CN106516087A - Novel high-strength high-compactness lightweight aircraft landing gear - Google Patents
Novel high-strength high-compactness lightweight aircraft landing gear Download PDFInfo
- Publication number
- CN106516087A CN106516087A CN201610921124.2A CN201610921124A CN106516087A CN 106516087 A CN106516087 A CN 106516087A CN 201610921124 A CN201610921124 A CN 201610921124A CN 106516087 A CN106516087 A CN 106516087A
- Authority
- CN
- China
- Prior art keywords
- kinematic chain
- connecting rod
- main carrier
- carrier bar
- lightweight
- 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
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- 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
-
- 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
-
- 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
- B64C2025/345—Multi-wheel bogies having one or more steering axes
Abstract
The invention discloses a novel high-strength high-compactness lightweight aircraft landing gear. The novel high-strength high-compactness lightweight aircraft landing gear comprises a driving system, a main bearing rod, a locking mechanism and a damping system, wherein the driving system is arranged on the upper part of the main bearing rod; the main bearing rod is arranged between an aircraft fuselage and the damping system; the locking mechanism is arranged between the aircraft fuselage and the main bearing rod; the locking system comprises two identical kinematic chains which are not arranged in the same plane and respectively include a first kinematic chain and a second kinematic chain; the damping system is arranged on the lower part of the main bearing rod and comprises a damper and a pneumatic tire; and the lower end of the damper is connected with the pneumatic tire. According to the novel high-strength high-compactness lightweight aircraft landing gear disclosed by the invention, a conventional plane four-link landing gear is changed into a space four-link mechanism, and the reliable double-locking structures are a great contribution to the prior aircraft landing gear technology; and two sets of double-locking mechanisms are separated from each other and distributed symmetrically, and the safety of the aircraft landing gear is greatly improved by such a redundant design.
Description
Technical field
The present invention relates to field of airplane design, more particularly to a kind of novel high-strength high intense lightweight aircraft takeoffs and landings
Frame.
Background technology
Undercarriage is the important safety feature of aircraft, be take off, land, ground taxi and master when parking
The load-carrying member wanted, undercarriage will be absorbed and dissipate from the energy with ground shock during aircraft landing and sliding,
Safety during ensureing aircraft landing and slide, the performance level of undercarriage are directly connected to aircraft overall performance and flight peace
Entirely, always large aircraft manufacturing company endeavours one of improved key member both at home and abroad.
The undercarriage of early stage typically adopts lanar four rod mechanism, when undercarriage is put down completely, has just two
Connecting rod is in collinear position, and to ensure the operating attitude of undercarriage, and that the main carrier bar of undercarriage then carries that aircraft is subject to is exhausted
Most load, therefore, in the case where there is failure in undercarriage attitude holding structure, undercarriage just cisco unity malfunction,
Cause aircraft safety accident.
In order to increase the safety and reliability of aircraft, undercarriage designer both domestic and external updates its scheme,
However, these improvement projects belong to the derivative schemes of conventional planar double leval jib, it is impossible to thoroughly solve the root that traditional undercarriage is present
This defect.
The content of the invention
In order to solve problem of the prior art, a kind of novel high-strength high intense lightweight is embodiments provided
Undercarriage.The technical scheme is as follows：
A kind of novel high-strength high intense lightweight undercarriage, including drive system, main carrier bar, lockable mechanism
And shock mitigation system；
The drive system arrangements are on the top of the main carrier bar；
The main carrier bar is arranged between airframe and the shock mitigation system；
The lockable mechanism is arranged between airframe and the main carrier bar, including two identical non-co-planar arrangements
Kinematic chain, respectively the first kinematic chain and the second kinematic chain；
The shock mitigation system is arranged in the bottom of the main carrier bar, including amortisseur and pneumatic tire, the amortisseur
Lower end connect the pneumatic tire.
Alternatively, first kinematic chain and second kinematic chain are located at different planes, and first kinematic chain
It is symmetrical relative to the plane of movement of main carrier bar with the plane of second kinematic chain.
Alternatively, the kinematic chain include upper connecting rod, lower link, intermediate connecting rod, slide block, the first rotatable bearing pin, second
Rotatable bearing pin, the 3rd rotatable bearing pin, pitman pin；
The upper connecting rod, the intermediate connecting rod and the lower link are linked together by pitman pin；
The upper end of the upper connecting rod is connected with the first rotatable bearing pin for being fixed on airframe；The intermediate connecting rod passes through
The second rotatable bearing pin is connected with the slide block, and the slide block is moved back and forth along the axis direction of the main carrier bar；
The lower end of the lower link is connected with the pin shaft hole on the main carrier bar by the 3rd rotatable bearing pin.
Alternatively, the kinematic chain isKinematic chain, wherein P are sliding pair, and U is universal pair, and R is to rotate secondary；
The sliding pair represents that the slide block is moved back and forth up and down in the main carrier bar；
The universal pair includes the first universal pair, the second universal pair, the 3rd universal pair, and wherein described first universal pair is represented
The annexation of the upper connecting rod and airframe, second universal pair represent the connection of the intermediate connecting rod and the slide block
Relation, the 3rd universal pair represent the annexation of the lower link and the main carrier bar；
The rotation subtabulation shows that the upper connecting rod, the intermediate connecting rod and the lower link are hinged by the pitman pin
Together.
Alternatively, first kinematic chain and second kinematic chain are space four bar linkage mechanism, and the space four connects
Linkage includes airframe, main carrier bar, upper connecting rod and lower link, and the airframe is fix bar, the main carrier bar
For drive rod, the upper connecting rod is follower lever, and the lower link is the connecting rod for connecting the drive rod and the follower lever.
Alternatively, the space four bar linkage mechanism is Dual-locking structure.
The beneficial effect that technical scheme provided in an embodiment of the present invention is brought is：
1) traditional plane double leval jib undercarriage is changed to into space four bar linkage mechanism, and introduces Planar Mechanisms, relative to
Traditional undercarriage, two kinematic chains of introducing can carry out double kinematic link Dual-locking to primary load bearing bar respectively, even if wherein
After one kinematic chain failure, as another kinematic chain still has Dual-locking function, therefore, undercarriage remains to normal work
Make, the reliable Dual-locking structure of space double kinematic link of its redundancy is to existing undercarriage technology one big contribution.
2) two groups of dual-locking mechanisms are separated from each other, and symmetrical, and such Redundancy Design substantially increases aircraft takeoffs and landings
The structural strength of frame, rigidity and security of system, after main carrier bar with Dual-locking structure locking, undercarriage becomes in order to indeterminate
Truss structure, is provided with preferably vertical, laterally and longitudinally intensity, rigidity and bearing capacity.
3) in the state that undercarriage is reclaimed completely, main carrier bar is with the dual-locking mechanism of double kinematic link in same flat
In face, ultimate attainment structural compactness is obtained.
Description of the drawings
For the technical scheme being illustrated more clearly that in the embodiment of the present invention, below will be to making needed for embodiment description
Accompanying drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the present invention, for
For those of ordinary skill in the art, on the premise of not paying creative work, can be obtaining other according to these accompanying drawings
Accompanying drawing.
Fig. 1 a are that a kind of novel high-strength high intense lightweight undercarriage provided in an embodiment of the present invention is put completely
Under attitude schematic diagram；
Fig. 1 b are that a kind of novel high-strength high intense lightweight undercarriage provided in an embodiment of the present invention is received completely
The attitude schematic diagram for rising；
Fig. 2 is that a kind of structure of novel high-strength high intense lightweight undercarriage provided in an embodiment of the present invention is shown
It is intended to；
Fig. 3 is a kind of the first fortune of novel high-strength high intense lightweight undercarriage provided in an embodiment of the present invention
Dynamic chain I structural representations；
Fig. 4 a are the attitude schematic diagrams that undercarriage is put down completely when kinematic chain provided in an embodiment of the present invention fails；
Fig. 4 b are the attitude schematic diagrams that undercarriage is packed up completely when kinematic chain provided in an embodiment of the present invention fails.
Specific embodiment
For making the object, technical solutions and advantages of the present invention clearer, below in conjunction with accompanying drawing to embodiment party of the present invention
Formula is described in further detail.
A kind of novel high-strength high intense lightweight undercarriage is embodiments provided, referring to Fig. 1 a and figure
1b, including drive system 1, main carrier bar 2, lockable mechanism 3 and shock mitigation system 4.
Drive system 1 is arranged in the top of main carrier bar 2.
Main carrier bar 2 is arranged between airframe and shock mitigation system 4.
Lockable mechanism 3 is arranged between airframe and main carrier bar 2, including the motion of two identical non-co-planar arrangements
Chain, respectively the first kinematic chain I, the second kinematic chain II.
Shock mitigation system 4 is arranged in the bottom of main carrier bar 2, and including amortisseur and pneumatic tire, the connection of amortisseur lower end is filled
Air filled tyre.
In the present embodiment, referring to Fig. 2, the first kinematic chain I and the second kinematic chain II is located at different planes, and the first fortune
The plane of dynamic chain I and the second kinematic chain II is symmetrical relative to the plane of movement of main carrier bar 2.
In the present embodiment, referring to Fig. 3, kinematic chain includes that the first rotatable bearing pin 5, upper connecting rod 6, slide block 7, second can turn
Dynamic bearing pin 8, intermediate connecting rod 9, pitman pin 10, lower link 11, the 3rd rotatable bearing pin 12.
Upper connecting rod 6, intermediate connecting rod 9 and lower link 11 are linked together by pitman pin 10.
Intermediate connecting rod 9 is connected with slide block 7 by the second rotatable bearing pin 8, axis direction of the slide block 7 along main carrier bar 2
Move back and forth；The lower end of lower link 11 is connected with the pin shaft hole 13 on main carrier bar 2 by the 3rd rotatable bearing pin 12；Upper connecting rod
6 upper end is connected with the first rotatable bearing pin 5 for being fixed on airframe.
In the present embodiment, kinematic chain isKinematic chain, wherein P are sliding pair, and U is universal pair, and R is to rotate
It is secondary.
Sliding pair represents that slide block 8 is moved back and forth up and down in main carrier bar 2.
Universal pair includes the first universal pair, the second universal pair, the 3rd universal pair, and wherein the first universal pair represents upper connecting rod 6
With the annexation of airframe, the second universal pair represents the annexation of intermediate connecting rod 9 and slide block 7, and the 3rd universal pair is represented
The annexation of lower link 11 and main carrier bar 2.
Rotate subtabulation and show that upper connecting rod 6, intermediate connecting rod 9 and lower link 11 are hinged by pitman pin 10.
In the present embodiment, the first kinematic chain I and the second kinematic chain II are space four bar linkage mechanism, the space four-linkses
Mechanism includes airframe, main carrier bar 2, upper connecting rod 6 and lower link 11, and wherein, airframe is fix bar, main carrier bar 2
For drive rod, upper connecting rod 6 is follower lever, and lower link 11 is the connecting rod of connection drive rod and follower lever.Intermediate connecting rod 9 and slide block
7 common auxiliary upper connecting rods 6 and lower link 11 carry out locking, it is to avoid upper connecting rod 6 and lower link 11 are lower in working order to be occurred relatively
Rotate.
Main carrier bar 2 and the first kinematic chain I and the second kinematic chain II realize that the folding and unfolding of undercarriage and state keep work(jointly
Can, when landing gear locking into place, main carrier bar 2 constitutes indeterminate truss structure with lockable mechanism 3, possesses carrying well
Ability, wherein also introduces Planar Mechanisms, it is ensured that even if after a kinematic chain therein failure, undercarriage remains to normal work,
Ensure that the safety and reliability of undercarriage.When undercarriage is withdrawn completely, main carrier bar 2 is located at lockable mechanism 3
In approximately the same plane, structure is extremely compact, greatly reduces the space of occupancy, highly beneficial to aircraft model Miniaturization Design.
On the one hand, when undercarriage is put down completely, the upper connecting rod 6 of every kinematic chain is conllinear with lower link 11, using connecting rod
Movement dead carries out locking, it is to avoid two connecting rods relatively rotate.At the same time, intermediate connecting rod 9 is moved to and upper connecting rod
6th, the vertical position of lower link 11, further prevents upper connecting rod 6, lower link 11 from relatively rotating.So, every kinematic chain rises
Dual-locking effect has been arrived, and hyperstatic truss structure has been defined with main carrier bar 2, can with good mechanical property and structure
By property.
Still further aspect, main carrier bar 2 are in same with the first kinematic chain I and the second kinematic chain II when withdrawing completely
In plane, during undercarriage is reclaimed, drive system 1 drives main carrier bar 2 to rotate, and drives the first kinematic chain I and second
Kinematic chain I I are rotated around the first rotatable bearing pin 5, and at the same time, upper connecting rod 6, intermediate connecting rod 9, lower link 11 will follow master to hold
Carry bar 2 to link together, when undercarriage is reclaimed completely, upper connecting rod 6, lower link 11, intermediate connecting rod 9 and 2 positive benefit of main carrier bar
It is in approximately the same plane so that the space that undercarriage occupies is greatly lowered, highly beneficial to the compact designed of aircraft model.
Referring to Fig. 4 a or Fig. 4 b, it is assumed that a certain bar kinematic chain failure of undercarriage, a kinematic chain is remained intact in addition, i.e.,
There is a failure kinematic chain 14, undercarriage now still has a complete Dual-locking kinematic chain to may insure main carrier bar
2 operating attitude, still ensure that undercarriage is packed up and put down, and can carry the impact of certain load, it is ensured that
Aircraft remains to normal landing when occurring unexpected, reduces the incidence rate of aviation accident, therefore, the undercarriage has high intensity and height
Reliability, possesses and remains under extreme conditions realize carrying the function with folding and unfolding.
In sum, the embodiment of the present invention can effectively improve the landing safety of undercarriage, it is ensured that the work of undercarriage
Make reliability, be with a wide range of applications and huge market value.
The foregoing is only presently preferred embodiments of the present invention, not to limit the present invention, all spirit in the present invention and
Within principle, any modification, equivalent substitution and improvements made etc. should be included within the scope of the present invention.
Claims (6)
1. a kind of novel high-strength high intense lightweight undercarriage, it is characterised in that including drive system, main carrying
Bar, lockable mechanism and shock mitigation system；
The drive system arrangements are on the top of the main carrier bar；
The main carrier bar is arranged between airframe and the shock mitigation system；
The lockable mechanism is arranged between airframe and the main carrier bar, including the fortune of two identical non-co-planar arrangements
Dynamic chain, respectively the first kinematic chain and the second kinematic chain；
The shock mitigation system is arranged in the bottom of the main carrier bar, including amortisseur and pneumatic tire, under the amortisseur
The end connection pneumatic tire.
2. a kind of novel high-strength high intense lightweight undercarriage according to claim 1, it is characterised in that institute
State the first kinematic chain and second kinematic chain and be located at different planes, and first kinematic chain and second kinematic chain
Plane is symmetrical relative to the plane of movement of main carrier bar.
3. a kind of novel high-strength high intense lightweight undercarriage according to claim 2, it is characterised in that institute
State the first kinematic chain and second kinematic chain include upper connecting rod, lower link, intermediate connecting rod, slide block, the first rotatable bearing pin,
Second rotatable bearing pin, the 3rd rotatable bearing pin, pitman pin；
The upper connecting rod, the intermediate connecting rod and the lower link are connected by the pitman pin；
The upper end of the upper connecting rod is connected with the described first rotatable bearing pin for being fixed on airframe；The intermediate connecting rod passes through
The second rotatable bearing pin is connected with the slide block, and the slide block is moved back and forth along the axis direction of the main carrier bar；
The lower end of the lower link is connected with the pin shaft hole on the main carrier bar by the 3rd rotatable bearing pin.
4. a kind of novel high-strength high intense lightweight undercarriage according to claim 3, it is characterised in that institute
State the first kinematic chain and second kinematic chain isKinematic chain, describedIn kinematic chain, P is slip
Pair, U are universal pair, and R is to rotate secondary；
The sliding pair represents that the slide block is moved back and forth up and down in the main carrier bar；
The universal pair includes the first universal pair, the second universal pair, the 3rd universal pair, and wherein described first universal pair represents described
The annexation of upper connecting rod and airframe, second universal pair represent that the intermediate connecting rod and the connection of the slide block are closed
System, the 3rd universal pair represent the annexation of the lower link and the main carrier bar；
The rotation subtabulation shows that the upper connecting rod, the intermediate connecting rod and the lower link are hinged by the pitman pin.
5. a kind of novel high-strength high intense lightweight undercarriage according to claim 4, it is characterised in that institute
State the first kinematic chain and second kinematic chain be space four bar linkage mechanism, the space four bar linkage mechanism be airframe,
Main carrier bar, upper connecting rod and lower link, the airframe be fix bar, the main carrier bar be drive rod, the upper connecting rod
For follower lever, the lower link is the connecting rod for connecting the drive rod and the follower lever.
6. a kind of novel high-strength high intense lightweight undercarriage according to claim 5, it is characterised in that institute
Space four bar linkage mechanism is stated for Dual-locking structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610921124.2A CN106516087A (en) | 2016-10-21 | 2016-10-21 | Novel high-strength high-compactness lightweight aircraft landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610921124.2A CN106516087A (en) | 2016-10-21 | 2016-10-21 | Novel high-strength high-compactness lightweight aircraft landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106516087A true CN106516087A (en) | 2017-03-22 |
Family
ID=58291856
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610921124.2A Pending CN106516087A (en) | 2016-10-21 | 2016-10-21 | Novel high-strength high-compactness lightweight aircraft landing gear |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107521670A (en) * | 2017-07-28 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | Truss-like main landing gear interface frame, mating frame |
| CN107985562A (en) * | 2017-12-07 | 2018-05-04 | 清华大学 | A kind of lightweight compact formula undercarriage |
| CN110834719A (en) * | 2018-08-17 | 2020-02-25 | 中国飞机强度研究所 | Bionic leg undercarriage system |
| CN111891340A (en) * | 2020-06-17 | 2020-11-06 | 成都飞机工业（集团）有限责任公司 | Undercarriage receive and releases actuator based on four-bar linkage operation |
| CN111924091A (en) * | 2020-08-18 | 2020-11-13 | 泊鹭（荆门）飞机有限公司 | Detachable aircraft landing gear suitable for stop on rough road |
| CN112958790A (en) * | 2021-03-02 | 2021-06-15 | 中航飞机起落架有限责任公司 | Turning method of semi-closed structure |
| CN114671011B (en) * | 2022-03-18 | 2023-10-03 | 成都飞机工业（集团）有限责任公司 | Symmetrical multi-connecting-rod electric drive aircraft landing gear structure |
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|---|---|---|---|---|
| US4328939A (en) * | 1979-12-26 | 1982-05-11 | The Boeing Company | Airplane main landing gear assembly |
| FR2800704A1 (en) * | 1999-11-10 | 2001-05-11 | Messier Dowty Sa | Aircraft landing gear for underwing use has stiffening actuator to allow flexibility except in deployment phase |
| CN101065292A (en) * | 2004-08-30 | 2007-10-31 | 梅西尔-道蒂（美国）公司 | Dual brace-determinate landing gear |
| CN102897325A (en) * | 2011-07-27 | 2013-01-30 | 霍尼韦尔国际公司 | Aircraft taxi system including drive chain |
| CN103895858A (en) * | 2014-03-24 | 2014-07-02 | 清华大学 | Novel undercarriage with high strength and high reliability |
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2016
- 2016-10-21 CN CN201610921124.2A patent/CN106516087A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4328939A (en) * | 1979-12-26 | 1982-05-11 | The Boeing Company | Airplane main landing gear assembly |
| FR2800704A1 (en) * | 1999-11-10 | 2001-05-11 | Messier Dowty Sa | Aircraft landing gear for underwing use has stiffening actuator to allow flexibility except in deployment phase |
| CN101065292A (en) * | 2004-08-30 | 2007-10-31 | 梅西尔-道蒂（美国）公司 | Dual brace-determinate landing gear |
| CN102897325A (en) * | 2011-07-27 | 2013-01-30 | 霍尼韦尔国际公司 | Aircraft taxi system including drive chain |
| CN103895858A (en) * | 2014-03-24 | 2014-07-02 | 清华大学 | Novel undercarriage with high strength and high reliability |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107521670A (en) * | 2017-07-28 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | Truss-like main landing gear interface frame, mating frame |
| CN107985562A (en) * | 2017-12-07 | 2018-05-04 | 清华大学 | A kind of lightweight compact formula undercarriage |
| CN110834719A (en) * | 2018-08-17 | 2020-02-25 | 中国飞机强度研究所 | Bionic leg undercarriage system |
| CN111891340A (en) * | 2020-06-17 | 2020-11-06 | 成都飞机工业（集团）有限责任公司 | Undercarriage receive and releases actuator based on four-bar linkage operation |
| CN111924091A (en) * | 2020-08-18 | 2020-11-13 | 泊鹭（荆门）飞机有限公司 | Detachable aircraft landing gear suitable for stop on rough road |
| CN112958790A (en) * | 2021-03-02 | 2021-06-15 | 中航飞机起落架有限责任公司 | Turning method of semi-closed structure |
| CN112958790B (en) * | 2021-03-02 | 2022-08-02 | 中航飞机起落架有限责任公司 | Turning method of semi-closed structure |
| CN114671011B (en) * | 2022-03-18 | 2023-10-03 | 成都飞机工业（集团）有限责任公司 | Symmetrical multi-connecting-rod electric drive aircraft landing gear structure |
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Application publication date: 20170322 |