CN112173087A - Unmanned aerial vehicle's damping formula undercarriage - Google Patents
Unmanned aerial vehicle's damping formula undercarriage Download PDFInfo
- Publication number
- CN112173087A CN112173087A CN202010975392.9A CN202010975392A CN112173087A CN 112173087 A CN112173087 A CN 112173087A CN 202010975392 A CN202010975392 A CN 202010975392A CN 112173087 A CN112173087 A CN 112173087A
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- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- hydraulic damper
- tension spring
- bolt
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- 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.)
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- 238000013016 damping Methods 0.000 title claims abstract description 21
- 230000002238 attenuated effect Effects 0.000 description 3
- 239000000872 buffer Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/60—Oleo legs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
- Fluid-Damping Devices (AREA)
- Vibration Prevention Devices (AREA)
Abstract
本发明公开了一种无人机的减振式起落架，包括安装于无人机上的液压阻尼器，与液压阻尼器的活塞杆铰接且与机轮活动连接的轮架，以及两端分别与液压阻尼器的缸体和轮架连接的拉簧。本发明通过三部分的衰减结构可以使无人机的各部分零部件受到的冲击极大地被衰减，以保证无人机的安全起落，并且拉簧的两端套设于插销上，从而可以快速地将拉簧与液压阻尼器和轮架连接在一起。在拆卸时，只需将拉簧的该端脱出插销即可快速地将拉簧拆卸下来，拆卸和更换方便、快捷。本发明还可以根据无人机的总体重量，通过更换不同的拉簧和液压阻尼器，可以调节起落架承重的范围，使搭配承重在许可范围内，使用灵活和范围广。
The invention discloses a vibration-damping undercarriage of an unmanned aerial vehicle, comprising a hydraulic damper mounted on the unmanned aerial vehicle, a wheel frame hinged with a piston rod of the hydraulic damper and movably connected with a wheel, and two ends respectively connected with The cylinder block of the hydraulic damper is connected to the tension spring of the wheel frame. The three-part attenuation structure of the present invention can greatly attenuate the impact on each part of the drone, so as to ensure the safe rise and fall of the drone. Attach the tension spring to the hydraulic damper and wheel carrier. During disassembly, the tension spring can be quickly disassembled by simply pulling the end of the tension spring out of the latch, and the disassembly and replacement are convenient and fast. According to the overall weight of the unmanned aerial vehicle, the present invention can also adjust the load-bearing range of the landing gear by replacing different tension springs and hydraulic dampers, so that the matching load-bearing range is within the permitted range, and the use is flexible and wide.
Description
Technical Field
The invention relates to an undercarriage, in particular to a vibration reduction type undercarriage of an unmanned aerial vehicle.
Background
When the unmanned aerial vehicle takes off, lands and slides on the ground, the undercarriage plays a role in supporting the aircraft. The main effect of undercarriage is that the damping unmanned aerial vehicle receives the impact vibration of ground transmission, is that unmanned aerial vehicle takes off, lands, runs, ground removes and parks necessary strutting arrangement, and an undercarriage that has good damping effect can effectively ensure that unmanned aerial vehicle does not receive the damage.
The undercarriage of the existing unmanned aerial vehicle has the following defects: 1. the existing landing gear only uses a tension spring to damp vibration, although the mode can play a certain role in damping vibration, aftershocks of a certain range can be generated when the tension spring rebounds, so that the unmanned aerial vehicle is in potential danger; 2. the damping module structural design of current undercarriage is more complicated, can not be by quick detach and change when it damages, and the maintenance is troublesome and consuming time long.
Disclosure of Invention
The invention aims to solve the problems and provides a vibration damping landing gear of an unmanned aerial vehicle, which has a good vibration damping effect and is convenient and quick to mount and dismount. This undercarriage can launch the damping structure of three kinds of differences simultaneously and cushion the impact, makes the impact that each part spare part of unmanned aerial vehicle received attenuated greatly to guarantee unmanned aerial vehicle's safety and take off and land.
The purpose of the invention can be achieved by adopting the following technical scheme:
the utility model provides an unmanned aerial vehicle's damping formula undercarriage, is including installing the hydraulic damper on unmanned aerial vehicle, articulated and wheel carrier with wheel swing joint with hydraulic damper's piston rod to and the extension spring that both ends are connected with hydraulic damper's cylinder body and wheel carrier respectively.
As a preferable scheme, the tension spring is mounted on a cylinder body of the hydraulic damper through a first bolt.
As a preferred scheme, be equipped with on the first bolt and be used for restricting the extension spring along the gliding retaining ring of first bolt axial direction, the retaining ring is located the both sides of extension spring.
As a preferable scheme, the first bolt is provided with an external thread, a cylinder body of the hydraulic damper is provided with a threaded hole, and the first bolt is in threaded connection with the cylinder body of the hydraulic damper.
Preferably, the tension spring is mounted on the upper part of the wheel frame through a second bolt.
As a preferred scheme, the second bolt is provided with a retaining ring for limiting the tension spring to slide along the axial direction of the second bolt, and the retaining ring is arranged on two sides of the tension spring.
As a preferable scheme, the second bolt is provided with an external thread, the wheel carrier is provided with a threaded hole, and the second bolt is in threaded connection with a cylinder body of the hydraulic damper.
As a preferable scheme, the wheel carrier is U-shaped, and the wheel is rotatably mounted in a U-shaped groove of the wheel carrier through a pin shaft.
Preferably, the wheel is rotatably mounted on the pin by a bearing.
As a preferred scheme, open on hydraulic damper's the cylinder body has the through-hole, the through-hole is connected and is in the same place hydraulic damper's cylinder body and unmanned aerial vehicle fixed connection through bolt and unmanned aerial vehicle.
The implementation of the invention has the following beneficial effects:
1. when the unmanned aerial vehicle takes off and slides or lands in the moment, the ground is in contact with the undercarriage to generate vibration impact. The attenuation of this impact by the landing gear mainly consists of three parts: 1. when the airplane wheel is in contact with the ground, the elasticity of the airplane wheel buffers small vibration impact; 2. the wheel carrier is stressed to tilt forwards, so that the tension spring connected with the wheel carrier is stretched, and a part of impact force is reduced; 3. when the wheel frame is stressed to generate forward tilting, the wheel frame simultaneously presses the hydraulic damper, so that the hydraulic damper generates damping force to attenuate a part of vibration force again. The whole process can make the impact that each part spare part of unmanned aerial vehicle received greatly attenuated through the decay structure of triplex to guarantee unmanned aerial vehicle's safety to rise and fall.
2. The invention can adjust the bearing range of the undercarriage by replacing different tension springs and hydraulic dampers according to the total weight of the unmanned aerial vehicle, so that the matched bearing is in an allowable range, and the unmanned aerial vehicle is flexible to use and wide in range.
3. Two ends of the tension spring are sleeved on the plug pins, so that the tension spring, the hydraulic damper and the wheel carrier can be quickly connected together. When the pull spring is disassembled, the pull spring can be rapidly disassembled only by separating the end of the pull spring from the bolt, and the disassembly and the replacement are convenient and rapid.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural view of a vibration-damped landing gear of the unmanned aerial vehicle of the present invention.
Fig. 2 is a schematic structural view of fig. 1 with the wheel frame and the frame removed.
Fig. 3 is a schematic structural view of fig. 1 with the tension spring and the hydraulic damper removed.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Examples
Referring to fig. 1 to 3, the embodiment relates to a vibration damping landing gear of an unmanned aerial vehicle, which includes a hydraulic damper 1 installed on the unmanned aerial vehicle, a wheel carrier 3 hinged to a piston rod 11 of the hydraulic damper 1 and movably connected to a wheel 2, and a tension spring 4 having two ends respectively connected to a cylinder 12 of the hydraulic damper 1 and the wheel carrier 3.
When the unmanned aerial vehicle takes off and slides or lands in the moment, the ground is in contact with the undercarriage to generate vibration impact. The attenuation of this impact by the landing gear mainly consists of three parts: 1. when the airplane wheel 2 is in contact with the ground, the elastic buffer of the airplane wheel 2 can buffer small vibration impact; 2. the wheel carrier 3 is stressed to tilt forwards, so that the tension spring 4 connected with the wheel carrier is stretched, and a part of impact force is reduced; 3. in the forward tilting process of the wheel frame 3 caused by force, the wheel frame 3 simultaneously presses the hydraulic damper 1, so that the hydraulic damper 1 generates damping force to attenuate a part of vibration force again. The whole process can make the impact that each part spare part of unmanned aerial vehicle received greatly attenuated through the decay structure of triplex to guarantee unmanned aerial vehicle's safety to rise and fall.
According to the invention, the load bearing range of the undercarriage can be adjusted by replacing different tension springs 4 and hydraulic dampers 1 according to the total weight of the unmanned aerial vehicle, so that the matched load bearing is in an allowable range, and the unmanned aerial vehicle is flexible to use and wide in range.
The tension spring 4 is mounted on the cylinder body 12 of the hydraulic damper 1 through a first bolt 5. One end of the tension spring 4 is sleeved on the first bolt 5, so that the tension spring 4 and the hydraulic damper 1 can be quickly connected together. When the tension spring 4 is disassembled, the tension spring 4 can be rapidly disassembled only by separating the end of the tension spring 4 from the first bolt 5, and the disassembly and the replacement are convenient and rapid.
In order to prevent one end of the tension spring 4 from sliding along the axial direction of the first bolt 5 and being separated, a retaining ring 6 for limiting the tension spring 4 to slide along the axial direction of the first bolt 5 is arranged on the first bolt 5, and the retaining ring 6 is arranged on two sides of the tension spring 4.
The hydraulic damper is characterized in that an external thread is arranged on the first bolt 5, a threaded hole is formed in the cylinder body 12 of the hydraulic damper 1, and the first bolt 5 is in threaded connection with the cylinder body 12 of the hydraulic damper 1. The purpose of rapidly detaching the tension spring 4 can also be achieved by unscrewing the first bolt 5 from the cylinder 12 of the hydraulic damper 1.
The tension spring 4 is mounted on the upper part of the wheel frame 3 through a second bolt 7. The other end of the tension spring 4 is sleeved on the second bolt 7, so that the tension spring 4 and the wheel carrier 3 can be quickly connected together. When the tension spring 4 is disassembled, the tension spring 4 can be rapidly disassembled only by separating the end of the tension spring 4 from the second bolt 7, and the disassembly and the replacement are convenient and rapid.
In order to prevent the other end of the tension spring 4 from sliding along the axial direction of the second bolt 7 and being disengaged, a retaining ring 6 for limiting the tension spring 4 to slide along the axial direction of the second bolt 7 is arranged on the second bolt 7, and the retaining ring 6 is arranged on two sides of the tension spring 4.
The second bolt 7 is provided with an external thread, the wheel carrier 3 is provided with a threaded hole, and the second bolt 7 is in threaded connection with the cylinder body 12 of the hydraulic damper 1. The second bolt 7 is unscrewed from the wheel frame 3, so that the tension spring 4 can be quickly disassembled.
The wheel carrier 3 is U-shaped, and the wheel 2 is rotatably arranged in the U-shaped groove of the wheel carrier 3 through a pin shaft 8. The wheel 2 is rotatably mounted on a pin 8 through a bearing.
Open on hydraulic damper 1's the cylinder body 12 has through-hole 13, through-hole 13 is connected and is in the same place hydraulic damper 1's cylinder body 12 and unmanned aerial vehicle fixed connection through bolt and unmanned aerial vehicle.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (10)
1. The utility model provides an unmanned aerial vehicle's damping formula undercarriage, its characterized in that, is including installing the hydraulic damper on unmanned aerial vehicle, articulated and wheel carrier with wheel swing joint with hydraulic damper's piston rod to and the extension spring that both ends are connected with hydraulic damper's cylinder body and wheel carrier respectively.
2. A vibration damped landing gear for unmanned aerial vehicles according to claim 1, wherein said tension spring is mounted to the cylinder of the hydraulic damper by a first pin.
3. The vibration damping landing gear of an unmanned aerial vehicle according to claim 2, wherein the first bolt is provided with a retaining ring for limiting the tension spring to slide along the axial direction of the first bolt, and the retaining ring is arranged on two sides of the tension spring.
4. A vibration damping undercarriage for an unmanned aerial vehicle according to claim 3 wherein the first pin has external threads and the hydraulic damper has a threaded bore in its cylinder, the first pin being threadedly connected to the hydraulic damper cylinder.
5. A vibration damping landing gear for unmanned aerial vehicles according to claim 1, wherein the tension spring is mounted to the upper portion of the wheel carrier by a second latch.
6. A vibration damping undercarriage for an unmanned aerial vehicle according to claim 5 wherein the second bolt is provided with a retaining ring for limiting the extension spring to slide along the axial direction of the second bolt, the retaining ring being provided on both sides of the extension spring.
7. A vibration damping landing gear for an unmanned aerial vehicle according to claim 6, wherein the second bolt is provided with external threads, the wheel carrier is provided with a threaded hole, and the second bolt is in threaded connection with a cylinder body of the hydraulic damper.
8. A vibration damped landing gear for unmanned aerial vehicles according to claim 1, wherein said wheel carrier is U-shaped, and said wheels are rotatably mounted in the U-shaped slots of the wheel carrier by pins.
9. A vibration damped landing gear for an unmanned aerial vehicle according to claim 8, wherein the wheel is rotatably mounted on the pin by means of a bearing.
10. A vibration damping undercarriage for an unmanned aerial vehicle according to claim 1 wherein the cylinder of the hydraulic damper is provided with a through hole, and the through hole is connected to the unmanned aerial vehicle by a bolt to fixedly connect the cylinder of the hydraulic damper to the unmanned aerial vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010975392.9A CN112173087A (en) | 2020-09-16 | 2020-09-16 | Unmanned aerial vehicle's damping formula undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010975392.9A CN112173087A (en) | 2020-09-16 | 2020-09-16 | Unmanned aerial vehicle's damping formula undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112173087A true CN112173087A (en) | 2021-01-05 |
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ID=73921484
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010975392.9A Pending CN112173087A (en) | 2020-09-16 | 2020-09-16 | Unmanned aerial vehicle's damping formula undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112173087A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090050736A1 (en) * | 2005-08-04 | 2009-02-26 | Messier-Dowty Limited | Landing gear |
| DE102011053613B3 (en) * | 2011-09-14 | 2012-10-11 | Erwin Tratz | Shock strut for chassis of model jet, has upper part at which linkage is arranged, where linkage is formed as two-arm lever and vibration damper is arranged between upper part and long lever arm of linkage |
| CN106507760B (en) * | 2007-12-21 | 2013-08-14 | 成都飞机工业（集团）有限责任公司 | Rocker-arm unmanned plane can quick-release undercarriage |
| CN204656000U (en) * | 2015-04-30 | 2015-09-23 | 李复钦 | Rocker extension spring shock-absorbing landing gear for model aircraft |
| CN106143881A (en) * | 2016-07-29 | 2016-11-23 | 江西核工业测绘院 | A kind of unmanned plane deceleration damping undercarriage |
-
2020
- 2020-09-16 CN CN202010975392.9A patent/CN112173087A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090050736A1 (en) * | 2005-08-04 | 2009-02-26 | Messier-Dowty Limited | Landing gear |
| CN106507760B (en) * | 2007-12-21 | 2013-08-14 | 成都飞机工业（集团）有限责任公司 | Rocker-arm unmanned plane can quick-release undercarriage |
| DE102011053613B3 (en) * | 2011-09-14 | 2012-10-11 | Erwin Tratz | Shock strut for chassis of model jet, has upper part at which linkage is arranged, where linkage is formed as two-arm lever and vibration damper is arranged between upper part and long lever arm of linkage |
| CN204656000U (en) * | 2015-04-30 | 2015-09-23 | 李复钦 | Rocker extension spring shock-absorbing landing gear for model aircraft |
| CN106143881A (en) * | 2016-07-29 | 2016-11-23 | 江西核工业测绘院 | A kind of unmanned plane deceleration damping undercarriage |
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| PB01 | Publication | ||
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Application publication date: 20210105 |