CN109835472A - A kind of small drone column support type spring nose-gear - Google Patents
A kind of small drone column support type spring nose-gear Download PDFInfo
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- CN109835472A CN109835472A CN201910222196.1A CN201910222196A CN109835472A CN 109835472 A CN109835472 A CN 109835472A CN 201910222196 A CN201910222196 A CN 201910222196A CN 109835472 A CN109835472 A CN 109835472A
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- landing gear
- piston rod
- undercarriage
- gear
- wheel
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- 238000013016 damping Methods 0.000 claims description 14
- 230000000712 assembly Effects 0.000 claims description 10
- 238000000429 assembly Methods 0.000 claims description 10
- 238000009434 installation Methods 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 229910001095 light aluminium alloy Inorganic materials 0.000 claims description 3
- 238000010521 absorption reaction Methods 0.000 abstract description 2
- 230000003139 buffering effect Effects 0.000 abstract description 2
- 239000006096 absorbing agent Substances 0.000 description 3
- 238000004064 recycling Methods 0.000 description 3
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 2
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- 241000283984 Rodentia Species 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- VLPFTAMPNXLGLX-UHFFFAOYSA-N trioctanoin Chemical compound CCCCCCCC(=O)OCC(OC(=O)CCCCCCC)COC(=O)CCCCCCC VLPFTAMPNXLGLX-UHFFFAOYSA-N 0.000 description 1
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Abstract
本发明提出的一种小型无人机支柱式弹簧前起落架，由机轮组件、起落架轮叉、活塞杆、起落架导向销、减震弹簧和起落架支撑杆组成；机轮组件与起落架轮叉通过起落架轮轴连接，活塞杆一端固连在起落架轮叉上，另一端插入前起落架支撑杆并通过起落架导向销安装在起落架支撑杆上。减震弹簧位于活塞杆与起落架支撑杆之间。起落架活塞杆可在起落架支撑杆内滑动。起落架活塞杆与起落架支撑杆之间的转动依靠起落架导向销限制约束，保证前起落架转向舵机对前轮的转向操纵。当无人机着地时，地面支反力通过机轮、轮叉传递到起落架活塞杆上。起落架活塞杆受力向上压缩缓冲弹簧，实现缓冲减震。起落架具有结构简单、重量轻、成本低的特点。
A small unmanned aerial vehicle strut-type spring front landing gear proposed by the present invention is composed of a wheel assembly, a landing gear fork, a piston rod, a landing gear guide pin, a shock-absorbing spring and a landing gear support rod; the wheel assembly is connected with the landing gear support rod. The landing gear wheel fork is connected through the landing gear wheel axle, one end of the piston rod is fixedly connected to the landing gear wheel fork, and the other end is inserted into the front landing gear support rod and installed on the landing gear support rod through the landing gear guide pin. The shock spring is located between the piston rod and the landing gear support rod. The landing gear piston rod is slidable within the landing gear support rod. The rotation between the landing gear piston rod and the landing gear support rod is restricted by the landing gear guide pin to ensure the steering control of the nose wheel by the steering gear of the front landing gear. When the drone hits the ground, the ground support reaction force is transmitted to the piston rod of the landing gear through the wheel and wheel fork. The piston rod of the landing gear is forced to compress the buffer spring upwards to achieve buffering and shock absorption. The landing gear has the characteristics of simple structure, light weight and low cost.
Description
Technical field
The present invention relates to air vehicle technique fields, specifically, rising and falling before being related to a kind of small drone column support type spring
Frame.
Background technique
Unmanned plane has the characteristics that weight is small, it is big to load, can go deep into numerous danger zones, has been widely used at present
The fields such as the reconnaissance of a campaign nature, geological prospecting, disaster assistance.The transmitting of unmanned plane and recovery stage are the key that in entire flight course
Stage.The radiation pattern of unmanned plane mainly has catapult-assisted take-off, rato, dolly takeoff, wheeled takeoff etc.；Recycling
Mode mainly has wheeled sliding race landing, arresting net recycling and parachuting recycling.Wherein, wheeled takeoff landing is due to its safety
It is good, take off before servicing time it is short the features such as and be widely used in most unmanned plane landing systems.
Currently, the crash energy absorption equipment of undercarriage mostly uses oleo-pneumatic shock absorber structure.Oleo-pneumatic shock absorber is due to its user
Just, energy absorbing efficiency height, reusable feature, and be applied in most of unmanned plane undercarriage endergonic structure.But it is right
For small drone, its weight of oil-gas type damper is larger, structure is complicated, the product manufacturing period is longer and pre-stage test takes
With higher, thus it is not suitable for small-sized sliding running UAV system.In order to be adapted to small-sized sliding race unmanned plane requirement, compel to be essential
Design a kind of low cost, small quality, the simple small drone Landing Gear System of structure.
Summary of the invention
In order to avoid the shortcomings of the prior art, the present invention rises and falls before proposing a kind of small drone column support type spring
Frame；The undercarriage has the characteristics that the Landing Gear System that structure is simple, light weight and cost is low, especially suitable for small drone.
The technical solution adopted by the present invention to solve the technical problems is: including wheel assemblies, undercarriage wheel shaft, undercarriage
Wheel fork, piston rod, undercarriage guide pin, damping spring and gear support bar, it is characterised in that the damping spring is mounted on
Between piston rod and gear support bar, damping spring one end and gear support bar are connected, and the other end is connect with piston rod, is subtracted
It shakes spring stress boil down to body and landing buffer power is provided；Undercarriage piston rod can slide in gear support bar；
The undercarriage wheel fork and wheel assemblies are connected by the installation of undercarriage wheel shaft, undercarriage wheel fork and piston rod one end
It is connected by bolt, the piston rod other end is embedded in gear support bar and passes through undercarriage guide pin and gear support bar is solid
Even；Rotational freedom between the undercarriage guide pin restriction piston rod and gear support bar, nose-gear turn to
Steering engine, which can be realized, controls steering；When UAV Landing, ground support reaction is transmitted to undercarriage by wheel, wheel fork
On piston rod, undercarriage piston rod stress compresses buffer spring upwards, realizes bumper and absorbing shock.
Landing gear structure uses light aluminum alloy material.
Beneficial effect
A kind of small drone column support type spring nose-gear proposed by the present invention, is a kind of mechanical elastic using column support type
Spring buffers nose-gear；Landing gear structure is simple, inexpensive and reusable；Undercarriage uses modular parts structure shape
Formula, Landing Gear System are assembled or are replaced simple and convenient.Landing gear structure is light-weight, using a large amount of aluminum hardwares, and padded coaming
Mechanical spring form is selected, it is light relative to oleo-pneumatic shock absorber system total quality.
Column support type spring nose-gear of the present invention by wheel assemblies, undercarriage wheel fork, piston rod, undercarriage guide pin, subtracts
Shake spring and gear support bar composition；By undercarriage wheel axis connection, piston rod one end is solid for wheel assemblies and undercarriage wheel fork
It is connected on undercarriage wheel fork, other end insertion nose-gear support rod is simultaneously mounted on gear support bar by undercarriage guide pin
On.Damping spring is between piston rod and gear support bar.Undercarriage piston rod can slide in gear support bar.It rises
The rotation between frame piston rod and gear support bar is fallen by undercarriage guide pin restriction, guarantees that nose-gear turns to rudder
Handling maneuver of the machine to front-wheel.When unmanned plane lands, ground support reaction is transmitted to undercarriage piston rod by wheel, wheel fork
On.Undercarriage piston rod stress compresses buffer spring upwards, realizes bumper and absorbing shock purpose.
Column support type spring nose-gear of the present invention can repeatedly use, non-maintaining during use；Made using compressed spring
It does not need to inspect periodically the components such as air pressure and sealing ring, maintenance workload is small relative to oil gas bumper for padded coaming.
Column support type spring nose-gear aerodynamic drag of the present invention is small；It being designed using column support type nose-gear, aerodynamic drag is small,
Convenient for nose-gear rectification repairing type design.
Column support type spring nose-gear of the present invention has the characteristics that structure is simple, light weight and cost is low, especially suitable for small
The Landing Gear System of type unmanned plane.
Detailed description of the invention
A kind of small drone column support type spring nose-gear of the present invention is made into one with embodiment with reference to the accompanying drawing
Step is described in detail.
Fig. 1 is small drone column support type spring nose-gear shaft side figure of the present invention.
Fig. 2 is small drone column support type spring nose-gear structural schematic diagram of the present invention.
Fig. 3 is small drone column support type spring nose-gear structural side view of the present invention.
In figure:
1. 5. gear support bar of wheel assemblies 2. undercarriage wheel shaft, 3. undercarriage wheel fork, 4. piston rod, 6. undercarriage is oriented to
7. damping spring of pin
Specific embodiment
The present embodiment is a kind of small drone column support type spring nose-gear.
Refering to fig. 1~Fig. 3, the present embodiment small drone column support type spring nose-gear, by wheel assemblies 1, undercarriage
Wheel shaft 2, undercarriage wheel fork 3, piston rod 4, undercarriage guide pin 6, damping spring 7 and gear support bar 5 form；Wherein, subtract
Shake spring 7 is mounted between piston rod 4 and gear support bar 5, and 7 one end of damping spring and gear support bar 5 are connected, another
End is fixedly connected with piston rod 4, and 7 forced compression of damping spring provides landing buffer power for body.Undercarriage piston rod 4 can rise
Fall sliding in frame support rod 5；Rotation between undercarriage piston rod and gear support bar limits about by undercarriage guide pin
Beam guarantees nose-gear steering-engine to the handling maneuver of front-wheel.
Undercarriage wheel fork 3 and wheel assemblies 1 are connected by the installation of undercarriage wheel shaft 2, undercarriage wheel fork 3 and piston rod 4 one
End is connected by bolt, and 4 other end of piston rod is embedded in nose-gear support rod 5 and passes through undercarriage guide pin 6 and undercarriage
Support rod 5 is fixedly connected.Rotational freedom between 6 restriction piston rod 4 of undercarriage guide pin and gear support bar 5,
Nose-gear steering-engine, which can be realized, controls steering.When UAV Landing, ground support reaction passes through wheel, wheel fork
It is transmitted on undercarriage piston rod, undercarriage piston rod stress compresses buffer spring upwards, realizes bumper and absorbing shock.
In the present embodiment, landing gear structure uses light aluminum alloy material.
In the present embodiment, after installation is complete, piston rod can slide in gear support bar.Undercarriage piston rod with rise
The rotation between frame support rod is fallen by undercarriage guide pin restriction, guarantees steering of the nose-gear steering-engine to front-wheel
Manipulation.When unmanned plane landing, the ground connection of wheel assemblies 1 is moved upwards by the effect of ground support reaction, to drive undercarriage wheel
Fork 3 and piston rod 4 move upwards together.Since 7 one end of damping spring and gear support bar 5 are connected, the other end and piston rod 4
It is connected.Therefore, 7 forced compression of damping spring provides landing buffer power for body.Undercarriage piston rod stress compresses buffering upwards
Spring, to reach bumper and absorbing shock.
In the ground taxi stage, since the rotational freedom of the rotational freedom and gear support bar 5 of piston rod 4 passes through
Undercarriage guide pin 6 constrains, and nose-gear steering-engine can realize the course changing control to aircraft.Landing gear structure has structure letter
Feature single, light weight and cost is low, the Landing Gear System especially suitable for small drone.
Claims (2)
1. a kind of small drone column support type spring nose-gear, including wheel assemblies, undercarriage wheel shaft, undercarriage wheel fork, work
Stopper rod, undercarriage guide pin, damping spring and gear support bar, it is characterised in that: the damping spring is mounted on piston rod
Between gear support bar, damping spring one end and gear support bar are connected, and the other end is connect with piston rod, damping spring
Forced compression provides landing buffer power for body；Undercarriage piston rod can slide in gear support bar；
The undercarriage wheel fork and wheel assemblies are connected by the installation of undercarriage wheel shaft, and undercarriage wheel fork passes through with piston rod one end
Bolt is connected, and the piston rod other end is embedded in gear support bar and is connected by undercarriage guide pin and gear support bar；
Rotational freedom between the undercarriage guide pin restriction piston rod and gear support bar, nose-gear steering-engine
It can be achieved to control steering；When UAV Landing, ground support reaction is transmitted to undercarriage piston by wheel, wheel fork
On bar, undercarriage piston rod stress compresses buffer spring upwards, realizes bumper and absorbing shock.
2. small drone column support type spring nose-gear according to claim 1, it is characterised in that: landing gear structure is adopted
With light aluminum alloy material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910222196.1A CN109835472A (en) | 2019-03-22 | 2019-03-22 | A kind of small drone column support type spring nose-gear |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910222196.1A CN109835472A (en) | 2019-03-22 | 2019-03-22 | A kind of small drone column support type spring nose-gear |
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| Publication Number | Publication Date |
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| CN109835472A true CN109835472A (en) | 2019-06-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910222196.1A Pending CN109835472A (en) | 2019-03-22 | 2019-03-22 | A kind of small drone column support type spring nose-gear |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110386245A (en) * | 2019-08-16 | 2019-10-29 | 西安星火航电智能科技有限公司 | A kind of rotation direction has the unmanned plane undercarriage and unmanned plane of damping |
| CN111086628A (en) * | 2020-01-17 | 2020-05-01 | 河南大学 | Hidden foot rest of unmanned aerial vehicle |
| CN113716028A (en) * | 2021-10-18 | 2021-11-30 | 复旦大学 | Shock attenuation undercarriage and unmanned aerial vehicle |
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| CN2675532Y (en) * | 2003-11-24 | 2005-02-02 | 蔡贵席 | Scooter steering device with damping device |
| CN206107553U (en) * | 2016-10-17 | 2017-04-19 | 江苏工程职业技术学院 | Unmanned wheel undercarriage for helicopter |
| CN106628130A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism |
| CN106628125A (en) * | 2016-12-28 | 2017-05-10 | 中国航天电子技术研究院 | Quick-disassembling energy absorption undercarriage for multi-rotor unmanned aerial vehicle |
| US20170203835A1 (en) * | 2016-01-14 | 2017-07-20 | Embraer S.A. | Retractable self-aligning aircraft stablizer strut assembly and aircraft including the same |
| CN107914868A (en) * | 2017-12-07 | 2018-04-17 | 佛山市神风航空科技有限公司 | Take photo by plane the undercarriage cushioning mechanism of unmanned plane |
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2019
- 2019-03-22 CN CN201910222196.1A patent/CN109835472A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2675532Y (en) * | 2003-11-24 | 2005-02-02 | 蔡贵席 | Scooter steering device with damping device |
| US20170203835A1 (en) * | 2016-01-14 | 2017-07-20 | Embraer S.A. | Retractable self-aligning aircraft stablizer strut assembly and aircraft including the same |
| CN206107553U (en) * | 2016-10-17 | 2017-04-19 | 江苏工程职业技术学院 | Unmanned wheel undercarriage for helicopter |
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| CN106628125A (en) * | 2016-12-28 | 2017-05-10 | 中国航天电子技术研究院 | Quick-disassembling energy absorption undercarriage for multi-rotor unmanned aerial vehicle |
| CN107914868A (en) * | 2017-12-07 | 2018-04-17 | 佛山市神风航空科技有限公司 | Take photo by plane the undercarriage cushioning mechanism of unmanned plane |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110386245A (en) * | 2019-08-16 | 2019-10-29 | 西安星火航电智能科技有限公司 | A kind of rotation direction has the unmanned plane undercarriage and unmanned plane of damping |
| CN111086628A (en) * | 2020-01-17 | 2020-05-01 | 河南大学 | Hidden foot rest of unmanned aerial vehicle |
| CN113716028A (en) * | 2021-10-18 | 2021-11-30 | 复旦大学 | Shock attenuation undercarriage and unmanned aerial vehicle |
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Application publication date: 20190604 |