CN106672221B - A kind of light aerocraft nose-gear - Google Patents
A kind of light aerocraft nose-gear Download PDFInfo
- Publication number
- CN106672221B CN106672221B CN201510755404.6A CN201510755404A CN106672221B CN 106672221 B CN106672221 B CN 106672221B CN 201510755404 A CN201510755404 A CN 201510755404A CN 106672221 B CN106672221 B CN 106672221B
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- damping
- rocker arm
- lockset
- chuck
- inner cylinder
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Abstract
The invention discloses a kind of light aerocraft nose-gears, including connection component, support component, wheel fork, wheel shaft and tire.Light aerocraft nose-gear further includes steering assembly and dampening assembly, and steering assembly and dampening assembly are respectively arranged at one end far from inner cylinder described in wheel fork.Steering assembly includes rocker arm and rocker arm control-rod, and one end of rocker arm is connected to inner cylinder, and the other end is connected to rocker arm control-rod.Dampening assembly includes damping lockset chuck, damping lockset and shock cord, and damping lockset chuck is fixed on inner cylinder, and one end of damping lockset is connected to damping lockset chuck, and shock cord is connected to damping lockset.Light aerocraft nose-gear of the invention has the characteristics that structure is simple, light-weight and complete function, meets the needs of light-duty class aircraft.
Description
Technical field
The invention belongs to the parts technical fields of light aerocraft, are related to light aerocraft nose-gear.
Background technique
With opening gradually for General Aviation in China field, the development of light-duty class aircraft welcomes opportunity, and modern aircraft
Nose-gear is many kinds of, and structure is often more complex, and components are more, heavier-weight, therefore is not suitable for light-duty class aircraft.
For this purpose, it is necessary to design a kind of light aerocraft nose-gear, the light aerocraft nose-gear have structure it is simple, it is light-weight and
The characteristics of complete function, to meet the needs of light-duty class aircraft.
Summary of the invention
The object of the present invention is to provide a kind of light aerocraft nose-gear, have the function of that structure is simple, light-weight and complete
Standby feature.
In order to solve the above-mentioned technical problem, the technical solution adopted by the present invention is that: a kind of light aerocraft nose-gear, including
Connection component, support component, wheel fork, wheel shaft and tire, the tire are installed on wheel shaft, and the wheel fork is connected with the wheel shaft
It connects, the support component includes outer cylinder and inner cylinder, and the inner tube installation is in the outer cylinder and can be in the outer cylinder along itself
Center line is freely rotated, and one end of the inner cylinder is connected to the wheel fork, and the connection component is for the outer cylinder to be installed on
On the fuselage of aircraft；
The light aerocraft nose-gear further includes steering assembly and dampening assembly, and the steering assembly and dampening assembly divide
It is not installed at one end far from inner cylinder described in the wheel fork, the steering assembly includes rocker arm and rocker arm control-rod, described to shake
One end of arm is connected to the inner cylinder, and the other end is connected to the rocker arm control-rod, and the dampening assembly includes damping lockset card
Disk, damping lockset and shock cord, the damping lockset chuck are fixed on the inner cylinder, and one end of the damping lockset is connected to
The damping lockset chuck, the shock cord are connected to the damping lockset.
Further, the quantity of the rocker arm control-rod is two, and one end of this two rocker arm control-rods is individually fixed in
The rocker arm, this two rocker arm control-rod shapes are in line.
Further, the connection component include connecting chuck, first connecting rod, the second connecting rod, third connecting rod and
4th connecting rod, the connecting chuck are installed at one end far from outer cylinder described in the wheel fork, the first connecting rod, second
Connecting rod, third connecting rod and the 4th connecting rod are connect with the fuselage of the connecting chuck and aircraft respectively.
Further, the center of the outer cylinder is equipped with fixed chuck.
Further, a sleeve, one end suit of the inner cylinder are installed at one end of outer cylinder described in the wheel fork
In in the sleeve.
The invention has the advantages that: light aerocraft nose-gears of the present invention, are equipped with steering assembly thereon, by turning
It is risen before the light aerocraft to the control inner cylinder rotation of the rocker arm control-rod of device so that rotating tire realizes the steering of light aerocraft
It falls frame and is also equipped with dampening assembly, the damping of light aerocraft is realized by the dampening assembly, therefore before light aerocraft of the invention
Undercarriage has the function of the steering of control light aerocraft and damping, and complete function, there are also the entirety of the light aerocraft nose-gear
Structure is simple, and components are few, and overall weight is light.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the light aerocraft nose-gear of the embodiment of the present invention.
Fig. 2 is the enlarged view of A in Fig. 1.
Fig. 3 is B direction view in Fig. 1.
Description of symbols:
Steering assembly 1, dampening assembly 3, outer cylinder 4, inner cylinder 5, sleeve 6, wheel fork 7, wheel shaft 8, tire 9, is consolidated connection component 2
Determine chuck 10；
Connecting chuck 21, first connecting rod 22, the second connecting rod 23, third connecting rod 24, the 4th connecting rod 25；
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
As shown in Figure 1, the light aerocraft nose-gear of the present embodiment, including connection component 2, support component, wheel fork 7, wheel
Axis 8, tire 9.Tire 9 is installed on wheel shaft 8, and wheel fork 7 is installed on wheel shaft 8.Support component includes outer cylinder 4 and inner cylinder 5, outer cylinder
A through-hole to match with inner cylinder 5 is machined on 4, the center line of the through-hole is overlapped with the center line of outer cylinder 4, and inner cylinder 5 is installed on outer
It can be freely rotated in the through-hole of cylinder 4 and along center line in the through hole, one end of inner cylinder 5 is fixed on wheel fork 7.It is preferred that setting
Meter, outer cylinder 4 and inner cylinder 5 are made of high strength steel, to improve its strength and stiffness.Connection component 2 is used for outer cylinder 4
It is installed on the fuselage of aircraft, referring to Fig. 2 and Fig. 3, connection component 2 includes connecting chuck 21, the connection of first connecting rod 22, second
Bar 23, third connecting rod 24 and the 4th connecting rod 25, connecting chuck 21 are fixed at one end far from 7 outer cylinder 4 of wheel fork, and first connects
Extension bar 22, the second connecting rod 23, third connecting rod 24 and the 4th connecting rod 25 one end be all machined with mounting hole, on connecting chuck
Four pairs of mounting holes are equably machined with, by bolt respectively by first connecting rod 22, the second connecting rod 23,24 and of third connecting rod
One end of 4th connecting rod 25 is fixed on connecting chuck 21, first connecting rod 22, the second connecting rod 23,24 and of third connecting rod
The other end of 4th connecting rod 25 is individually fixed in the fuselage (attached drawing is not shown) of aircraft, thus realize outer cylinder 4 is installed on it is winged
On the fuselage of machine.
The light aerocraft nose-gear of the present embodiment further includes steering assembly 1 and dampening assembly 3, steering assembly 1 and damping
Component 3 is respectively arranged at one end far from 7 inner cylinder 5 of wheel fork.
Referring to Figure 1 and Figure 3, steering assembly 1 includes rocker arm 11 and rocker arm control-rod 12, by bolt by one end of rocker arm 11
It is fixed on inner cylinder 5, the other end of rocker arm 11 is fixed with two rocker arm control-rods 12, one end point of this two rocker arm control-rods 12
It is not fixed on one end of rocker arm 11, this two 12 shapes of rocker arm control-rod are in line.
Referring to 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 at one end far from 7 inner cylinder 5 of wheel fork, and one end of damping lockset 32 is installed on damping lockset card by screw
On disk 31, shock cord 33 is set at one end far from 31 damping lockset 32 of damping lockset chuck, which is simultaneously connected to
The fuselage of aircraft.When design, shock cord 33 is also designed to elastomeric spring.
As optimal technical scheme, the center of outer cylinder 4 is equipped with fixed chuck 10, the machine of the fixation chuck 10 and aircraft
Body connection, so that preferably outer cylinder 4 is installed on the fuselage of aircraft.
As optimal technical scheme, a sleeve 6 is installed at one end of 7 outer cylinder 4 of wheel fork, inner cylinder 5 is set in the set
In cylinder 6.
Light aerocraft nose-gear of the present invention, is equipped with steering assembly thereon, passes through the rocker arm control of transfer
Bar control inner cylinder rotation processed, so that rotating tire realizes the steering of light aerocraft, which, which is also equipped with, subtracts
Component is shaken, the damping of light aerocraft is realized by the dampening assembly, therefore light aerocraft nose-gear of the invention has control
Light aerocraft turns to and the function of damping, and complete function, overall structure is also simple, and components are few, and overall weight is light.There are also uses
Non-maintaining self-lubricating technology reduces maintenance link and maintenance workload to light aerocraft nose-gear.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (5)
1. a kind of light aerocraft nose-gear, including connection component (2), support component, wheel fork (7), wheel shaft (8) and tire (9),
The tire (9) is installed on wheel shaft (8), and the wheel fork (7) is connected with the wheel shaft (8), and the support component includes outer
Cylinder (4) and inner cylinder (5), the inner cylinder (5) are installed in the outer cylinder (4) and can be in the outer cylinders (4) along center line
It is freely rotated, one end of the inner cylinder (5) is connected to the wheel fork (7), and the connection component (2) is used for the outer cylinder (4)
It is installed on the fuselage of aircraft, it is characterised in that:
The light aerocraft nose-gear further includes steering assembly (1) and dampening assembly (3), the steering assembly (1) and damping
Component (3) is respectively arranged at one end far from the wheel fork (7) inner cylinder (5), and the steering assembly (1) includes rocker arm
(11) and rocker arm control-rod (12), one end of the rocker arm (11) are connected to the inner cylinder (5), and the other end is connected to the rocker arm
Control-rod (12), the dampening assembly (3) include damping lockset chuck (31), damping lockset (32) and shock cord (33), described
Damping lockset chuck (31) is fixed on the inner cylinder (5), and one end of the damping lockset (32) is connected to the damping lockset
Chuck (31), the shock cord (33) are connected to the damping lockset (32).
2. a kind of light aerocraft nose-gear according to claim 1, which is characterized in that the rocker arm control-rod (12)
Quantity is two, and one end of this two rocker arm control-rods (12) is individually fixed in the rocker arm (11), this two rocker arm control-rods
(12) shape is in line.
3. a kind of light aerocraft nose-gear according to claim 1, which is characterized in that the connection component (2) includes
Connecting chuck (21), first connecting rod (22), the second connecting rod (23), third connecting rod (24) and the 4th connecting rod (25), institute
It states connecting chuck (21) to be installed at one end far from the wheel fork (7) outer cylinder (4), the first connecting rod (22), the
Two connecting rods (23), third connecting rod (24) and the 4th connecting rod (25) fuselage with the connecting chuck (21) and aircraft respectively
Connection.
4. a kind of light aerocraft nose-gear according to claim 1, which is characterized in that the center of the outer cylinder (4)
Fixed chuck (10) are installed.
5. a kind of light aerocraft nose-gear according to claim 1, which is characterized in that close to described in the wheel fork (7)
It is equipped at one end of outer cylinder (4) sleeve (6), the inner cylinder (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 CN106672221A (en) | 2017-05-17 |
| CN106672221B true 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) |
Families Citing this family (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 |
| 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 |
Citations (6)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7578465B2 (en) * | 2004-01-20 | 2009-08-25 | Lord Corporation | Aircraft front nose landing gear and method of making an aircraft landing gear |
-
2015
- 2015-11-06 CN CN201510755404.6A patent/CN106672221B/en not_active Expired - Fee Related
Patent Citations (6)
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106672221A (en) | 2017-05-17 |
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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 |