CN108995795A - A kind of aviation undercarriage with buffering effect - Google Patents
A kind of aviation undercarriage with buffering effect Download PDFInfo
- Publication number
- CN108995795A CN108995795A CN201810756288.3A CN201810756288A CN108995795A CN 108995795 A CN108995795 A CN 108995795A CN 201810756288 A CN201810756288 A CN 201810756288A CN 108995795 A CN108995795 A CN 108995795A
- Authority
- CN
- China
- Prior art keywords
- fixedly connected
- main support
- support rod
- spring
- buffering effect
- 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
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses a kind of aviation undercarriage with buffering effect, including bracket, the lower rotation of the bracket is connected with main support rod, and the inside of main support rod offers dashpot, the first spring is fixedly connected at the top of the dashpot inner wall, and the bottom end of the first spring is fixedly connected with motion bar, and the present invention relates to technical field of aerospace.The aviation undercarriage with buffering effect; second spring is fixedly connected to by the bottom of motion bar surface two sides; reduce the impact force in aircraft dropping process; the 4th spring is fixedly connected between surface by fixed link and the bottom positioned at loose slot inner wall and the bottom of movable block; with buffer function; protect the components of interior of aircraft; prolong the service life; contraction pole is rotatably connected to by the side of cradle top; and the side rotation connection of the bottom end and main support rod surface of contraction pole; structure is simple, can reduce the weight of aircraft itself.
Description
Technical field
The present invention relates to technical field of aerospace, specially a kind of aviation undercarriage with buffering effect.
Background technique
Main landing gear, which is aircraft, to be parked on ground, slides, landing when, rise: bearing the undercarriage of Main Load in dropping control device
Component.In preceding two-point undercarriage, refers to and refer to and be mounted in tail wheel type landing gear mounted in the subsequent undercarriage of the center of gravity of airplane
Undercarriage before the center of gravity of airplane.Refer to forward and backward undercarriage in bicycle gear, main landing gear by hydraulic actuation, and to
Wheel cabin is inside taken in, once takeing in, main undercarriage unit is just completely enclosed by the hatch door of radome fairing and hydraulic actuation that pillar connects,
Each device keeps undercarriage in locked position without hydraulic by a pressurized strut actuation, and by a mechanical linkage
It helps, main-wheel door pressurized strut is by a sequence mechanism controls, when undercarriage puts down or takes in completely, closes hatch door.
Present undercarriage has a single function since structure is simple, and undercarriage is caused to be not achieved in use very
Good damping effect, makes to generate biggish impact force in aircraft dropping process, damage to aircraft components, influence using the longevity
Life, and unreasonable structural design, installing and dismounting are complicated.
Summary of the invention
In view of the deficiencies of the prior art, the present invention provides a kind of aviation undercarriage with buffering effect, solves winged
Machine landing gear structure is simple, the unconspicuous problem of damping effect.
In order to achieve the above object, the present invention is achieved by the following technical programs: a kind of aviation with buffering effect
Undercarriage, including bracket, the lower rotation of the bracket is connected with main support rod, and the inside of main support rod offers buffering
Slot is fixedly connected with the first spring at the top of the dashpot inner wall, and the bottom end of the first spring is fixedly connected with motion bar,
The bottom end of the motion bar is through dashpot and main support rod and the outside for extending to main support rod, the bottom of the main support rod
It is fixedly connected with connecting plate, and the two sides of connecting plate bottom are fixedly connected to fixed block, the inside of the fixed block opens up
There is loose slot, and be fixedly connected with fixed link between the top and bottom of loose slot inner wall, and the surface sliding of fixed link
It is connected with movable block, the inside of the fixed block and two sides for being located at loose slot offer sliding groove, the table of the fixed link
Face and be located at loose slot inner wall top and movable block top between be fixedly connected with third spring, the surface of the fixed link
And it is located between the bottom of loose slot inner wall and the bottom of movable block and is fixedly connected with the 4th spring.
Preferably, the side of the movable block is fixedly connected with wheel shaft, and the surface pivots of wheel shaft are connected with wheel.
Preferably, the lower rotation on the main support rod surface is connected with first connecting rod, and one at the top of the connecting plate
Side is rotatably connected to the second connecting rod, and is turned between one end of first connecting rod and one end of the second connecting rod by connector
Dynamic connection.
Preferably, the bottom of motion bar surface two sides is fixedly connected to second spring, and the one of second spring
End is fixedly connected with connector.
Preferably, the side of the cradle top is rotatably connected to contraction pole, and the bottom end of contraction pole and main support rod
The side on surface is rotatablely connected.
Preferably, the lower rotation of the bracket is connected with the first rotating bar, the top of main support rod surface side
It is rotatably connected to the second rotating bar, one end of first rotating bar and one end rotation connection of the second rotating bar.
Beneficial effect
The present invention provides a kind of aviation undercarriage with buffering effect.Have it is following the utility model has the advantages that
(1), aviation undercarriage with buffering effect, by between one end of first connecting rod and one end of the second connecting rod
It is rotatablely connected by connector, the bottom of motion bar surface two sides is fixedly connected to second spring, solves undercarriage
Structure is simple, has a single function, the unconspicuous problem of damping effect, reduces the impact force in aircraft dropping process, improves people
Comfort level when seating.
(2), the aviation undercarriage with buffering effect, the surface by fixed link and the top positioned at loose slot inner wall
Be fixedly connected with third spring between the top of movable block, the surface of the fixed link and be located at the bottom of loose slot inner wall with
The 4th spring is fixedly connected between the bottom of movable block, impact force when aircraft being made to fall reduces, and protects the zero of interior of aircraft
Component prolongs the service life.
(3), the aviation undercarriage with buffering effect, is rotatably connected to contraction pole by the side of cradle top, and
And the side rotation connection of the bottom end and main support rod surface of contraction pole, contraction pole is flexible to drive main support rod rotation, by wheel
Wheel cabin is taken in, structure is simple, and the weight for reducing aircraft itself.
Detailed description of the invention
Fig. 1 is the cross-sectional view of structure of the invention；
Fig. 2 is the partial enlarged view in Fig. 1 of the present invention at A；
Fig. 3 is the partial enlarged view in Fig. 1 of the present invention at B.
In figure: 1 bracket, 2 main support rods, 3 dashpots, 4 first springs, 5 motion bars, 6 connecting plates, 7 fixed blocks, 8 activities
Slot, 9 fixed links, 10 movable blocks, 11 sliding grooves, 12 third springs, 13 the 4th springs, 14 wheel shafts, 15 wheels, 16 first connections
Bar, 17 second connecting rods, 18 connectors, 19 second springs, 20 contraction poles, 21 first rotating bars, 22 second rotating bars.
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.
Fig. 1-3 is please referred to, the present invention provides a kind of technical solution: a kind of aviation undercarriage with buffering effect, including
Bracket 1, the lower rotation of bracket 1 are connected with the first rotating bar 21, and main support rod is rotatably connected to second at the top of 2 surface side
One end of rotating bar 22, one end of the first rotating bar 21 and the second rotating bar 22 is rotatablely connected, connecting bracket 1 and main support rod 2,
Keep structure more firm, the side at 1 top of bracket is rotatably connected to contraction pole 20, and contraction pole 20 drives main support rod 2 to rotate, makes machine
Wheel 15 can take in wheel cabin, and the side rotation connection on 2 surface of the bottom end of contraction pole 20 and main support rod, the bottom of bracket 1
It is rotatably connected to main support rod 2, the lower rotation on 2 surface of main support rod is connected with first connecting rod 16, and the one of 6 top of connecting plate
Side is rotatably connected to the second connecting rod 17, and passes through company between one end of first connecting rod 16 and one end of the second connecting rod 17
Fitting 18 is rotatablely connected, and the inside of main support rod 2 offers dashpot 3, and the is fixedly connected at the top of 3 inner wall of dashpot
One spring 4, and the bottom end of the first spring 4 is fixedly connected with motion bar 5, and the bottom of 5 surface two sides of motion bar is fixedly connected with
There is second spring 19, and one end of second spring 19 is fixedly connected with connector 18, dashpot 3 is run through in the bottom end of motion bar 5
With main support rod 2 and the outside of main support rod 2 is extended to, the bottom of main support rod 2 is fixedly connected with connecting plate 6, and connects
The two sides of 6 bottom of plate are fixedly connected to fixed block 7, and the inside of fixed block 7 offers loose slot 8, and 8 inner wall of loose slot
Fixed link 9 is fixedly connected between top and bottom, and the surface of fixed link 9 slidably connects movable block 10, movable block 10
Side be fixedly connected with wheel shaft 14, and the surface pivots of wheel shaft 14 are connected with wheel 15, and the inside of fixed block 7 and being located at is lived
The two sides of dynamic slot 8 offer sliding groove 11, the surface of fixed link 9 and top and the movable block 10 for being located at 8 inner wall of loose slot
Third spring 12, the surface of fixed link 9 and bottom and the movable block 10 for being located at 8 inner wall of loose slot are fixedly connected between top
The 4th spring 13 is fixedly connected between bottom, buffer structure at three makes aircraft fall more stable.
In use, contraction pole 20 stretches out, drive main support rod 2 along rotating clockwise, while the first rotating bar 21 and second
Rotating bar 22 turn to it is on the same line, wheel 15 contact ground after, complete aircraft by the structure in fixed block 7
First time damping, connecting plate 6 move upwards, and reduce angle between first connecting rod 16 and the second connecting rod 17, second spring
19 are stretched, and complete second of damping, and motion bar 5, which moves upwards, squeezes the first spring 4, complete third time damping.
It should be noted that, in this document, relational terms such as first and second and the like are used merely to a reality
Body or operation are distinguished with another entity or operation, are deposited without necessarily requiring or implying between these entities or operation
In any actual relationship or order or sequence.Moreover, the terms "include", "comprise" or its any other variant are intended to
Non-exclusive inclusion, so that the process, method, article or equipment including a series of elements is not only wanted including those
Element, but also including other elements that are not explicitly listed, or further include for this process, method, article or equipment
Intrinsic element.
It although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with
A variety of variations, modification, replacement can be carried out to these embodiments without departing from the principles and spirit of the present invention by understanding
And modification, the scope of the present invention is defined by the appended.
Claims (6)
1. a kind of aviation undercarriage with buffering effect, including bracket (1), it is characterised in that: the bottom of the bracket (1) turns
It is dynamic to be connected with main support rod (2), and the inside of main support rod (2) offers dashpot (3), dashpot (3) inner wall
Top is fixedly connected with the first spring (4), and the bottom end of the first spring (4) is fixedly connected with motion bar (5), the motion bar
(5) bottom end is through dashpot (3) and main support rod (2) and the outside for extending to main support rod (2), the main support rod (2)
Bottom be fixedly connected with connecting plate (6), and the two sides of connecting plate (6) bottom are fixedly connected to fixed block (7), described solid
The inside for determining block (7) offers loose slot (8), and is fixedly connected with fixation between the top and bottom of loose slot (8) inner wall
Bar (9), and the surface of fixed link (9) slidably connects movable block (10), the inside of the fixed block (7) and is located at loose slot
(8) two sides offer sliding groove (11), the surface of the fixed link (9) and top and the work for being located at loose slot (8) inner wall
Be fixedly connected between the top of motion block (10) third spring (12), the surface of the fixed link (9) and be located at loose slot (8) in
The 4th spring (13) is fixedly connected between the bottom of wall and the bottom of movable block (10).
2. a kind of aviation undercarriage with buffering effect according to claim 1, it is characterised in that: the movable block
(10) side is fixedly connected with wheel shaft (14), and the surface pivots of wheel shaft (14) are connected with wheel (15).
3. a kind of aviation undercarriage with buffering effect according to claim 1, it is characterised in that: the main support rod
(2) lower rotation on surface is connected with first connecting rod (16), and the side at the top of the connecting plate (6) is rotatably connected to the second company
Extension bar (17), and rotated between one end of first connecting rod (16) and one end of the second connecting rod (17) by connector (18)
Connection.
4. a kind of aviation undercarriage with buffering effect according to claim 1, it is characterised in that: the motion bar
(5) bottom of surface two sides is fixedly connected to second spring (19), and one end of second spring (19) and connector (18)
It is fixedly connected.
5. a kind of aviation undercarriage with buffering effect according to claim 1, it is characterised in that: the bracket (1)
The side at top is rotatably connected to contraction pole (20), and the side on the bottom end of contraction pole (20) and main support rod (2) surface turns
Dynamic connection.
6. a kind of aviation undercarriage with buffering effect according to claim 1, it is characterised in that: the bracket (1)
Lower rotation be connected with the first rotating bar (21), be rotatably connected to second turn at the top of main support rod (2) the surface side
Lever (22), one end of first rotating bar (21) and one end rotation connection of the second rotating bar (22).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810756288.3A CN108995795A (en) | 2018-07-11 | 2018-07-11 | A kind of aviation undercarriage with buffering effect |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810756288.3A CN108995795A (en) | 2018-07-11 | 2018-07-11 | A kind of aviation undercarriage with buffering effect |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108995795A true CN108995795A (en) | 2018-12-14 |
Family
ID=64599714
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810756288.3A Pending CN108995795A (en) | 2018-07-11 | 2018-07-11 | A kind of aviation undercarriage with buffering effect |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108995795A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110143244A (en) * | 2019-06-26 | 2019-08-20 | 江西制造职业技术学院 | A kind of wheeled mobile robot |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0976947A2 (en) * | 1998-07-29 | 2000-02-02 | Continental Aktiengesellschaft | Air spring strut and manufacturing thereof |
| GB0516030D0 (en) * | 2005-08-04 | 2005-09-14 | Messier Dowty Ltd | Landing gear |
| US20170217574A1 (en) * | 2016-01-29 | 2017-08-03 | Daniel Roger Dufault | Suspension For Aircraft Tail Wheel |
| CN107914869A (en) * | 2017-12-07 | 2018-04-17 | 佛山市神风航空科技有限公司 | Beneficial to the aerial photography aircraft undercarriage for stablizing landing |
| CN107985565A (en) * | 2017-12-07 | 2018-05-04 | 佛山市神风航空科技有限公司 | The unmanned plane undercarriage of taking photo by plane of dual shock absorption |
| CN207417136U (en) * | 2017-11-02 | 2018-05-29 | 白辰飞 | A kind of buffer protection device of unmanned plane |
| CN108216589A (en) * | 2017-12-15 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of undercarriage leg contracting mechanism |
| CN207580158U (en) * | 2017-12-19 | 2018-07-06 | 江西冠一通用飞机有限公司 | A kind of navigation undercarriage |
-
2018
- 2018-07-11 CN CN201810756288.3A patent/CN108995795A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0976947A2 (en) * | 1998-07-29 | 2000-02-02 | Continental Aktiengesellschaft | Air spring strut and manufacturing thereof |
| GB0516030D0 (en) * | 2005-08-04 | 2005-09-14 | Messier Dowty Ltd | Landing gear |
| US20170217574A1 (en) * | 2016-01-29 | 2017-08-03 | Daniel Roger Dufault | Suspension For Aircraft Tail Wheel |
| CN207417136U (en) * | 2017-11-02 | 2018-05-29 | 白辰飞 | A kind of buffer protection device of unmanned plane |
| CN107914869A (en) * | 2017-12-07 | 2018-04-17 | 佛山市神风航空科技有限公司 | Beneficial to the aerial photography aircraft undercarriage for stablizing landing |
| CN107985565A (en) * | 2017-12-07 | 2018-05-04 | 佛山市神风航空科技有限公司 | The unmanned plane undercarriage of taking photo by plane of dual shock absorption |
| CN108216589A (en) * | 2017-12-15 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of undercarriage leg contracting mechanism |
| CN207580158U (en) * | 2017-12-19 | 2018-07-06 | 江西冠一通用飞机有限公司 | A kind of navigation undercarriage |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110143244A (en) * | 2019-06-26 | 2019-08-20 | 江西制造职业技术学院 | A kind of wheeled mobile robot |
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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 | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20181214 |