CN108839791A - A kind of damping wheel mechanism - Google Patents
A kind of damping wheel mechanism Download PDFInfo
- Publication number
- CN108839791A CN108839791A CN201810992060.4A CN201810992060A CN108839791A CN 108839791 A CN108839791 A CN 108839791A CN 201810992060 A CN201810992060 A CN 201810992060A CN 108839791 A CN108839791 A CN 108839791A
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- CN
- China
- Prior art keywords
- connector
- hinge hole
- wheel mechanism
- steering shaft
- damping wheel
- 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.)
- Pending
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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
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
Abstract
The invention discloses a kind of damping wheel mechanisms, it is installed on the fuselage of fixed-wing unmanned plane, including the first connector and the second vertically arranged connector being laterally arranged, the both ends of first connector are provided with hinge hole, the upper end of second connector and middle-end are provided with hinge hole, the front end of first connector and the upper end of the second connector or middle-end are hinged, the rear end of first connector is corresponding to be provided with elastomeric element between the middle-end or upper end of the second connector, and the lower end of the second connector is fixed with wheel by removable fixation means.Damping wheel mechanism of the invention has many advantages, such as that effectiveness in vibration suppression is excellent, turns to flexible.
Description
Technical field
The present invention relates to unmanned plane fields, and in particular to a kind of damping wheel mechanism.
Background technique
Unmanned plane was quickly grown in recent years, the wheel of fixed-wing unmanned plane as unmanned plane it is sliding run, load-bearing important zero
Part, play the role of to the operation of unmanned plane it is vital, especially front-wheel also carry unmanned plane steering effect, nobody
Machine front-wheel needs more flexible steering and better vibration-damping function, therefore, how to design it is a kind of turn to flexibly, vibration-damping function it is excellent
Front-wheel mechanism be a technical problem that technical personnel in the field need to solve at present.
Summary of the invention
The main object of the present invention is to provide a kind of damping wheel mechanism, this damping wheel mechanism can be flexibly when unmanned plane takes off
Direction is controlled, when landing can play the role of buffer shock-absorbing.
In order to achieve the above object, the present invention is resolved using following technical scheme.
A kind of damping wheel mechanism, is installed on the fuselage of fixed-wing unmanned plane, including the first connector for being laterally arranged and
The second vertically arranged connector, the rear and front end of the first connector are provided with hinge hole, the upper end of the second connector and middle-end
It is provided with hinge hole, the front end of the first connector and the upper end of the second connector or middle-end are hinged, the rear end pair of the first connector
Elastomeric element should be provided between the middle-end or upper end of the second connector, the lower end of the second connector is detachable solid by first
Determine device and is fixed with wheel.
Preferably, the hinge hole of the first connector front end and the hinge hole of the second connector upper end are hinged, and elastomeric element is
Compressed spring；Compressed spring both ends are provided with mounting hole, the mounting hole at compressed spring both ends respectively with the first connector rear end
Hinge hole and the hinge hole of the second connector middle-end are hinged.
Preferably, the hinge hole of the first connector front end and the hinge hole of the second connector middle-end are hinged, and elastomeric element is
Extension spring；Extension spring both ends are provided with mounting hole, the mounting hole at extension spring both ends respectively with the first connector rear end
Hinge hole and the hinge hole of the second connector upper end are hinged.
Preferably, the first connector is symmetrically arranged dual link arm, and extension spring quantity is two, is symmetrically disposed on the
The two sides of a connection piece.
Preferably, the second connector is curved boom, and the upper end and knee of curved boom is arranged in the hinge hole of the second connector 2.
Preferably, the lower end of the second connector is provided with wheel mounting hole, and the first removable fixation means are stud
And nut, it wheel and is fixed on by stud and nut on the wheel mounting hole of the second connector lower end.
Preferably, fuselage is provided with wheel steering-engine, and wheel steering-engine is connected with steering shaft；Steering shaft connects with first
Fitting is fixedly connected by the second removable fixation means.
Preferably, the first connector rear end is vertically arranged with steering shaft mounting hole, and pin hole is provided in steering shaft, turns to
Axis and the first connector are fixedly connected by pin.
Preferably, it is connected between wheel steering-engine and steering shaft by connecting rod.
Preferably, fuselage is provided with fixing seat, fixing seat and steering axis connection, and is provided between fixing seat and steering shaft
Bearing.
For the vibration damping wheel mechanism of technical solution of the present invention compared with the existing technology, have effectiveness in vibration suppression excellent, turns to spirit
The advantages that living.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
The structure shown according to these attached drawings obtains other attached drawings.
Fig. 1 is the schematic diagram of the damping wheel mechanism of one embodiment of the present invention；
Fig. 2 is the exploded view of the damping wheel mechanism of one embodiment of the present invention.
In the above figure：1 first connector；2 second connectors；21 wheel mounting holes；22 studs；23 nuts；3 draw
Stretch spring；4 wheels；5 wheel steering-engines；6 steering shafts；61 pin holes；7 turn to shaft mounting hole；8 fixing seats；9 pins.
Specific embodiment
It is understandable in order to enable the above objects, features and advantages of the present invention to become apparent, with reference to the accompanying drawing to this hair
Bright specific embodiment is described in detail.
Detail is elaborated in the following description to fully understand the present invention.But the present invention can with it is a variety of not
Other way described herein is same as to implement, those skilled in the art can do class without violating the connotation of the present invention
Like popularization.Therefore the present invention is not limited by following public specific embodiment.
With reference to Fig. 1 and Fig. 2, a kind of damping wheel mechanism is installed on the fuselage of fixed-wing unmanned plane, including what is be laterally arranged
First connector 1 and the second vertically arranged connector 2, the rear and front end of the first connector 1 are provided with hinge hole, the second connection
The upper end of part 2 and middle-end are provided with hinge hole, and the front end of the first connector 1 and the upper end of the second connector 2 or middle-end are hinged, the
The rear end of a connection piece 1 is corresponding to be provided with elastomeric element between the middle-end or upper end of the second connector 2, the second connector 2
Lower end is fixed with wheel 4 by the first removable fixation means.
In above embodiments, wheel 4 and ground generate impact force when unmanned plane lands, and are absorbed by setting elastomeric element
The impact force of wheel 4 when being contacted with ground, elastomeric element are equipped with two ways, the first is：The front end of first connector 1
It is hinged with the upper end of the second connector 2, then bullet is arranged between the rear end of the first connector 1 and the middle-end of the second connector 2
Property component；It is for second：The front end of first connector 1 and the middle-end of the second connector 2 are hinged, then in the first connector 1
Elastomeric element is set between rear end and the upper end of the second connector 2.
Further, the hinge hole of 1 front end of the first connector and the hinge hole of 2 upper end of the second connector are hinged, elastic portion
Part is compressed spring；The both ends of compressed spring are provided with mounting hole, the mounting hole at compressed spring both ends respectively with the first connector 1
The hinge hole of 2 middle-end of the hinge hole of rear end and the second connector is hinged.
In above embodiments, when the hinge hole hinge of 2 upper end of hinge hole and the second connector of the front end of the first connector 1
It connects, elastomeric element is compressed spring；Compressed spring one end is mounted on the rear end hinge hole of the first connector 1, and the other end is installed on
Second connector, 2 middle-end hinge hole, the unmanned plane smaller for impact force can choose the damper mechanism of this mode.
Further, the hinge hole of 1 front end of the first connector and the hinge hole of 2 middle-end of the second connector are hinged, elastic portion
Part is extension spring 3；3 both ends of extension spring are provided with mounting hole, the mounting hole at 3 both ends of extension spring respectively with the first connector
The hinge hole of 2 upper end of the hinge hole of 1 rear end and the second connector is hinged.
In above embodiments, the hinge hole of 1 front end of the first connector and the hinge hole of 2 middle-end of the second connector are hinged, bullet
Property component be extension spring 3,3 one end of extension spring is mounted on the rear end hinge hole of the first connector 1, and the other end is installed on second
2 upper end hinge hole of connector, the damper mechanism effectiveness in vibration suppression of the unmanned plane bigger for impact force, such mode is more excellent, and
And since spring is in tensional state, the defects of bending will not be generated.
Further, the first connector 1 is symmetrically arranged dual link arm, and 3 quantity of extension spring is two, symmetrically
It is set to the two sides of the first connector 1.
In above embodiments, for stress equalization, the first connector 1 is designed as dual link arm configuration, is accordingly used
Two extension springs 3 are laid in 1 two sides of the first connector respectively, and effectiveness in vibration suppression is more stable, and the service life is longer.
Further, the second connector 2 is curved boom, and upper end and the bending of curved boom is arranged in the hinge hole of the second connector 2
Place.
In above embodiments, in order to enhance the intensity of the second connector 2, the second connector 2 is designed as curved under normal conditions
Arm configuration.In addition, by the actual conditions of unmanned plane structure, 2 upper space of the second connector is narrow, by the second connector 2
It is designed to that curved boom structure can make full use of space.
Further, the lower end of the second connector 2 is provided with wheel mounting hole 21, and the first removable fixation means are double end
Bolt 22 and nut 23, wheel 4 and the wheel mounting hole that 2 lower end of the second connector is fixed on by stud 22 and nut 23
On 21.
In above embodiments, wheel 4 is fixed on the lower end wheel peace of the second connector 2 by stud 22 and nut 23
It fills on hole 21, design for disassembly makes easy to maintenance, and in preferred situation, axis can be set between wheel 4 and stud 22
Hold reduction frictional force.
Further, fuselage is provided with wheel steering-engine 5, and wheel steering-engine 5 is connected with steering shaft 6；Steering shaft 6 with
First connector 1 is fixedly connected by the second removable fixation means.
In above embodiments, turned to control unmanned plane, fuselage is provided with wheel steering-engine 5, wheel steering-engine 5
It is connected with steering shaft 6, steering shaft 6 is fixedly connected with the first connector 1.For the ease of maintenance, connection type passes through detachable
Fixed device connection.
Further, 1 rear end of the first connector, which is vertically arranged with, turns to shaft mounting hole 7, is provided with pin hole in steering shaft 6
61, steering shaft 6 is fixedly connected with the first connector 1 by pin 9.
In above embodiments, rotation cannot skid between steering shaft 6 and the first connector 1, therefore, steering shaft 6 and first
Connector 1 passes through the pin hole 61 in steering shaft 6 by pin 9, can prevent from skidding between steering shaft 6 and the first connector 1.
Further, it is connected between wheel steering-engine 5 and the steering shaft 6 by connecting rod.
Further, fuselage is provided with fixing seat 8, and the fixing seat 8 is connect with steering shaft 6, and fixing seat 8 and described turn
Bearing is provided between axis 6.
In above embodiments, fixing seat 8 is provided on fuselage, it, can be with fuselage after fixing seat 8 is connect with steering shaft 6
It is connected as one, in order to rotate flexibly, bearing is usually set between fixing seat 8 and steering shaft 6 and reduces frictional force.
Although the present invention is described in detail with a general description of the specific embodiments in this specification,
But on the basis of the present invention, it can be made some modifications or improvements, this it will be apparent to those skilled in the art that.Cause
This, these modifications or improvements on the basis of without departing from the present invention are fallen within the scope of the claimed invention.
Claims (10)
1. a kind of damping wheel mechanism, is installed on the fuselage of fixed-wing unmanned plane, which is characterized in that including be laterally arranged first
Connector (1) and vertically arranged the second connector (2), the rear and front end of first connector (1) are provided with hinge hole, institute
The upper end and middle-end for stating the second connector (2) are provided with hinge hole, and the front end of first connector (1) is connect with described second
The upper end of part (2) or middle-end are hinged, the corresponding middle-end or upper end with the second connector (2) in the rear end of first connector (1)
Between be provided with elastomeric element, the lower end of second connector (2) is fixed with wheel by the first removable fixation means
(4)。
2. damping wheel mechanism according to claim 1, which is characterized in that the hinge hole of the first connector (1) front end
Hinged with the hinge hole of the second connector (2) upper end, the elastomeric element is compressed spring；The compressed spring both ends are set
It is equipped with mounting hole, the mounting hole at the compressed spring both ends hinge hole and second with the first connector (1) rear end respectively
The hinge hole of connector (2) middle-end is hinged.
3. damping wheel mechanism according to claim 1, which is characterized in that the hinge hole of the first connector (1) front end
Hinged with the hinge hole of the second connector (2) middle-end, the elastomeric element is extension spring (3)；The extension spring (3)
Both ends are provided with mounting hole, and the mounting hole at extension spring (3) both ends is hinged with the first connector (1) rear end respectively
The hinge hole of hole and the second connector (2) upper end is hinged.
4. damping wheel mechanism according to claim 3, which is characterized in that first connector (1) is symmetrically arranged
Dual link arm, extension spring (3) quantity are two, are symmetrically disposed on the two sides of the first connector (1).
5. damping wheel mechanism according to claim 1, which is characterized in that second connector (2) is curved boom, described the
The upper end and knee of curved boom is arranged in the hinge hole of two connectors (2).
6. damping wheel mechanism according to claim 1, which is characterized in that the lower end of second connector (2) is provided with
Wheel mounting hole (21), first removable fixation means are stud (22) and nut (23), and the wheel (4) passes through
The stud (22) and nut (23) are fixed on the wheel mounting hole (21) of the second connector (2) lower end.
7. damping wheel mechanism according to claim 1, which is characterized in that the fuselage is provided with wheel steering-engine (5),
The wheel steering-engine (5) is connected with steering shaft (6)；The steering shaft (6) and first connector (1) can by second
Fixed device is dismantled to be fixedly connected.
8. damping wheel mechanism according to claim 7, which is characterized in that the first connector (1) rear end is vertically arranged
Have steering shaft mounting hole (7), is provided with pin hole (61) on the steering shaft (6), the steering shaft (6) and the first connector
(1) it is fixedly connected by pin (9).
9. damping wheel mechanism according to claim 7, which is characterized in that the wheel steering-engine (5) and the steering
It is connected between axis (6) by connecting rod.
10. damping wheel mechanism according to claim 7, which is characterized in that the fuselage is provided with fixing seat (8), described
Fixing seat (8) is connect with the steering shaft (6), and is provided with bearing between the fixing seat (8) and the steering shaft (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810992060.4A CN108839791A (en) | 2018-08-29 | 2018-08-29 | A kind of damping wheel mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810992060.4A CN108839791A (en) | 2018-08-29 | 2018-08-29 | A kind of damping wheel mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108839791A true CN108839791A (en) | 2018-11-20 |
Family
ID=64233883
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810992060.4A Pending CN108839791A (en) | 2018-08-29 | 2018-08-29 | A kind of damping wheel mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108839791A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111216880A (en) * | 2020-02-05 | 2020-06-02 | 新昌县羽林街道智西机械厂 | Undercarriage control mechanism of small aircraft |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB282715A (en) * | 1926-12-27 | 1928-08-23 | Ford Motor Co | Improvements in airplane tail supporting wheel |
| CN103057693A (en) * | 2012-12-25 | 2013-04-24 | 天津三爻航空航天科技发展有限公司 | Fixed wing aircraft tail wheel steering apparatus |
| CN105197229A (en) * | 2015-10-16 | 2015-12-30 | 河南翱翔航空科技有限公司 | Front landing gear of unmanned aerial vehicle |
| CN205738066U (en) * | 2016-06-12 | 2016-11-30 | 北京象限空间科技有限公司 | One turns to undercarriage to control to subtract oscillator system |
| CN106428535A (en) * | 2016-12-02 | 2017-02-22 | 北京尖翼科技有限公司 | Nose landing gear of unmanned aerial vehicle |
| CN206327564U (en) * | 2016-11-29 | 2017-07-14 | 北京白米科技有限公司 | A kind of main landing gear of unmanned flight's machine |
| US20170217574A1 (en) * | 2016-01-29 | 2017-08-03 | Daniel Roger Dufault | Suspension For Aircraft Tail Wheel |
| CN207045710U (en) * | 2017-06-29 | 2018-02-27 | 北京国遥星图航空科技有限公司 | A kind of light-duty fixed-wing unmanned plane undercarriage |
| CN208731212U (en) * | 2018-08-29 | 2019-04-12 | 西安航远数字技术有限公司 | A kind of damping wheel mechanism |
-
2018
- 2018-08-29 CN CN201810992060.4A patent/CN108839791A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB282715A (en) * | 1926-12-27 | 1928-08-23 | Ford Motor Co | Improvements in airplane tail supporting wheel |
| CN103057693A (en) * | 2012-12-25 | 2013-04-24 | 天津三爻航空航天科技发展有限公司 | Fixed wing aircraft tail wheel steering apparatus |
| CN105197229A (en) * | 2015-10-16 | 2015-12-30 | 河南翱翔航空科技有限公司 | Front landing gear of unmanned aerial vehicle |
| US20170217574A1 (en) * | 2016-01-29 | 2017-08-03 | Daniel Roger Dufault | Suspension For Aircraft Tail Wheel |
| CN205738066U (en) * | 2016-06-12 | 2016-11-30 | 北京象限空间科技有限公司 | One turns to undercarriage to control to subtract oscillator system |
| CN206327564U (en) * | 2016-11-29 | 2017-07-14 | 北京白米科技有限公司 | A kind of main landing gear of unmanned flight's machine |
| CN106428535A (en) * | 2016-12-02 | 2017-02-22 | 北京尖翼科技有限公司 | Nose landing gear of unmanned aerial vehicle |
| CN207045710U (en) * | 2017-06-29 | 2018-02-27 | 北京国遥星图航空科技有限公司 | A kind of light-duty fixed-wing unmanned plane undercarriage |
| CN208731212U (en) * | 2018-08-29 | 2019-04-12 | 西安航远数字技术有限公司 | A kind of damping wheel mechanism |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111216880A (en) * | 2020-02-05 | 2020-06-02 | 新昌县羽林街道智西机械厂 | Undercarriage control mechanism of small aircraft |
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