CN109927889A - A kind of military aircraft main landing gear - Google Patents
A kind of military aircraft main landing gear Download PDFInfo
- Publication number
- CN109927889A CN109927889A CN201711365917.1A CN201711365917A CN109927889A CN 109927889 A CN109927889 A CN 109927889A CN 201711365917 A CN201711365917 A CN 201711365917A CN 109927889 A CN109927889 A CN 109927889A
- Authority
- CN
- China
- Prior art keywords
- strut
- main landing
- landing gear
- military aircraft
- aircraft main
- 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
Links
Landscapes
- General Details Of Gearings (AREA)
Abstract
The invention discloses a kind of military aircraft main landing gears, including baffle, the outer surface of the baffle is fixedly installed with inserted camera, the outer surface lower end of the baffle is provided with load pillar, the outer surface lower end of the load pillar is provided with water pipe, one end of the water pipe is provided with hose nozzle, the outer surface lower end of the water pipe is provided with strut support, the outer surface lower end of the strut support is provided with shock strut, the outer surface lower end of the shock strut is provided with rocker arm, the outer surface side of the rocker arm is provided with lubrication hydraulic fluid port, the outer surface of the lubrication hydraulic fluid port is provided with tyre framework, the outer surface of the tyre framework is provided with tire.A kind of military aircraft main landing gear of the present invention, equipped with inserted camera, lubrication hydraulic fluid port and water pipe, bottom conditions can be observed when body operates, it is convenient to be maintained to internal bearings and gear, it also helps and reaches cooling effect to tire, bring better prospect of the application.
Description
Technical field
The present invention relates to undercarriage field, in particular to a kind of military aircraft main landing gear.
Background technique
Undercarriage is a kind of machine depressurized using thermal energy conversion, when damper, which is impacted, to be compressed, the effect of air
It is equivalent to spring, storing energy.And oil liquid passes through aperture with high speed, absorbs a large amount of Impact energies, they are changed into
Thermal energy steadily gets off quickly after making aircraft impact, will not jolt more than, all install on existing aircraft, has obtained wide
General use can cause the damage of ambiguity when the overheat of tire in use cannot cool down in time to the surface of tire；It is existing
Undercarriage there are certain drawbacks when in use, contacted with ground friction firstly, declining undercarriage after traveling and can generate height
Temperature cannot such as be handled in time, and the damage of ambiguity can be caused to outer surface of tire, and it is certain unfavorable to cause, secondly, undercarriage
Lower end idler wheel cannot add in time when often operating at required lubricating oil, substantially reduce action efficiency, in addition, under undercarriage
Square visual field blank cannot be observed in time, be unfavorable for people's use, certain influence is brought to the use process of people, for this purpose,
It is proposed that a kind of military aircraft main landing gear.
Summary of the invention
The main purpose of the present invention is to provide a kind of military aircraft main landing gears, can effectively solve in background technique
Problem.
To achieve the above object, the technical scheme adopted by the invention is as follows:
A kind of military aircraft main landing gear, including baffle, the outer surface of the baffle is fixedly installed with inserted camera, described
The outer surface lower end of baffle is provided with load pillar, and the outer surface lower end of the load pillar is provided with water pipe, the water pipe
One end is provided with hose nozzle, and the outer surface lower end of the water pipe is provided with strut support, the outer surface lower end setting of the strut support
There is shock strut, the outer surface lower end of the shock strut is provided with rocker arm, and the outer surface side of the rocker arm is provided with lubrication
The outer surface of hydraulic fluid port, the lubrication hydraulic fluid port is provided with tyre framework, and the outer surface of the tyre framework is provided with tire, described to hold
The outer surface side of power pillar is provided with retraction jack, and outer surface one end of the retraction jack is provided with upper hook,
The outer surface lower end of the upper hook is provided with connecting rod, and lower end is provided with strut in the middle part of the outer surface of the connecting rod, institute
The outer surface side for stating connecting rod is provided with shaft, and the outer surface side upper end of the connecting rod is provided with link block, the company
The outer surface other side upper end of extension bar is provided with fixed bracket, and toggle, the torsion are provided between the shaft and strut support
Toggle shaft is provided in the middle part of the outer surface of the arm of force.
Preferably, strut is provided between the rocker arm and tyre framework, and the inner surface of strut is provided with rotary shaft, institute
The inner surface for stating lubrication hydraulic fluid port is provided with pipeline.
Preferably, protective cover is provided between the inserted camera and baffle, the shape of protective cover is circle, described
The inner surface of shock strut is provided with oil liquid.
Preferably, the outer surface of the tire is provided with screw thread, and the outer surface of the link block is provided with screw hole, screw
The quantity in hole is several groups.
Preferably, the inner surface of the retraction jack is provided with spring, and the outer surface of the shaft is provided with screw, institute
The inner surface for stating tyre framework is provided with strut, and the quantity of strut is several groups.
Preferably, the outer surface of the hose nozzle is provided with shower nozzle, and the outer surface of shower nozzle is provided with hole,
The quantity of hole is several groups.
Compared with prior art, the invention has the following beneficial effects: a kind of military aircraft main landing gear, pass through setting
Water pipe can cool down in time to the surface of tire when tyre temperature is excessively high, to extend the service life of tire, pass through
The inserted camera being arranged can clearly observe the visual field below undercarriage, be conducive to people and intuitively find the problem, profit
The setting of lubricating oil mouth can be very good maintenance body agitator bearing, can prolong its service life, entire landing gear structure letter
Single, easy to operate, the effect used is more preferable relative to traditional approach.
Detailed description of the invention
Fig. 1 is a kind of overall structure diagram of military aircraft main landing gear of the present invention.
Fig. 2 is a kind of partial view of military aircraft main landing gear of the present invention.
Fig. 3 is the enlarged drawing of A in a kind of Fig. 2 of military aircraft main landing gear of the present invention.
Fig. 4 is the enlarged drawing of B in a kind of Fig. 2 of military aircraft main landing gear of the present invention.
In figure: 1, connecting rod；2, link block；3, upper hook；4, fixed bracket；5, retraction jack；6, baffle；7, it holds
Power pillar；8, shock strut；9, water pipe；10, hose nozzle；11, shaft；12, strut；13, toggle shaft；14, toggle；
15, strut support；16, rocker arm；17, tyre framework；18, tire；19, hydraulic fluid port is lubricated；20, inserted camera.
Specific embodiment
To be easy to understand the technical means, the creative features, the aims and the efficiencies achieved by the present invention, below with reference to
Specific embodiment, the present invention is further explained.
As shown in Figs 1-4, a kind of military aircraft main landing gear, including baffle 6, the outer surface of baffle 6 are fixedly installed with edge
Embedded camera 20, the outer surface lower end of baffle 6 are provided with load pillar 7, and the outer surface lower end of load pillar 7 is provided with water pipe
9, one end of water pipe 9 is provided with hose nozzle 10, and the outer surface lower end of water pipe 9 is provided with strut support 15, the outer surface of strut support 15
Lower end is provided with shock strut 8, and the outer surface lower end of shock strut 8 is provided with rocker arm 16, the outer surface side setting of rocker arm 16
There is lubrication hydraulic fluid port 19, the outer surface of lubrication hydraulic fluid port 19 is provided with tyre framework 17, and the outer surface of tyre framework 17 is provided with tire
18, the outer surface side of load pillar 7 is provided with retraction jack 5, and outer surface one end of retraction jack 5 is provided with upper extension
The outer surface lower end of hook 3, upper hook 3 is provided with connecting rod 1, and the lower section of connecting rod 1 is provided with strut 12, connecting rod 1 it is outer
Surface side is provided with shaft 11, and the outer surface side upper end of connecting rod 1 is provided with link block 2, and the outer surface of connecting rod 1 is another
Side upper end is provided with fixed bracket 4, and toggle 14, the outer surface middle part of toggle 14 are provided between shaft 11 and strut support 15
It is provided with toggle shaft 13.
It is provided with strut between rocker arm 16 and tyre framework 17, and the inner surface of strut is provided with rotary shaft, can make to prop up
The inner surface of bar rotation, lubrication hydraulic fluid port 19 is provided with pipeline, can be convenient lubricating oil and flows directly into shaft；Inserted camera 20
Protective cover is provided between baffle 6, the shape of protective cover is circle, and camera can be prevented by external impact, damping branch
The inner surface of column 8 is provided with oil liquid, and oil liquid can be allowed to be converted into thermal energy to reach damping effect in damping；Outside tire 18
Surface is provided with screw thread, can increase friction, and the outer surface of link block 2 is provided with screw hole, and the quantity of screw hole is several groups,
Component can be made more firm；The inner surface of retraction jack 5 is provided with spring, and undercarriage can effectively be made to withdraw fuselage bottom
The outer surface in portion, shaft 11 is provided with screw, can better fixed rotating shaft, the inner surface of tyre framework 17 is provided with strut,
The quantity of strut is several groups, can prevent wheel bone from being hit or being squeezed and cause to deform；The outer surface of hose nozzle 10 is provided with
Shower nozzle, and the outer surface of shower nozzle is provided with hole, the quantity of hole is several groups, more efficiently can give tire
Cooling.
It should be noted that the present invention is that a kind of military aircraft main landing gear when in use consolidates link block 2 with screw
It is scheduled on machine bottom, then by upper 3 connection fuselage bottom of hook, then bracket 4 will be fixed and fixed with fuselage, make undercarriage and fuselage more
Add firm, then link block 2, upper hook 3, fixed bracket 4 is connect with connecting rod 1 respectively, overall operation can be made to reach more
Good effect can be convenient undercarriage in this way and withdraw machine then with toggle 14 is connected between shaft 11 and toggle shaft 13
Body bottom, then make water from hose nozzle by the logical water pipe 9 of strut support 15 with the fixed toggle 14 of strut 12 and shaft 11
10 reach cooling to tire out, then baffle 6 is fixed on load pillar 7, and bottom uses shock strut 8 to connect again, subtract in this way
The deformation that will not cause load pillar 7 when shake because of undercarriage and collision on the ground, subsequently controls turning for wheel with rocker arm 16
Dynamic direction can be convenient fuselage control wheel and arbitrarily rotate and fuselage be driven to turn to, as wheel can be with when long-time uses
Lubricating oil is added by the lubrication hydraulic fluid port 19 in tyre framework 17 utilizes receipts after aircraft landing stops to tire offer maintenance
It puts action barrel 5 and withdraws fuselage bottom, it is more practical.
The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and the above embodiments and description only describe this
The principle of invention, without departing from the spirit and scope of the present invention, various changes and improvements may be made to the invention, these changes
Change and improvement all fall within the protetion scope of the claimed invention.The claimed scope of the invention by appended claims and its
Equivalent thereof.
Claims (6)
1. a kind of military aircraft main landing gear, including baffle (6), it is characterised in that: the outer surface of the baffle (6) is fixedly mounted
Have inserted camera (20), the outer surface lower end of the baffle (6) is provided with load pillar (7), the load pillar (7)
Outer surface lower end is provided with water pipe (9), and one end of the water pipe (9) is provided with hose nozzle (10), the outer surface of the water pipe (9)
Lower end is provided with strut support (15), and the outer surface lower end of the strut support (15) is provided with shock strut (8), the shock strut
(8) outer surface lower end is provided with rocker arm (16), and the outer surface side of the rocker arm (16) is provided with lubrication hydraulic fluid port (19), described
The outer surface of lubrication hydraulic fluid port (19) is provided with tyre framework (17), and the outer surface of the tyre framework (17) is provided with tire
(18), the outer surface side of the load pillar (7) is provided with retraction jack (5), the outer surface of the retraction jack (5)
One end is provided with upper hook (3), and the outer surface lower end of the upper hook (3) is provided with connecting rod (1), the connecting rod
(1) it is provided with below strut (12), the outer surface side of the connecting rod (1) is provided with shaft (11), the connecting rod (1)
Outer surface side upper end be provided with link block (2), the outer surface other side upper end of the connecting rod (1) is provided with fixed bracket
(4), it is provided with toggle (14) between the shaft (11) and strut support (15), is set in the middle part of the outer surface of the toggle (14)
It is equipped with toggle shaft (13).
2. a kind of military aircraft main landing gear according to claim 1, it is characterised in that: the rocker arm (16) and wheel tire bone
Strut is provided between frame (17), and the inner surface of strut is provided with rotary shaft, the inner surface setting of lubrication hydraulic fluid port (19)
There is pipeline.
3. a kind of military aircraft main landing gear according to claim 1, it is characterised in that: the inserted camera (20)
Protective cover is provided between baffle (6), the shape of protective cover is circle, and the inner surface of the shock strut (8) is provided with oil
Liquid.
4. a kind of military aircraft main landing gear according to claim 1, it is characterised in that: the outer surface of the tire (18)
It is provided with screw thread, the outer surface of the link block (2) is provided with screw hole, and the quantity of screw hole is several groups.
5. a kind of military aircraft main landing gear according to claim 1, it is characterised in that: the retraction jack (5)
Inner surface is provided with spring, and the outer surface of the shaft (11) is provided with screw, the inner surface setting of the tyre framework (17)
There is strut, the quantity of strut is several groups.
6. a kind of military aircraft main landing gear according to claim 1, it is characterised in that: the appearance of the hose nozzle (10)
Face is provided with shower nozzle, and the outer surface of shower nozzle is provided with hole, and the quantity of hole is several groups.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711365917.1A CN109927889A (en) | 2017-12-18 | 2017-12-18 | A kind of military aircraft main landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711365917.1A CN109927889A (en) | 2017-12-18 | 2017-12-18 | A kind of military aircraft main landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109927889A true CN109927889A (en) | 2019-06-25 |
Family
ID=66982682
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711365917.1A Pending CN109927889A (en) | 2017-12-18 | 2017-12-18 | A kind of military aircraft main landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109927889A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112061382A (en) * | 2020-09-11 | 2020-12-11 | 中航飞机起落架有限责任公司 | Frame formula undercarriage brake hose connection structure |
| CN112373679A (en) * | 2020-10-15 | 2021-02-19 | 南京航空航天大学 | Aircraft undercarriage tire abrasionproof decreases device |
-
2017
- 2017-12-18 CN CN201711365917.1A patent/CN109927889A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112061382A (en) * | 2020-09-11 | 2020-12-11 | 中航飞机起落架有限责任公司 | Frame formula undercarriage brake hose connection structure |
| CN112373679A (en) * | 2020-10-15 | 2021-02-19 | 南京航空航天大学 | Aircraft undercarriage tire abrasionproof decreases device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109927889A (en) | A kind of military aircraft main landing gear | |
| CN110056603A (en) | A kind of external mounting type planetary roller screw-rubber composite vibration reducing device | |
| CN103016275A (en) | Sliding bearing type wind driven generator unit yaw system and friction plate replacement method | |
| CN203356979U (en) | Pin dismounting device | |
| CN203542523U (en) | Novel pumping unit crank pin bush extractor | |
| CN205225925U (en) | Buffering rack and pinion jar with recovered energy | |
| CN209818207U (en) | Yaw brake system of wind turbine generator | |
| CN210218526U (en) | Rubber friction shock absorber with adjustable structure | |
| CN207547007U (en) | A kind of powdery paints filter | |
| CN103591079B (en) | Novel hydraulic cylinder | |
| CN206555413U (en) | A kind of automobile gearbox input shaft end lid arrangement | |
| CN204512282U (en) | A kind of two rod hydraulic damper | |
| CN203836184U (en) | Combination piston covered with rubber | |
| CN206517210U (en) | A kind of maximum type fixed seat | |
| CN205034353U (en) | Rotor system fluid pressure type subtracts puts grease squirt for attenuator | |
| CN203809413U (en) | Air cylinder lubrication system | |
| CN208592786U (en) | A kind of horizontal assembly tool of Self-lubricating bearing bush | |
| CN205310153U (en) | Beam -pumping unit bush takes out specialized tool | |
| CN207682306U (en) | Armored vehicle hydraulic damper dismantles puller | |
| CN207388884U (en) | A kind of sparrow hawk formula current collecting equipment special type hydraulic spring grease cup combined power system | |
| CN204328423U (en) | There is the disc of atomizing component and dampening assembly | |
| CN201941851U (en) | Integral turnover device for engine hood of construction machinery | |
| CN206159158U (en) | Upset hydro -cylinder of auttombilism room | |
| CN203627399U (en) | Novel hydraulic oil cylinder | |
| CN204512276U (en) | A kind of unidirectional tension hydraulic damper |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190625 |