CN212125507U - Shock attenuation formula unmanned aerial vehicle stabilizer blade mechanism that rises and falls - Google Patents
Shock attenuation formula unmanned aerial vehicle stabilizer blade mechanism that rises and falls Download PDFInfo
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- CN212125507U CN212125507U CN202020897990.4U CN202020897990U CN212125507U CN 212125507 U CN212125507 U CN 212125507U CN 202020897990 U CN202020897990 U CN 202020897990U CN 212125507 U CN212125507 U CN 212125507U
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Abstract
The utility model discloses a shock-absorbing unmanned aerial vehicle landing leg mechanism, which comprises a mounting seat fixedly connected with an unmanned aerial vehicle main body, wherein a micro motor is fixedly arranged inside the mounting seat, a mounting sleeve is fixedly arranged at the bottom of the mounting seat, a driving shaft of the micro motor is connected with the upper end of a vertically arranged screw rod, the screw rod is coaxially arranged with the mounting sleeve, and the lower end of the screw rod is rotationally connected with the bottom of the mounting sleeve; the screw rod is provided with a nut sleeve in threaded connection with the screw rod, and the outer peripheral wall of the nut sleeve is in sliding fit with the inner peripheral wall of the mounting sleeve. The utility model discloses when unmanned aerial vehicle landed, drive through micro motor the screw rod is rotatory, and nut cover can be followed the screw rod and made linear motion, and nut cover upward movement in-process struts three stabilizer blade pole outward through three connecting rod to increased the landing area of unmanned aerial vehicle stabilizer blade mechanism, reduced the impact force that the stabilizer blade received, and formed three point support structure, had good stability.
Description
Technical Field
The utility model relates to a field especially relates to a shock attenuation formula unmanned aerial vehicle stabilizer blade mechanism that rises and falls.
Background
To rotor unmanned aerial vehicle, the foot rest is than indispensable part, and it plays the supporting role to unmanned aerial vehicle when unmanned aerial vehicle descends. Present unmanned aerial vehicle's stabilizer blade generally is single-point's shaft-like structure, can receive great vibrations when unmanned aerial vehicle descends and strike, and the shaft-like stabilizer blade structure of single-point is more poor when receiving great impact stability, easily produces the deformation under the effect that the rigidity is strikeed moreover. In order to improve above-mentioned defect, some nobody will be through the cross-sectional area of increase stabilizer blade bottom, thereby increase the area of contact of stabilizer blade and ground promptly and reduce the impact that the stabilizer blade received, but the bottom stabilizer blade of large tracts of land can influence unmanned aerial vehicle's shooting scope, influences unmanned aerial vehicle's normal use.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a shock attenuation formula unmanned aerial vehicle stabilizer blade mechanism that rises and falls, the problem of solution.
In order to solve the technical problem, the utility model adopts the following technical scheme:
the utility model relates to a shock attenuation formula unmanned aerial vehicle stabilizer blade mechanism that rises and falls, including the mount pad that is used for with unmanned aerial vehicle main part fixed connection, the inside of mount pad is fixed and is provided with the micro motor, the bottom of mount pad is fixed and is provided with the installation cover, the drive shaft of micro motor is connected with the upper end of the screw rod of vertical setting, the screw rod with the coaxial setting of installation cover and its lower extreme with the bottom of installation cover is rotated and is connected; the screw rod is provided with a nut sleeve in threaded connection with the screw rod, and the outer peripheral wall of the nut sleeve is in sliding fit with the inner peripheral wall of the mounting sleeve.
The upper part of the mounting sleeve is uniformly provided with three first connecting lugs along the circumferential direction, and each first connecting lug is hinged with one end of one supporting leg rod; the middle part of the mounting sleeve is evenly provided with three guide grooves at positions respectively corresponding to the three first connecting lugs.
The outer side of the nut sleeve is uniformly provided with three second connecting lugs which correspond to the three guide grooves respectively and are in sliding fit with the guide grooves, each second connecting lug is hinged with one end of one connecting rod respectively, and the other end of each connecting rod is hinged with a third connecting lug arranged on the corresponding support rod.
Furthermore, the other end of each support leg rod is provided with a support point ball.
Still further, the other end of each support foot rod is provided with a buffer slot, a slide rod is arranged in the buffer slot in a sliding mode, a buffer spring is arranged between the slide rod and the inner end of the buffer slot, and the support foot ball is arranged at one end, located outside the buffer slot, of the slide rod.
Compared with the prior art, the utility model discloses a beneficial technological effect:
the utility model discloses when unmanned aerial vehicle landed, drive through micro motor the screw rod is rotatory, nut cover can be followed the screw rod and made linear motion, and nut cover upward movement in-process struts three stabilizer blade pole outward through three connecting rod to increased the landing area of unmanned aerial vehicle stabilizer blade mechanism, reduced the impact force that the stabilizer blade received, and formed three point support structure, had good stability. After unmanned aerial vehicle normally takes off, micro motor drives the screw rod antiport, and nut cover downstream is three in the time the leg pole draws in, can not lead to the fact like this to shelter from unmanned aerial vehicle's shooting sight and scope, can not influence unmanned aerial vehicle's normal function of making a video recording.
Drawings
The present invention will be further explained with reference to the following description of the drawings.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an enlarged schematic view of the structure at A in FIG. 1;
description of reference numerals: 1. a mounting seat; 2. a micro motor; 3. installing a sleeve; 4. a screw; 5. a nut sleeve; 6. a first connecting lug; 7. a leg bar; 8. a guide groove; 9. a second engaging lug; 10. a connecting rod; 11. a third link lug; 12. a fulcrum ball; 13. a buffer tank; 14. a slide bar; 15. a buffer spring.
Detailed Description
As shown in fig. 1-2, a shock attenuation formula unmanned aerial vehicle landing leg mechanism, including be used for with unmanned aerial vehicle main part fixed connection's mount pad 1, the inside fixed mounting of mount pad 1 has micro motor 2, the bottom of mount pad 1 is fixed and is provided with installation cover 3. The drive shaft of micro motor 2 is connected with the upper end of the screw rod 4 of vertical setting, screw rod 4 with the coaxial setting of installation cover 3 and its lower extreme with the bottom of installation cover 3 is rotated and is connected. And the screw rod 4 is provided with a nut sleeve 5 in threaded connection with the screw rod, and the peripheral wall of the nut sleeve 5 is in sliding fit with the inner peripheral wall of the mounting sleeve 3.
The upper portion of the mounting sleeve 3 is uniformly and fixedly provided with three first connecting lugs 6 along the circumferential direction, and each first connecting lug 6 is hinged to one end of one supporting leg rod 7. A fulcrum ball 12 is mounted at the other end of each of the fulcrum bars 7, specifically, a buffer slot 13 is formed at the other end of each of the fulcrum bars 7, a slide bar 14 is slidably mounted in the buffer slot 13, a buffer spring 15 is disposed between the slide bar 14 and the inner end of the buffer slot 13, one end of the buffer spring 15 is fixedly connected with the slide bar 14, the other end of the buffer spring 15 is fixedly connected with the inner end of the buffer slot 13, and the fulcrum ball 12 is fixedly mounted at one end of the slide bar 14, which is located outside the buffer slot 13.
Three guide grooves 8 are uniformly formed in the middle of the mounting sleeve 3 at positions corresponding to the three first connecting lugs 6 respectively, three second connecting lugs 9 which correspond to the three guide grooves 8 respectively and are in sliding fit with the guide grooves 8 are uniformly and fixedly arranged on the outer side of the nut sleeve 5, each second connecting lug 9 is hinged to one end of one connecting rod 10, and the other end of each connecting rod 10 is hinged to a third linking lug 11 arranged on the corresponding support leg rod 7.
The utility model discloses when unmanned aerial vehicle normal flight state, it is three the connecting rod and three the foot pole is in the state of drawing in, can not cause to shelter from to unmanned aerial vehicle's shooting sight and scope like this, can not influence unmanned aerial vehicle's normal function of making a video recording. When the unmanned aerial vehicle needs to land, the micro motor is started to drive the screw rod to rotate, and in the rotating process of the screw rod, the nut sleeve is connected with the thread threads, so that the nut sleeve can move linearly along the screw rod, and in the upward movement process of the nut sleeve, the three supporting leg rods are outwards propped open through the three connecting rods, so that the landing area of the unmanned aerial vehicle supporting leg mechanism is increased, the impact force applied to the supporting legs is reduced, a three-point supporting structure is formed, and the unmanned aerial vehicle supporting leg mechanism has good stability.
The above-mentioned embodiments are only intended to describe the preferred embodiments of the present invention, but not to limit the scope of the present invention, and those skilled in the art should also be able to make various modifications and improvements to the technical solution of the present invention without departing from the spirit of the present invention, and all such modifications and improvements are intended to fall within the scope of the present invention as defined in the appended claims.
Claims (3)
1. The utility model provides a shock attenuation formula unmanned aerial vehicle plays stabilizer blade mechanism that falls which characterized in that: the unmanned aerial vehicle is characterized by comprising a mounting seat (1) fixedly connected with an unmanned aerial vehicle main body, wherein a micro motor (2) is fixedly arranged inside the mounting seat (1), a mounting sleeve (3) is fixedly arranged at the bottom of the mounting seat (1), a driving shaft of the micro motor (2) is connected with the upper end of a vertically arranged screw (4), the screw (4) and the mounting sleeve (3) are coaxially arranged, and the lower end of the screw is rotatably connected with the bottom of the mounting sleeve (3); a nut sleeve (5) in threaded connection with the screw rod (4) is arranged on the screw rod, and the outer peripheral wall of the nut sleeve (5) is in sliding fit with the inner peripheral wall of the mounting sleeve (3);
three first connecting lugs (6) are uniformly arranged on the upper part of the mounting sleeve (3) along the circumferential direction, and each first connecting lug (6) is hinged with one end of one supporting leg rod (7) respectively; three guide grooves (8) are uniformly formed in the middle of the mounting sleeve (3) at positions corresponding to the three first connecting lugs (6) respectively;
the outer side of the nut sleeve (5) is uniformly provided with three second connecting lugs (9) which correspond to the three guide grooves (8) respectively and are in sliding fit with the guide grooves (8), each second connecting lug (9) is hinged with one end of a connecting rod (10), and the other end of each connecting rod (10) is hinged with a third connecting lug (11) arranged on the corresponding support leg rod (7).
2. The shock absorbing unmanned aerial vehicle landing leg mechanism of claim 1, wherein: the other end of each supporting foot rod (7) is provided with a supporting point ball (12).
3. The shock absorbing unmanned aerial vehicle landing leg mechanism of claim 2, wherein: the other end of each supporting foot rod (7) is provided with a buffer groove (13), a sliding rod (14) is arranged in each buffer groove (13) in a sliding mode, a buffer spring (15) is arranged between each sliding rod (14) and the inner end of each buffer groove (13), and the supporting point ball (12) is arranged at one end, located outside the buffer grooves (13), of each sliding rod (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020897990.4U CN212125507U (en) | 2020-05-26 | 2020-05-26 | Shock attenuation formula unmanned aerial vehicle stabilizer blade mechanism that rises and falls |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020897990.4U CN212125507U (en) | 2020-05-26 | 2020-05-26 | Shock attenuation formula unmanned aerial vehicle stabilizer blade mechanism that rises and falls |
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| Publication Number | Publication Date |
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| CN212125507U true CN212125507U (en) | 2020-12-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202020897990.4U Active CN212125507U (en) | 2020-05-26 | 2020-05-26 | Shock attenuation formula unmanned aerial vehicle stabilizer blade mechanism that rises and falls |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112319783A (en) * | 2021-01-04 | 2021-02-05 | 尚良仲毅(沈阳)高新科技有限公司 | System and unmanned aerial vehicle rise and fall |
| CN112407319A (en) * | 2020-12-15 | 2021-02-26 | 芜湖中科飞机制造有限公司 | Tail support frame of small-size training machine |
| CN113772091A (en) * | 2021-09-14 | 2021-12-10 | 海安市华军测量有限责任公司 | Engineering measuring equipment based on unmanned aerial vehicle |
-
2020
- 2020-05-26 CN CN202020897990.4U patent/CN212125507U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407319A (en) * | 2020-12-15 | 2021-02-26 | 芜湖中科飞机制造有限公司 | Tail support frame of small-size training machine |
| CN112407319B (en) * | 2020-12-15 | 2023-08-18 | 芜湖中科飞机制造有限公司 | Tail support frame of small training machine |
| CN112319783A (en) * | 2021-01-04 | 2021-02-05 | 尚良仲毅(沈阳)高新科技有限公司 | System and unmanned aerial vehicle rise and fall |
| CN113772091A (en) * | 2021-09-14 | 2021-12-10 | 海安市华军测量有限责任公司 | Engineering measuring equipment based on unmanned aerial vehicle |
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