CN211401222U - Flight control gyroscope shock-absorbing structure - Google Patents
Flight control gyroscope shock-absorbing structure Download PDFInfo
- Publication number
- CN211401222U CN211401222U CN202020020719.2U CN202020020719U CN211401222U CN 211401222 U CN211401222 U CN 211401222U CN 202020020719 U CN202020020719 U CN 202020020719U CN 211401222 U CN211401222 U CN 211401222U
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- mounting
- flight control
- damping
- control gyroscope
- shock
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Abstract
The utility model provides a fly accuse gyroscope shock-absorbing structure, it includes shock attenuation part, mount pad, installing support and flexible line way board to fly accuse gyroscope shock-absorbing structure, be equipped with the damping ball on the shock attenuation part, the shock attenuation part upper end runs through the mount pad and with mount pad fixed connection, the damping part lower extreme runs through the installing support and with installing support fixed connection, the mount pad with centre gripping is still in the shock attenuation ball between the installing support, be equipped with the mounting groove on the mount pad, the one end fixed mounting of flexible line way board is in the mounting groove, it flies accuse gyroscope and fuselage and reaches the shock attenuation purpose to connect through the damping part, and the shock attenuation effect of such shock attenuation scheme is better.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to a flight control gyroscope shock-absorbing structure.
Background
Appear numerous unmanned aerial vehicle products in the market today, current unmanned aerial vehicle product often uses sponge structure to carry out the shock attenuation to flying control gyroscope in flying control gyroscope shock attenuation design, and the sponge is soft relatively, appears the mistake easily at the in-process that carries out the assembly, also appears the condition of bad assembly easily, and the sponge of having a specified duration can appear softening moreover to lead to flying control gyroscope crooked, it just can not keep relatively steady with the fuselage to fly control gyroscope like this.
SUMMERY OF THE UTILITY MODEL
In order to solve the problem, the utility model provides a flight control gyroscope shock-absorbing structure.
The utility model discloses a following technical scheme realizes:
the utility model provides a fly accuse gyroscope shock-absorbing structure, it includes shock attenuation part, mount pad, installing support and flexible line way board to fly accuse gyroscope shock-absorbing structure, be equipped with the damping ball on the shock attenuation part, the shock attenuation part upper end runs through the mount pad and with mount pad fixed connection, the damping part lower extreme runs through the installing support and with installing support fixed connection, the mount pad with centre gripping is in between the installing support the damping ball, be equipped with the mounting groove on the mount pad, the one end fixed mounting of flexible line way board is in the mounting groove.
Further, flight control gyroscope shock-absorbing structure still includes the silica gel board, the silica gel board is acceptd in the mounting groove, silica gel board one side with the flexible line way board contact, silica gel board another side with mount pad fixed connection.
Furthermore, the mounting base is further provided with a first connecting hole, and the upper end of the damping component penetrates through the first connecting hole.
Furthermore, a second connecting hole is formed in the mounting support, and the lower end of the damping part penetrates through the second connecting hole.
Furthermore, four accommodating grooves are further formed in the mounting support, and one second connecting hole is formed in each accommodating groove.
Furthermore, the shock absorption structure of the flight control gyroscope further comprises a protective cover, and the protective cover is fixedly connected with the mounting seat.
Furthermore, the mounting seat is further provided with a fixing column, the protective cover is provided with a fixing hole, and the flight control gyroscope damping structure further comprises a fixing screw, wherein the fixing screw penetrates through the fixing hole and is contained in the fixing column, so that the protective cover is fixedly connected with the mounting seat.
Further, a notch is formed in one side of the mounting groove, and when one end of the flexible circuit board is mounted in the mounting groove, the other end of the flexible circuit board can extend to the periphery of the mounting seat from the notch.
The utility model has the advantages that:
the utility model provides a flight control gyroscope shock-absorbing structure connects together mount pad and installing support through the shock-absorbing part, and mount pad and installing support bracket accompany a rubber damper ball, and the material of rubber damper ball is more elastic for the sponge, and the rubber damper ball can not soften yet after a long time, and the durability is high, convenient assembling; still installed a rubber slab in the mounting groove, the rubber slab can further play the shock attenuation effect to the gyroscope, has dual shock attenuation effect with the shock attenuation part together, protects the gyroscope better for the gyroscope can keep normal operating condition constantly.
Drawings
Fig. 1 is an exploded view of a damping structure of a flight control gyroscope according to the present invention;
fig. 2 is the structural schematic diagram of the damping structure of the flight control gyroscope of the present invention.
Detailed Description
In order to more clearly and completely explain the technical scheme of the present invention, the present invention is further explained with reference to the attached drawings.
Please refer to fig. 1 and fig. 2, the utility model provides a fly and control gyroscope shock-absorbing structure, fly and control gyroscope shock-absorbing structure includes shock attenuation part 20, mount pad 15, installing support 22 and flexible line way board 13, be equipped with damping ball 21 on the shock attenuation part 20, the shock attenuation part 20 upper end run through mount pad 15 and with mount pad 15 fixed connection, the shock attenuation part 20 lower extreme run through the installing support 22 and with installing support 22 fixed connection, mount pad 15 with the centre gripping is in damping ball 21 between the installing support 22, be equipped with mounting groove 18 on the mount pad 15, the one end fixed mounting of flexible line way board 13 is in mounting groove 18.
In the present embodiment, the damping balls 21 are made of rubber material, four damping members 20 are provided in the damping structure of the flight control gyroscope, one damping ball 21 is provided on each damping member 20, the mounting base 15 is fixedly connected to the upper end of the damping member 20, the mounting bracket 22 is fixedly connected to the lower end of the damping member 20, and the damping balls 21 are sandwiched between the mounting base 15 and the mounting bracket 22. The portion of the flexible circuit board 13 installed in the installation groove 18 is fixedly installed with a flight control gyroscope, and the flight control gyroscope is electrically connected with the flexible circuit board 13, that is, the flight control gyroscope is installed in the installation groove 18.
Further, the shock absorption structure of the flight control gyroscope further comprises a silica gel plate 14, the silica gel plate 14 is accommodated in the mounting groove 18, one surface of the silica gel plate 14 is in contact with the flexible circuit board 13, and the other surface of the silica gel plate 14 is fixedly connected with the mounting seat 15.
In this embodiment, when assembling the damping structure of the flight control gyroscope, the silicone plate 14 is first fixedly mounted in the mounting groove 18, and then the flexible circuit board 13 is placed above the silicone plate 14, and the silicone plate 14 can play a role in damping and protecting the flight control gyroscope mounted on the head-type circuit board.
Further, a first connection hole 17 is further formed in the mounting seat 15, and an upper end of the shock absorbing member 20 penetrates through the first connection hole 17. The mounting bracket 22 is provided with a second connecting hole 23, and the lower end of the shock absorption part 20 penetrates through the second connecting hole 23. The mounting bracket 22 is further provided with four receiving grooves 24, and each receiving groove 24 is provided with one second connecting hole 23.
In the present embodiment, there are four receiving grooves 24 in the mounting bracket 22, one second connecting hole 23 is provided in each receiving groove 24, and the receiving grooves 24 are formed by two crossing partition plates.
Further, the shock absorption structure of the flight control gyroscope further comprises a protective cover 11, and the protective cover 11 is fixedly connected with the mounting base 15. The mounting seat 15 is further provided with fixing columns 16, the protective cover 11 is provided with fixing holes 12, the flight control gyroscope shock absorption structure further comprises fixing screws 10, and the fixing screws 10 penetrate through the fixing holes 12 and are contained in the fixing columns 16, so that the protective cover 11 is fixedly connected with the mounting seat 15. A notch 19 is formed in one side of the mounting groove 18, and when one end of the flexible printed circuit board 13 is mounted in the mounting groove 18, the other end of the flexible printed circuit board 13 can extend from the notch 19 to the periphery of the mounting seat 15.
In this embodiment, the protective cover 11 completely covers one end of the flexible printed circuit 13 in the mounting groove 18, and the protective cover 11 is fixedly connected to the mounting seat 15 by the fixing screw 10.
Of course, the present invention can also have other various embodiments, and based on the embodiments, those skilled in the art can obtain other embodiments without any creative work, and all of them belong to the protection scope of the present invention.
Claims (8)
1. The damping structure of the flight control gyroscope is characterized by comprising a damping component, a mounting seat, a mounting support and a flexible circuit board, wherein a damping ball is arranged on the damping component, the upper end of the damping component penetrates through the mounting seat and is fixedly connected with the mounting seat, the lower end of the damping component penetrates through the mounting support and is fixedly connected with the mounting support, the damping ball is clamped between the mounting seat and the mounting support, a mounting groove is formed in the mounting seat, and one end of the flexible circuit board is fixedly mounted in the mounting groove.
2. The flight control gyroscope shock-absorbing structure according to claim 1, further comprising a silicone plate, wherein the silicone plate is accommodated in the mounting groove, one surface of the silicone plate is in contact with the flexible circuit board, and the other surface of the silicone plate is fixedly connected with the mounting seat.
3. The structure of claim 1, wherein the mounting base further includes a first connecting hole, and an upper end of the damping member extends through the first connecting hole.
4. The flight control gyroscope shock absorbing structure of claim 1, wherein the mounting bracket is provided with a second connecting hole, and a lower end of the shock absorbing component penetrates through the second connecting hole.
5. The flight control gyroscope shock absorption structure according to claim 4, wherein the mounting bracket is further provided with four receiving grooves, and each receiving groove is provided with one second connecting hole.
6. The flight control gyroscope shock absorbing structure of claim 1, further comprising a protective cover fixedly connected with the mount.
7. The flight control gyroscope shock absorption structure according to claim 6, wherein the mounting base is further provided with a fixing post, the protection cover is provided with a fixing hole, and the flight control gyroscope shock absorption structure further comprises a fixing screw, the fixing screw penetrates through the fixing hole and is accommodated in the fixing post, so that the protection cover is fixedly connected with the mounting base.
8. The flight control gyroscope shock absorbing structure according to claim 1, wherein one side of the mounting groove is provided with a notch, and when one end of the flexible circuit board is mounted in the mounting groove, the other end of the flexible circuit board can extend from the notch to the periphery of the mounting seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020020719.2U CN211401222U (en) | 2020-01-03 | 2020-01-03 | Flight control gyroscope shock-absorbing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020020719.2U CN211401222U (en) | 2020-01-03 | 2020-01-03 | Flight control gyroscope shock-absorbing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211401222U true CN211401222U (en) | 2020-09-01 |
Family
ID=72216784
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020020719.2U Active CN211401222U (en) | 2020-01-03 | 2020-01-03 | Flight control gyroscope shock-absorbing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211401222U (en) |
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2020
- 2020-01-03 CN CN202020020719.2U patent/CN211401222U/en active Active
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