CN106672221A - Light aircraft nose landing gear - Google Patents
Light aircraft nose landing gear Download PDFInfo
- Publication number
- CN106672221A CN106672221A CN201510755404.6A CN201510755404A CN106672221A CN 106672221 A CN106672221 A CN 106672221A CN 201510755404 A CN201510755404 A CN 201510755404A CN 106672221 A CN106672221 A CN 106672221A
- Authority
- CN
- China
- Prior art keywords
- damping
- chuck
- outer tube
- inner core
- rocking arm
- 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.)
- Granted
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Abstract
The invention discloses a light aircraft nose landing gear, which comprises a coupling assembly, a supporting assembly, a wheel-fork, a wheel spindle and a tyre. The light aircraft nose landing gear also comprises a steering assembly and a damping assembly, which are respectively installed at one end of an inner cylinder far from the wheel-fork. The steering assembly contains a rocker arm and a rocker arm controlling rod. One end of the rocker arm is connected to the inner cylinder, and the other end of the rocker arm is connected to the rocker arm controlling rod. The damping assembly contains a damping lock chuck, a damping lock and a damping rope. The damping lock chuck is fixed on the inner cylinder. One end of the damping lock is connected to the damping lock chuck. The damping rope is connected to the damping lock. The light aircraft nose landing gear has characteristics of simple structure, light weight and complete function, and meets requirements of light aircrafts.
Description
Technical field
The invention belongs to the parts technical field of light aerocraft, is related to light aerocraft nose-gear.
Background technology
With opening gradually for General Aviation in China field, the development of light-duty class aircraft welcomes opportunity, and rises and falls before present generation aircraft
Frame species is various, and its structure is often more complicated, and parts are more, heavier-weight, therefore is not suitable for light-duty class aircraft.For this purpose,
Necessary to design a kind of light aerocraft nose-gear, the light aerocraft nose-gear has simple structure, lightweight and function complete
Standby the characteristics of, to meet the demand of light-duty class aircraft.
The content of the invention
It is an object of the invention to provide a kind of light aerocraft nose-gear, it has simple structure, lightweight and complete function spy
Point.
In order to solve above-mentioned technical problem, the technical solution used in the present invention is：A kind of light aerocraft nose-gear, including connection
Component, support component, wheel fork, wheel shaft and tire, the tire is installed on wheel shaft, and the wheel fork is connected with the wheel shaft,
The support component includes outer tube and inner core, and the inner tube installation is in the outer tube and can be in the outer tube along its center line
Freely rotate, one end of the inner core is connected to the wheel fork, and the coupling assembly is used to that the outer tube to be installed on the machine of aircraft
With；
The light aerocraft nose-gear also includes steering assembly and dampening assembly, and the steering assembly and dampening assembly are respectively mounted
In the end away from inner core described in the wheel fork, the steering assembly includes rocking arm and rocking arm control-rod, one end of the rocking arm
The inner core is connected to, the other end is connected to the rocking arm control-rod, and the dampening assembly includes that damping lockset chuck, damping are locked
Tool and shock cord, the damping lockset chuck is fixed on the inner core, and one end of the damping lockset is connected to the damping lock
Tool chuck, the shock cord is connected to the damping lockset.
Further, the quantity of the rocking arm control-rod is two, and one end of this two rocking arm control-rods is individually fixed in described shaking
Arm, this two rocking arm control-rod shapes are in line.
Further, the coupling assembly includes connecting chuck, head rod, the second connecting rod, the 3rd connecting rod and the 4th
Connecting rod, the connecting chuck is installed on the end away from outer tube described in the wheel fork, the head rod, the second connection
Bar, the 3rd connecting rod and the 4th connecting rod are connected respectively with the fuselage of the connecting chuck and aircraft.
Further, the center of the outer tube is provided with fixed chuck.
Further, the end near outer tube described in the wheel fork is provided with a sleeve, and one end of the inner core is set in the set
In cylinder.
Beneficial effect of the present invention：Light aerocraft nose-gear of the present invention, is provided with thereon steering assembly, by turning to dress
The rocking arm control-rod control inner core put is rotated, and so as to rotating tire realizes the steering of light aerocraft, the light aerocraft nose-gear is also
Dampening assembly is installed, the damping of light aerocraft, therefore the light aerocraft nose-gear tool of the present invention are realized by the dampening assembly
There is control light aerocraft to turn to the function with damping, complete function, the also overall structure of the light aerocraft nose-gear are simple,
Parts are few, and overall weight is light.
Description of the drawings
Fig. 1 is the structural representation of the light aerocraft nose-gear of the embodiment of the present invention.
Fig. 2 is the zoomed-in view of A in Fig. 1.
Fig. 3 is B direction views in Fig. 1.
Description of reference numerals：
Steering assembly 1, coupling assembly 2, dampening assembly 3, outer tube 4, inner core 5, sleeve 6, wheel fork 7, wheel shaft 8, tire
9th, fixed chuck 10；
Rocking arm 11, rocking arm control-rod 12；
Connecting chuck 21, head rod 22, the second connecting rod 23, the 3rd connecting rod 24, the 4th connecting rod 25；
Damping lockset chuck 31, damping lockset 32, shock cord 33.
Specific embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely retouched
State, it is clear that described embodiment is only a part of embodiment of the invention, rather than the embodiment of whole.Based on the present invention
In embodiment, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made,
Belong to the scope of protection of the invention.
As shown in figure 1, the light aerocraft nose-gear of the present embodiment, including coupling assembly 2, support component, wheel fork 7, wheel shaft
8th, tire 9.Tire 9 is installed on wheel shaft 8, and wheel fork 7 is installed on wheel shaft 8.Support component includes outer tube 4 and inner core 5,
A through hole matched with inner core 5 is machined with outer tube 4, the center line of the through hole overlaps with the center line of outer tube 4, and inner core 5 is pacified
Can rotate in through hole loaded on outer tube 4 and freely along its center line in the through hole, one end of inner core 5 is fixed on wheel fork 7.
Decision design, outer tube 4 and inner core 5 are made using high strength steel and are formed, so as to improve its strength and stiffness.Coupling assembly 2 is used
In outer tube 4 is installed on the fuselage of aircraft, with reference to Fig. 2 and Fig. 3, coupling assembly 2 connects including connecting chuck 21, first
Bar 22, the second connecting rod 23, the 3rd connecting rod 24 and the 4th connecting rod 25, connecting chuck 21 is fixed on outside away from wheel fork 7
The end of cylinder 4, one end of head rod 22, the second connecting rod 23, the 3rd connecting rod 24 and the 4th connecting rod 25 all adds
Work has installing hole, and four pairs of installing holes are equably machined with connecting chuck, is respectively connected head rod 22, second by bolt
One end of extension bar 23, the 3rd connecting rod 24 and the 4th connecting rod 25 is fixed on connecting chuck 21, head rod 22,
The other end of two connecting rods 23, the 3rd connecting rod 24 and the 4th connecting rod 25 is individually fixed in the fuselage (accompanying drawing is not shown) of aircraft,
So as to realize that outer tube 4 is installed on the fuselage of aircraft.
The light aerocraft nose-gear of the present embodiment also includes steering assembly 1 and dampening assembly 3, steering assembly 1 and dampening assembly 3
It is respectively arranged in the end away from the inner core 5 of wheel fork 7.
With reference to Fig. 1 and Fig. 3, steering assembly 1 includes rocking arm 11 and rocking arm control-rod 12, by bolt by one end of rocking arm 11
It is fixed on inner core 5, the other end of rocking arm 11 is fixed with two rocking arm control-rods 12, one end of this two rocking arm control-rods 12
One end of rocking arm 11 is individually fixed in, this two shapes of rocking arm control-rod 12 are in line.
See figures.1.and.2, dampening assembly 3 includes damping lockset chuck 31, damping lockset 32 and shock cord 33, damping lock
Tool chuck 31 is fixed on the end away from the inner core 5 of wheel fork 7, and one end of damping lockset 32 is installed on damping lockset by screw
On chuck 31, shock cord 33 is set in the end away from the damping lockset 32 of damping lockset chuck 31, and the shock cord 33 simultaneously connects
It is connected to the fuselage of aircraft.During design, shock cord 33 is also designed to elastomeric spring.
Used as optimal technical scheme, the center of outer tube 4 is provided with fixed chuck 10, the fuselage of the fixation chuck 10 and aircraft
Connection, so as to preferably outer tube 4 is installed on the fuselage of aircraft.
Used as optimal technical scheme, the end near the outer tube 4 of wheel fork 7 is provided with a sleeve 6, and inner core 5 is set in the sleeve 6
It is interior.
Light aerocraft nose-gear of the present invention, is provided with thereon steering assembly, by the rocking arm control-rod control of transfer
Inner core processed is rotated, and so as to rotating tire realizes the steering of light aerocraft, the light aerocraft nose-gear is also equipped with dampening assembly,
The damping of light aerocraft is realized by the dampening assembly, therefore there is the light aerocraft nose-gear of the present invention control light aerocraft to turn
To the function with damping, complete function, overall structure is also simple, and parts are few, and overall weight is light.Also using non-maintaining
Self-lubricating technology, reduces the maintenance link to light aerocraft nose-gear and maintenance workload.
Presently preferred embodiments of the present invention is the foregoing is only, not to limit the present invention, all spiritual and originals in the present invention
Within then, any modification, equivalent substitution and improvements made etc. should be included within the scope of the present invention.
Claims (5)
1. a kind of light aerocraft nose-gear, including coupling assembly (2), support component, wheel fork (7), wheel shaft (8) and wheel
Tire (9), the tire (9) is installed on wheel shaft (8), and the wheel fork (7) is connected with the wheel shaft (8), described
Support component includes outer tube (4) and inner core (5), and the inner core (5) is installed in the outer tube (4) and can be in the outer tube
(4) freely rotate along its center line in, one end of the inner core (5) is connected to the wheel fork (7), the coupling assembly
(2) for the outer tube (4) to be installed on the fuselage of aircraft, it is characterised in that：
The light aerocraft nose-gear also includes steering assembly (1) and dampening assembly (3), the steering assembly (1) and subtracts
Shake component (3) is respectively arranged in the end away from the wheel fork (7) inner core (5), steering assembly (1) bag
Rocking arm (11) and rocking arm control-rod (12) are included, one end of the rocking arm (11) is connected to the inner core (5), other end connection
In the rocking arm control-rod (12), the dampening assembly (3) is including damping lockset chuck (31), damping lockset (32) and subtracts
Shake rope (33), the damping lockset chuck (31) is fixed on the inner core (5), one end of the damping lockset (32)
The damping lockset chuck (31) is connected to, the shock cord (33) is connected to the damping lockset (32).
2. a kind of light aerocraft nose-gear according to claim 1, it is characterised in that the rocking arm control-rod (12)
Quantity be two, one end of this two rocking arm control-rods (12) is individually fixed in the rocking arm (11), this two rocking arms control
Bar (12) shape is in line.
3. a kind of light aerocraft nose-gear according to claim 1, it is characterised in that the coupling assembly (2) includes
Connecting chuck (21), head rod (22), the second connecting rod (23), the 3rd connecting rod (24) and the 4th connecting rod (25),
The connecting chuck (21) is installed on the end away from the wheel fork (7) outer tube (4), the head rod (22),
Second connecting rod (23), the 3rd connecting rod (24) and the 4th connecting rod (25) respectively with the connecting chuck (21) and aircraft
Fuselage connection.
4. a kind of light aerocraft nose-gear according to claim 1, it is characterised in that the center of the outer tube (4)
Fixed chuck (10) is installed.
5. a kind of light aerocraft nose-gear according to claim 1, it is characterised in that near the wheel fork (7) described
The end of outer tube (4) is provided with a sleeve (6), and the inner core (5) is set in the sleeve (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510755404.6A CN106672221B (en) | 2015-11-06 | 2015-11-06 | A kind of light aerocraft nose-gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510755404.6A CN106672221B (en) | 2015-11-06 | 2015-11-06 | A kind of light aerocraft nose-gear |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106672221A true CN106672221A (en) | 2017-05-17 |
| CN106672221B CN106672221B (en) | 2019-10-15 |
Family
ID=58863964
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510755404.6A Expired - Fee Related CN106672221B (en) | 2015-11-06 | 2015-11-06 | A kind of light aerocraft nose-gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106672221B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985566A (en) * | 2017-12-07 | 2018-05-04 | 佛山市神风航空科技有限公司 | Aerial photography aircraft undercarriage with damping auxiliary wheel |
| CN114148509A (en) * | 2021-12-03 | 2022-03-08 | 中国特种飞行器研究所 | Steering structure of front landing gear of light sport aircraft and assembling method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB505109A (en) * | 1937-11-04 | 1939-05-04 | Gen Aircraft Ltd | Improvements relating to landing gear arrangements of aircraft |
| GB893550A (en) * | 1958-08-11 | 1962-04-11 | Dowty Rotol Ltd | Improvements in or relating to aircraft undercarriages |
| FR2801865A1 (en) * | 1999-12-03 | 2001-06-08 | Messier Dowty Sa | Aircraft front landing gear comprises undercarriage leg pivoted by actuator, leg comprises caisson, sliding rod and rotating sleeve connected to orientation control device |
| WO2005070761A2 (en) * | 2004-01-20 | 2005-08-04 | Lord Corporation | Aircraft front nose landing gear and method of making an aircraft landing gear |
| CN104192303A (en) * | 2014-09-15 | 2014-12-10 | 沈阳飞机工业（集团）有限公司 | Small nose landing gear for unmanned aerial vehicle |
| CN204399469U (en) * | 2014-12-04 | 2015-06-17 | 天津全华时代航天科技发展有限公司 | A kind of unmanned plane alighting gear |
| CN205150224U (en) * | 2015-11-06 | 2016-04-13 | 珠海航太科技有限公司 | Light aircraft nose -gear |
-
2015
- 2015-11-06 CN CN201510755404.6A patent/CN106672221B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB505109A (en) * | 1937-11-04 | 1939-05-04 | Gen Aircraft Ltd | Improvements relating to landing gear arrangements of aircraft |
| GB893550A (en) * | 1958-08-11 | 1962-04-11 | Dowty Rotol Ltd | Improvements in or relating to aircraft undercarriages |
| FR2801865A1 (en) * | 1999-12-03 | 2001-06-08 | Messier Dowty Sa | Aircraft front landing gear comprises undercarriage leg pivoted by actuator, leg comprises caisson, sliding rod and rotating sleeve connected to orientation control device |
| WO2005070761A2 (en) * | 2004-01-20 | 2005-08-04 | Lord Corporation | Aircraft front nose landing gear and method of making an aircraft landing gear |
| CN104192303A (en) * | 2014-09-15 | 2014-12-10 | 沈阳飞机工业（集团）有限公司 | Small nose landing gear for unmanned aerial vehicle |
| CN204399469U (en) * | 2014-12-04 | 2015-06-17 | 天津全华时代航天科技发展有限公司 | A kind of unmanned plane alighting gear |
| CN205150224U (en) * | 2015-11-06 | 2016-04-13 | 珠海航太科技有限公司 | Light aircraft nose -gear |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985566A (en) * | 2017-12-07 | 2018-05-04 | 佛山市神风航空科技有限公司 | Aerial photography aircraft undercarriage with damping auxiliary wheel |
| CN114148509A (en) * | 2021-12-03 | 2022-03-08 | 中国特种飞行器研究所 | Steering structure of front landing gear of light sport aircraft and assembling method thereof |
| CN114148509B (en) * | 2021-12-03 | 2023-12-22 | 中国特种飞行器研究所 | Light-duty sport aircraft nose landing gear steering structure and assembly method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106672221B (en) | 2019-10-15 |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191015 Termination date: 20201106 |