generated by the propeller wind force and the vibration of the fuselage are effectively filtered, avoiding misjudgment by the inertial measurement unit 3 due to excessive vibration, significantly improving the stability of the UAV during takeoff, landing and flight, and ensuring the accuracy of inertial navigation.

[0024] The shock-absorbing spring 13 can share the pressure borne by the support leg 112 of the silicone bracket 11, reduce the deformation loss of the support leg 112, extend the overall service life of the silicone bracket 11, and reduce the maintenance and replacement cost of the drone.

[0025] The mounting plate 111 has multiple through slots 114, and the bottom of the fixing block 113 is fixedly connected to a threaded post 115.

[0026] According to the appendix Figure 3 - Appendix Figure 4 As shown, the pallet 12 further includes a pallet body 121 and a plurality of buckles 122. The plurality of buckles 122 are fixedly installed on the bottom of the pallet body 121 and are respectively engaged in a plurality of slots 114.

[0027] According to the appendix Figure 1 - Appendix Figure 3 As shown, the threaded post 115 is further disposed through the UAV flight control board 2, and the threaded post 115 is fixedly connected to the UAV flight control board 2 by a nut.

[0028] The silicone bracket 11 is quickly snapped into place with the buckle 122 of the tray 12 via the slot 114 of the mounting plate 111. The threaded post 115 at the bottom of the fixing block 113 can be securely connected to the drone flight control board 2 via a nut. The inertial measurement unit 3 is bonded to the tray 12 with 3M double-sided tape. The overall assembly process is simple and efficient, meeting the needs of mass production.

[0029] A ribbon cable 22 is provided between the inertial measurement unit 3 and the UAV flight control board 2. Both ends of the ribbon cable 22 are equipped with connectors 21, and the two connectors 21 are respectively connected to the inertial measurement unit 3 and the UAV flight control board 2.

[0030] First, the inertial measurement unit 3 is attached to the tray body 121 of the tray 12 using its own strong 3M double-sided adhesive, ensuring the correct installation direction. Then, the buckles 122 at the bottom of the tray 12 are inserted into the corresponding slots 114 of the mounting plate 111 of the silicone bracket 11 to fix the tray 12 to the silicone bracket 11. Next, the shock-absorbing springs 13 are respectively sleeved on the outside of the support legs 112 of the silicone bracket 11, so that the top of the shock-absorbing springs 13 abuts against the tray body 121 and the mounting plate 111, and the bottom abuts against the fixing block 113 at the bottom of the support leg 112. Finally, the threaded post 115 at the bottom of the fixing block 113 passes through the UAV flight control board 2 and is tightened with a nut. At the same time, the connectors 21 at both ends of the ribbon cable 22 are used to connect the inertial measurement unit 3 and the UAV flight control board 2, respectively, to complete the assembly of the overall shock-absorbing structure and flight control system.

[0031] When the drone vibrates during operation, the vibration energy is first transmitted to the drone flight control board 2, and then through the threaded post 115 to the fixing block 113 and support leg 112 of the silicone bracket 11. At this time, the silicone bracket 11 initially attenuates some of the vibration energy through its own elastic deformation; simultaneously, the shock-absorbing spring 13 on the outside of the support leg 112 is axially compressed by the vibration pressure, according to Hooke's Law... ,in This refers to the spring stiffness coefficient of the damping spring. To compensate for the compression, the damping spring 13 generates a reverse elastic force, further buffering the vibration energy and preventing the vibration from being directly transmitted to the inertial measurement unit 3 on the tray 12. The dual damping effect can effectively filter high-frequency vibrations, ensuring that the inertial measurement unit 3 stably collects acceleration and angular velocity data, and transmits it to the UAV flight control board 2 in real time through the ribbon cable 22, providing accurate data support for UAV attitude correction and navigation, and ensuring flight stability.

[0032] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0033] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claims. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A shock-absorbing structure for a UAV gyroscope, comprising a shock-absorbing structure (1), wherein a UAV flight control board (2) is disposed at the bottom of the shock-absorbing structure (1), characterized in that, The shock-absorbing structure (1) consists of a silicone bracket (11) and a tray (12). The tray (12) is installed on the top of the silicone bracket (11). Multiple shock-absorbing springs (13) are sleeved on the outside of the silicone bracket (11). An inertial measurement unit (3) is installed on the top of the tray (12). The inertial measurement unit (3) is electrically connected to the UAV flight control board (2).

2. The vibration damping structure for a UAV gyroscope according to claim 1, characterized in that, The silicone bracket (11) includes a mounting plate (111) and multiple support legs (112). The tops of the multiple support legs (112) are fixedly connected to the mounting plate (111), and the bottoms of the support legs (112) are fixedly connected to a fixing block (113).

3. The vibration damping structure for a UAV gyroscope according to claim 2, characterized in that, Multiple shock-absorbing springs (13) are respectively sleeved on the outside of multiple support legs (112), and the top of the shock-absorbing springs (13) abuts against the tray (12) and the mounting plate (111), and the bottom of the shock-absorbing springs (13) abuts against the fixing block (113).

4. The vibration damping structure for a UAV gyroscope according to claim 2, characterized in that, The mounting plate (111) has multiple through slots (114), and the bottom of the fixing block (113) is fixedly connected with a threaded post (115).

5. The vibration damping structure for a UAV gyroscope according to claim 4, characterized in that, The tray (12) includes a tray body (121) and multiple buckles (122). The multiple buckles (122) are fixedly installed on the bottom of the tray body (121), and the multiple buckles (122) are respectively engaged in multiple slots (114).

6. The vibration damping structure for a UAV gyroscope according to claim 4, characterized in that, The threaded post (115) is installed through the UAV flight control board (2), and the threaded post (115) is fixedly connected to the UAV flight control board (2) by a nut.

7. The vibration damping structure for a UAV gyroscope according to claim 1, characterized in that, A ribbon cable (22) is provided between the inertial measurement unit (3) and the UAV flight control board (2). Both ends of the ribbon cable (22) are equipped with connectors (21), and the two connectors (21) are respectively connected to the inertial measurement unit (3) and the UAV flight control board (2).

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