CN107380408A - A kind of aircraft landing drag-type device - Google Patents
A kind of aircraft landing drag-type device Download PDFInfo
- Publication number
- CN107380408A CN107380408A CN201710589850.3A CN201710589850A CN107380408A CN 107380408 A CN107380408 A CN 107380408A CN 201710589850 A CN201710589850 A CN 201710589850A CN 107380408 A CN107380408 A CN 107380408A
- Authority
- CN
- China
- Prior art keywords
- aircraft landing
- hydraulic cylinder
- branch layer
- pole
- dilatory
- 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
-
- 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
- B64C25/42—Arrangement or adaptation of brakes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tires In General (AREA)
Abstract
The invention discloses a kind of aircraft landing drag-type device, including aircraft landing support bar, connecting pole and pull bar, one end of the hydraulic cylinder is connected with pole, and the other end of hydraulic cylinder is connected with dilatory plate, the upper end of the pole is connected with aircraft landing support bar, the dilatory plate includes upper branch layer and lower branch layer, and the lower end of the upper branch layer is provided with lower branch layer, and the upper end of the connecting pole is provided with pull bar.The present invention is scientific and reasonable for structure, it is safe and convenient to use, aircraft landing mode is improved, there is provided hydraulic cylinder and dilatory plate, the flexible of dilatory plate is controlled using hydraulic cylinder, shifted by dilatory plate and decompose the own wt of fuselage, dilatory plate is rubbed on (or and deck) with ground, aircraft can be made to carry out dilatory landing, the time of aircraft landing can be effectively reduced, shorten landing distance, reduce maintenance frequency, the design is not only simple in structure, easy for operation, while also improves the efficiency of aircraft landing.
Description
Technical field
The present invention relates to aircraft landing drag-type device technical field, specially a kind of aircraft landing drag-type device.
Background technology
Aircraft, refer to produce the thrust advanced or pulling force by power set, lift is produced by the fixation wing of fuselage, big
The airborne vehicle for overweighting air of flight in gas-bearing formation, it is one kind of Fixed-Wing, and most common one kind, another kind are solid
It is aerodone to determine wing airborne vehicle, and the engine type that aircraft uses according to it can be divided into jet airplane and propeller aeroplane again,
Existing aircraft technology landing is to slow down to carry out fall-retarding with the brake of aircraft wheel hub by the drag parachute of airplane tail group, is caused
The time length of landing, landing distance are elongated, and efficiency is low etc..
The content of the invention
The present invention provides a kind of aircraft landing drag-type device, can effectively solve to propose in above-mentioned background technology existing
Aircraft technology landing is to slow down to carry out fall-retarding with the brake of aircraft wheel hub by the drag parachute of airplane tail group, causes landing
The problem of time is grown, and landing distance is elongated, and efficiency is low.
To achieve the above object, the present invention provides following technical scheme：A kind of aircraft landing drag-type device, including aircraft
Land support bar, pole, hydraulic cylinder, dilatory plate, connecting pole and pull bar, and one end of the hydraulic cylinder is connected with pole, and hydraulic pressure
The other end of cylinder is connected with dilatory plate, and the upper end of the pole is connected with aircraft landing support bar, and the dilatory plate includes upper branch
Layer and lower branch layer, the lower end of the upper branch layer is provided with lower branch layer, and upper branch layer upper end is set close to the side opening position of hydraulic cylinder
Connecting pole is equipped with, the upper end of the connecting pole is provided with pull bar.
Preferably, the bottom of the lower branch layer is flank.
Preferably, the pole and dilatory plate are connected by being rotatablely connected seat with hydraulic cylinder.
Preferably, one end of the pull bar is fixed with connecting pole by column sleeve, and the other end is connected with airframe.
Preferably, the dilatory plate 4 is a kind of component of abrasive rubber material.
Compared with prior art, beneficial effects of the present invention：The present invention is scientific and reasonable for structure, safe and convenient to use, to flying
Machine landing modes are improved, and there is provided hydraulic cylinder and dilatory plate, the flexible of dilatory plate is controlled using hydraulic cylinder, by dragging
Arm-tie is shifted and decomposes the own wt of fuselage, and dilatory plate is rubbed on (or and deck) with ground, you can is dragged aircraft
Landing is drawn, can effectively reduce time of aircraft landing, shortens landing distance, reduces maintenance frequency, the design not only structure
Simply, it is easy for operation, while also improve the efficiency of aircraft landing.
Brief description of the drawings
Accompanying drawing is used for providing a further understanding of the present invention, and a part for constitution instruction, the reality with the present invention
Apply example to be used to explain the present invention together, be not construed as limiting the invention.
In the accompanying drawings：
Fig. 1 is the structural representation of the present invention；
Label in figure：1st, aircraft landing support bar；2nd, pole；3rd, hydraulic cylinder；4th, plate is drawn；5th, upper branch layer；6th, lower branch layer；
7th, connecting pole；8th, pull bar.
Embodiment
The preferred embodiments of the present invention are illustrated below in conjunction with accompanying drawing, it will be appreciated that described herein preferred real
Apply example to be merely to illustrate and explain the present invention, be not intended to limit the present invention.
Embodiment：As shown in figure 1, the present invention provides a kind of technical scheme, a kind of aircraft landing drag-type device, including fly
Machine landing support bar 1, pole 2, hydraulic cylinder 3, dilatory plate 4, connecting pole 7 and pull bar 8, one end of hydraulic cylinder 3 are connected with pole 2,
And the other end of hydraulic cylinder 3 is connected with dilatory plate 4, the upper end of pole 2 is connected with aircraft landing support bar 1, draws plate 4 including upper
Branch layer 5 and lower branch layer 6, the lower end of upper branch layer 5 is provided with lower branch layer 6, and the upper upper end of branch layer 5 is close to a side position of hydraulic cylinder 3
Place is provided with connecting pole 7, and the upper end of connecting pole 7 is provided with pull bar 8.
In order to increase the frictional force of dilatory plate 4 and ground, in the present embodiment, it is preferred that the bottom of lower branch layer 6 is screw thread
Face.
In order to realize the contraction of dilatory plate 4 by hydraulic cylinder 3, in the present embodiment, it is preferred that pole 2 and dilatory plate 4 are logical
Rotation connection seat is crossed to be connected with hydraulic cylinder 3.
In order to improve the tightness that towed equipment is connected with airframe, in the present embodiment, it is preferred that one end of pull bar 8
Fixed with connecting pole 7 by column sleeve, the other end is connected with airframe.
In order to increase the service life of dilatory plate 4, in the present embodiment, it is preferred that dilatory plate 4 is a kind of abrasive rubber material
Component.
The operation principle and process for using of the present invention：Pole 2 and dilatory plate 4 are connected by being rotatablely connected seat with hydraulic cylinder 3
Connect, the upper end of pole 2 is connected with aircraft landing support bar 1, and dilatory plate 4 includes upper branch layer 5 and lower branch layer 6, the lower end of upper branch layer 5
Lower branch layer 6 is provided with, the bottom of lower branch layer 6 is flank, and the upper upper end of branch layer 5 is set close to the side opening position of hydraulic cylinder 3
There is connecting pole 7, one end and the connecting pole 7 of pull bar 8 are fixed by column sleeve, and the other end is connected with airframe, dilatory in order to improve
The tightness that device is connected with airframe, there is provided hydraulic cylinder 3 and dilatory plate 4, and dilatory plate 4 is controlled using hydraulic cylinder 3
It is flexible, shifted by dilatory plate 4 and decompose the own wt of fuselage, dilatory plate is rubbed on (or and deck) with ground, you can
Aircraft is carried out dilatory landing, can effectively reduce the time of aircraft landing, shorten landing distance, reduce maintenance frequency, this
Design is not only simple in structure, easy for operation, while also improves the efficiency of aircraft landing.
Finally it should be noted that：The preferred embodiment of the present invention is the foregoing is only, is not intended to limit the invention, to the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, and for those skilled in the art, it still can be with
Technical scheme described in foregoing embodiments is modified, or equivalent substitution is carried out to which part technical characteristic.It is all
Within the spirit and principles in the present invention, any modification, equivalent substitution and improvements made etc., it should be included in the guarantor of the present invention
Within the scope of shield.
Claims (5)
1. a kind of aircraft landing drag-type device, including aircraft landing support bar (1), pole (2), hydraulic cylinder (3), dilatory plate
(4), connecting pole (7) and pull bar (8), it is characterised in that：One end of the hydraulic cylinder (3) is connected with pole (2), and hydraulic cylinder
(3) the other end is connected with dilatory plate (4), and the upper end of the pole (2) is connected with aircraft landing support bar (1), described dilatory
Plate (4) includes upper branch layer (5) and lower branch layer (6), and the lower end of the upper branch layer (5) is provided with lower branch layer (6), and upper branch layer (5)
Upper end is provided with connecting pole (7) close to the side opening position of hydraulic cylinder (3), and the upper end of the connecting pole (7) is provided with pull bar
(8)。
A kind of 2. aircraft landing drag-type device according to claim 1, it is characterised in that：The bottom of the lower branch layer (6)
Hold as flank.
A kind of 3. aircraft landing drag-type device according to claim 1, it is characterised in that：The pole (2) and dilatory
Plate (4) is connected by being rotatablely connected seat with hydraulic cylinder (3).
A kind of 4. aircraft landing drag-type device according to claim 1, it is characterised in that：One end of the pull bar (8)
Fixed with connecting pole (7) by column sleeve, the other end is connected with airframe.
A kind of 5. aircraft landing drag-type device according to claim 1, it is characterised in that：The dilatory plate (4) is one
The component of kind abrasive rubber material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710589850.3A CN107380408A (en) | 2017-07-19 | 2017-07-19 | A kind of aircraft landing drag-type device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710589850.3A CN107380408A (en) | 2017-07-19 | 2017-07-19 | A kind of aircraft landing drag-type device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107380408A true CN107380408A (en) | 2017-11-24 |
Family
ID=60339329
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710589850.3A Pending CN107380408A (en) | 2017-07-19 | 2017-07-19 | A kind of aircraft landing drag-type device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107380408A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216598A (en) * | 2018-01-02 | 2018-06-29 | 晨龙飞机（荆门）有限公司 | A kind of aircraft braking device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1099858B (en) * | 1953-01-30 | 1961-02-16 | George Herbert Dowty | Braking device provided on the aircraft chassis or fuselage |
| CN2355937Y (en) * | 1998-10-20 | 1999-12-29 | 马玉希 | Emergency braking system for transport device |
| CN103121444A (en) * | 2013-01-24 | 2013-05-29 | 韩丰收 | Braking device dragging on ground |
| US20140191078A1 (en) * | 2013-01-08 | 2014-07-10 | The Boeing Company | Airplane Emergency Supplemental Braking System And Method |
| US9487190B1 (en) * | 2015-02-10 | 2016-11-08 | Alfredo Alvarado | Emergency brake system for vehicles and aircraft |
-
2017
- 2017-07-19 CN CN201710589850.3A patent/CN107380408A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1099858B (en) * | 1953-01-30 | 1961-02-16 | George Herbert Dowty | Braking device provided on the aircraft chassis or fuselage |
| CN2355937Y (en) * | 1998-10-20 | 1999-12-29 | 马玉希 | Emergency braking system for transport device |
| US20140191078A1 (en) * | 2013-01-08 | 2014-07-10 | The Boeing Company | Airplane Emergency Supplemental Braking System And Method |
| CN103121444A (en) * | 2013-01-24 | 2013-05-29 | 韩丰收 | Braking device dragging on ground |
| US9487190B1 (en) * | 2015-02-10 | 2016-11-08 | Alfredo Alvarado | Emergency brake system for vehicles and aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216598A (en) * | 2018-01-02 | 2018-06-29 | 晨龙飞机（荆门）有限公司 | A kind of aircraft braking device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20171124 |
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| RJ01 | Rejection of invention patent application after publication |