CN205150223U - Four shaft air vehicle's shock attenuation undercarriage - Google Patents
Four shaft air vehicle's shock attenuation undercarriage Download PDFInfo
- Publication number
- CN205150223U CN205150223U CN201520911551.3U CN201520911551U CN205150223U CN 205150223 U CN205150223 U CN 205150223U CN 201520911551 U CN201520911551 U CN 201520911551U CN 205150223 U CN205150223 U CN 205150223U
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- CN
- China
- Prior art keywords
- undercarriage
- gear
- alighting gear
- upper arm
- profile
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
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Abstract
The utility model relates to a four shaft air vehicle's shock attenuation undercarriage, it has the shock -absorbing function unmanned aerial vehicle undercarriage to belong to one kind. Utilize the support to fix the motor, the motor drives the receipts of undercarriage through two sections belts of a set of gear drive along different orientation transmission, rethread belt, and the undercarriage hinges with linking firmly the ware, and the upper end is connected through the extension spring, and built -in spring is connected through the crossbeam to two arms about the undercarriage is divided into. The advantage is novel structure, and the undercarriage can receive and release according to the state of flight, has reduced the resistance of flight in -process air, has improved unmanned aerial vehicle's stability greatly. At the descending in -process, the undercarriage is scalable, has reduced the impact load coefficient, has improved unmanned aerial vehicle's security.
Description
Technical field
The utility model belongs to one shock-absorbing function unmanned plane alighting gear, is specifically related to the alighting gear of freedom retractable and Telescopic, be mainly used in reducing in flight course slowing down in resistance and decline process in the face of the impulsive force of fuselage.
Background technology
Four rotor wing unmanned aerial vehicles are a kind of Small and micro-satellite, and because flexibility ratio is high, stability is strong, and simple to operate, the advantages such as cost is lower gain great popularity.But, four current rotor wing unmanned aerial vehicles, aloft during flight because its fixing alighting gear makes resistance increase, in addition, when landing faced by fuselage can cause very strong rigid shock, in this regard, four rotor wing unmanned aerial vehicles still face very large challenge.
Summary of the invention
The utility model provides a kind of damping alighting gear of four-axle aircraft, the problem of rigid shock during to solve the flight resistance of current Small and micro-satellite existence and to land.
The technical scheme that the utility model is taked is: motor is contained in for connecting in the support of unmanned plane, gear one is connected with the output shaft of motor, gear two is connected with holder pivots by axle, gear one and gear two are connected with a joggle, profile of tooth power wheel one is fixedly connected on the output shaft between gear one and motor, profile of tooth power wheel two is fixedly connected between gear and support, profile of tooth power wheel one is connected with odontoid belt one, profile of tooth power wheel two is connected with odontoid belt two, odontoid belt one, odontoid belt two opposite side is connected with the profile of tooth power wheel of two alighting gear upper arm respectively, wherein alighting gear upper arm and the device chain connection that is connected, alighting gear upper arm is connected extension spring with being connected between device, it is fixing after alighting gear upper arm and alighting gear underarm enter the chute of alighting gear upper arm by crossbeam-rotating, and the built-in spring of difference, the attaching parts be connected with fuselage is connected with the device that is connected.
The utility model alighting gear upper arm one is connected extension spring one with being connected between device one.
The utility model has the advantages that novel structure, alighting gear can carry out folding and unfolding according to state of flight, decreases the resistance of air in flight course, substantially increases the stability of unmanned plane.In descent, alighting gear is scalable, reduces impact load coefficient, improves the safety of unmanned plane.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the birds-eye view of the utility model transmission device and alighting gear;
Fig. 3 is the part sectional view of the utility model transmission device;
Fig. 4 is the structural representation of the utility model alighting gear;
Fig. 5 is the structural representation of the built-in spring of the utility model alighting gear;
Fig. 6 is the structural representation of the utility model alighting gear upper arm;
Fig. 7 is the A-A cutaway view of Fig. 6.
Detailed description of the invention
Motor 2 is contained in for connecting in the support 1 of unmanned plane, gear 1 is connected with the output shaft of motor 2, gear 24 is connected with holder pivots by axle, gear 1 and gear 24 are connected with a joggle, profile of tooth power wheel 1 is fixedly connected on the output shaft between gear 1 and motor 2, profile of tooth power wheel 26 is fixedly connected between gear 4 and support 2, profile of tooth power wheel 1 is connected with odontoid belt 1, profile of tooth power wheel 26 is connected with odontoid belt 28, odontoid belt one, odontoid belt two opposite side is connected with the profile of tooth power wheel 1201 of two alighting gear upper arm 12 respectively, wherein alighting gear upper arm 12 and device 10 chain connection that is connected, alighting gear upper arm 12 is connected extension spring 11 with being connected between device 10, alighting gear upper arm 12 and alighting gear underarm 13 are fixing rotated into the chute 1202 of alighting gear upper arm 12 by crossbeam 1301 after, and the built-in spring 14 of difference, the attaching parts 9 be connected with fuselage is connected with the device 10 that is connected.
Principle of work: in unmanned plane during flying process, by the rotation of control step motor 2, driven gear 1 and profile of tooth power wheel 1 rotate, power is reached on belt 1, gear 1 drives driven gear 24 to rotate, power is passed to profile of tooth power wheel 26, power reaches on belt 28 by profile of tooth power wheel 26; Belt 27, belt 28 drive the profile of tooth power wheel 1201 of alighting gear upper arm 12 to rotate respectively, drive the folding and unfolding of alighting gear entirety, alighting gear upper arm 12 is connected extension spring 11 with being connected between device 10, when stepping motor 2 runs out of steam, alighting gear can be retracted initial position in time, alighting gear upper arm 12 is connected with alighting gear underarm 13, and built-in spring 14 is when droping to ground, alighting gear underarm 13 Compress Spring 14, plays the effect of damping.
Claims (2)
1. the damping alighting gear of a four-axle aircraft, it is characterized in that: motor is contained in for connecting in the support of unmanned plane, gear one is connected with the output shaft of motor, gear two is connected with holder pivots by axle, gear one and gear two are connected with a joggle, profile of tooth power wheel one is fixedly connected on the output shaft between gear one and motor, profile of tooth power wheel two is fixedly connected between gear and support, profile of tooth power wheel one is connected with odontoid belt one, profile of tooth power wheel two is connected with odontoid belt two, odontoid belt one, odontoid belt two opposite side is connected with the profile of tooth power wheel of two alighting gear upper arm respectively, wherein alighting gear upper arm and the device chain connection that is connected, alighting gear upper arm is connected extension spring with being connected between device, it is fixing after alighting gear upper arm and alighting gear underarm enter the chute of alighting gear upper arm by crossbeam-rotating, and the built-in spring of difference, the attaching parts be connected with fuselage is connected with the device that is connected.
2. the damping alighting gear of a kind of four-axle aircraft according to claim 1, is characterized in that: alighting gear upper arm one is connected extension spring one with being connected between device one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520911551.3U CN205150223U (en) | 2015-11-16 | 2015-11-16 | Four shaft air vehicle's shock attenuation undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520911551.3U CN205150223U (en) | 2015-11-16 | 2015-11-16 | Four shaft air vehicle's shock attenuation undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205150223U true CN205150223U (en) | 2016-04-13 |
Family
ID=55685941
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520911551.3U Withdrawn - After Issue CN205150223U (en) | 2015-11-16 | 2015-11-16 | Four shaft air vehicle's shock attenuation undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205150223U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292446A (en) * | 2015-11-16 | 2016-02-03 | 吉林大学 | Damping undercarriage of quadrotor |
| CN105966605A (en) * | 2016-05-19 | 2016-09-28 | 郑琳琳 | Delta parallel mechanism-based six-rotor aircraft |
| CN106394882A (en) * | 2016-09-18 | 2017-02-15 | 西安爱生技术集团公司 | Sliding groove type unmanned aerial vehicle skid collecting and releasing mechanism |
| CN107444622A (en) * | 2016-05-31 | 2017-12-08 | 比亚迪股份有限公司 | For unmanned plane landing gear assembly and there is its unmanned plane |
-
2015
- 2015-11-16 CN CN201520911551.3U patent/CN205150223U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292446A (en) * | 2015-11-16 | 2016-02-03 | 吉林大学 | Damping undercarriage of quadrotor |
| CN105966605A (en) * | 2016-05-19 | 2016-09-28 | 郑琳琳 | Delta parallel mechanism-based six-rotor aircraft |
| CN105966605B (en) * | 2016-05-19 | 2017-11-24 | 亳州沃野知识产权服务有限公司 | A kind of six rotorcraft based on delta parallel institutions |
| CN107444622A (en) * | 2016-05-31 | 2017-12-08 | 比亚迪股份有限公司 | For unmanned plane landing gear assembly and there is its unmanned plane |
| CN107444622B (en) * | 2016-05-31 | 2020-01-03 | 比亚迪股份有限公司 | A unmanned aerial vehicle that is used for unmanned aerial vehicle's undercarriage subassembly and has it |
| CN106394882A (en) * | 2016-09-18 | 2017-02-15 | 西安爱生技术集团公司 | Sliding groove type unmanned aerial vehicle skid collecting and releasing mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160413 Effective date of abandoning: 20170531 |