CN109850132A - A kind of detachable undercarriage contracting leg mechanism - Google Patents
A kind of detachable undercarriage contracting leg mechanism Download PDFInfo
- Publication number
- CN109850132A CN109850132A CN201811492795.7A CN201811492795A CN109850132A CN 109850132 A CN109850132 A CN 109850132A CN 201811492795 A CN201811492795 A CN 201811492795A CN 109850132 A CN109850132 A CN 109850132A
- Authority
- CN
- China
- Prior art keywords
- toggle
- rocker arm
- pressurized strut
- type rocker
- piston rod
- 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.)
- Granted
Links
Classifications
-
- 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
- Transmission Devices (AREA)
- Fluid-Damping Devices (AREA)
Abstract
A kind of detachable undercarriage contracting leg mechanism, including pillar outer cylinder (1), support piston bar (9), wheel tire (4), it further include upper toggle (2) and lower toggle (3), upper toggle (2) the hinged pillar outer cylinder (1), lower toggle (3) hinged pillar piston rod (9), it is hinged between upper toggle (2) and lower toggle (3), wheel tire (4) is mounted on support piston bar (9) lower end, the present invention keeps undercarriage leg safe, reliable compaction, save undercarriage parking space, and do not influence damper leg normal use.
Description
Technical field
A kind of aircraft landing gear mechanism design field, and in particular to detachable undercarriage contracting leg mechanism.
Background technique
Undercarriage is to park for aircraft on ground, slide, the device that take-off and landing uses.In aircraft flight process
In, in order to reduce flight resistance, most of undercarriage can all be taken in aircraft landing gear cabin.But the space of landing gear compartment is universal
Narrow, for aircraft longer for undercarriage legs such as carrier-borne aircrafts, the space of landing gear compartment is more compact.In order to save
Frame storage space is fallen, moderate compression (contracting leg) can be carried out to undercarriage leg, taken in again after reducing undercarriage leg length
It falls in frame cabin.
Currently, aircraft mainly pulls support piston bar by multi-connecting-rod mechanism, the contracting leg of undercarriage leg is realized.But it should
Class mechanism is complex, weight is larger, and reliability and maintainability are to be improved.Further, since actuator by multi link with
Support piston bar is connected directly, and in aircraft landing, damper leg compression, actuator and link mechanism will follow support piston bar
Movement, the possibility of have an impact damper leg free movement or generation clamping stagnation.And clamping stagnation once occurs for actuator or link mechanism, it will
Cause undercarriage leg piston rod can not proper motion, threaten aircraft security.
Summary of the invention
Goal of the invention:
In order to solve, existing undercarriage contracting leg mechanism has an impact to damper leg proper motion, there are clamping stagnation risk and mechanisms
Complicated problem, the invention proposes one kind can make the safe and reliable compression of undercarriage leg, and does not influence damper leg and normally make
Simple, lightweight detachable contracting leg mechanism.
Technical solution:
A kind of detachable undercarriage contracting leg mechanism, including pillar outer cylinder 1, support piston bar 9, wheel tire 4 further include
Upper toggle 2 and lower toggle 3, the upper 2 hinged pillar outer cylinder 1 of toggle, lower 3 hinged pillar piston rod 9 of toggle, upper torsion
Hinged between the arm of force 2 and lower toggle 3, wheel tire 4 is mounted on 9 lower end of support piston bar.
A kind of detachable undercarriage contracting leg mechanism, further includes pressurized strut 5, pressurized strut piston rod 6, pulley 7, L
Type rocker arm 8, the pressurized strut 5 are fixedly mounted on the top of pillar outer cylinder 1 along strut lengths direction, and pressurized strut piston rod 6 can root
According to needing to stretch out or take in pressurized strut 5, the lower end of pressurized strut piston rod 6 is equipped with a pulley 7, which can install around itself
Axis is freely rotated；The side auricle of the end of the L-type rocker arm 8 and upper 2 upper end of toggle is connected, upper toggle 2 and L-type rocker arm
8 with after pillar outer cylinder 1 hingedly installation, and upper toggle 2 synchronous can be rotated with L-type rocker arm 8 around hinge hole, the free end of L-type rocker arm 8
Plane is located at the lower section of pulley 7；Pulley 7 contacts the free transverse plane of L-type rocker arm 8 when pressurized strut piston rod 6 extends downwardly, and enables and turning round
The arm of force 2 and the rotation of L-type rocker arm 8 drive lower toggle 3 to shrink upwards, complete the receipts leg movement of support piston bar 9.
A kind of detachable undercarriage contracting leg mechanism, upper 2 plane of toggle and 8 plane of L-type rocker arm form 130 °
Angle.
A kind of detachable undercarriage contracting leg mechanism, the free transverse plane of L-type rocker arm 8 are hinged with L-type rocker arm 8
Transverse plane forms about 160 ° of angles.
A kind of detachable undercarriage contracting leg mechanism, pressurized strut piston rod 6 can be in the upper and lower poles in pressurized strut 5
Extreme position locking.
Beneficial effect includes:
(a) present invention can make undercarriage leg realize reliable compaction.By separation design, make the pressurized strut of contracting leg can be with branch
Column piston bar is detached from, to not influence the normal use of damper leg；
(b) complexity that the present invention can reduce the installation of undercarriage contracting leg mechanism, disassemble and maintain, improves contracting leg mechanism
Reliability simultaneously mitigates undercarriage weight；
(c) mechanism manufacturing process of the present invention is simple, material is mature, is easily achieved, and can be widely used in column support type
On undercarriage.
Detailed description of the invention
Fig. 1 is primary structure composition of the invention；
Fig. 2 is upper toggle and L-type rocker structure axonometric drawing；
Fig. 3 is upper toggle and L-type rocker structure side view；
Fig. 4 is the full elongation state of pillar；
Fig. 5 is pillar full compression state；
Fig. 6 is pillar contracting leg state.
Specific embodiment
Fig. 1 is primary structure composition schematic diagram of the invention.The present invention is on the top of pillar outer cylinder 1 along strut lengths direction
Pressurized strut 5 is fixedly mounted, pressurized strut piston rod 6 can be stretched out as needed or be taken in pressurized strut 5, and can be in Upper-lower Limit position
Set locking.The lower end of pressurized strut piston rod 6 is equipped with a pulley 7, which can be freely rotated around itself installation axle.Upper torsion
The upper end of arm 2 and the lower end of pillar outer cylinder 1 are hinged, and the lower end of upper toggle 2 and the upper end of lower toggle 3 are hinged, lower toggle 3
Lower end and support piston bar 9 lower end it is hinged.
Fig. 2 and Fig. 3 is upper toggle 2 and the connected structural schematic diagram formed of L-type rocker arm 8.The end of L-type rocker arm 8 with it is upper
The side auricle of 2 upper end of toggle is connected, and 2 plane of toggle and 8 plane of L-type rocker arm is made to form about 130 ° of angle.L-type is shaken
The free end of arm 8 bypasses pillar outer cylinder 1, and free transverse plane and hinged end plane form about 160 ° of angles, make free transverse plane position
In the lower section of pulley 7.2 auricles of the hinge hole through 2 upper end of end and upper toggle of L-type rocker arm 8.Upper toggle 2 and L-type
After rocker arm 8 and pillar outer cylinder 1 are hingedly installed, upper toggle 2 synchronous can be rotated with L-type rocker arm 8 around hinge hole, in rotation process
In, free end will not be interfered with pillar outer cylinder 1.
Fig. 4,5,6 are the working principle of the invention schematic diagram.Equal stages, pressurized strut piston rod 6 are parked and slided in aircraft
It takes in pressurized strut 5, and is locked in retracted position.Total travel motion process of the pillar from full elongation state to full compression state
In, L-type rocker arm 8 is rotated with upper toggle 2 around articulated shaft, and L-type rocker arm 8 is not in contact always with pulley 7, avoids influencing pillar
Piston rod 9 moves.Take off it is liftoff after, 6 latch-release of pressurized strut piston rod is extended downwardly from pressurized strut 5.Pulley 7 and L
The free end face of type rocker arm 8 is in contact, and the end face is pushed to move downward, and rotates L-type rocker arm 8 around articulated shaft, and then is driven
Upper toggle 2 and the movement of lower toggle 3, compress support piston bar 9 into pillar outer cylinder 1, realize contracting leg.When actuation cylinder piston
It will be locked in extended position after bar 6 is fully extended, pillar is made to be maintained at contracting leg state, undercarriage can take in landing gear compartment
In.When aircraft landing, pillar is released from landing gear compartment, and pressurized strut piston rod 6 unlocks, and is taken in pressurized strut 5.Pulley
7 move upwards under the drive of pressurized strut piston rod 6, disengage with L-type rocker arm 8, and pressurized strut piston rod 6 is finally locked in
Retracted position.Support piston bar 9 freely stretches out under the effect of pillar buffer pressure, until full elongation state, support piston bar 9
It can be freely moved.
Claims (5)
1. a kind of detachable undercarriage contracting leg mechanism, including pillar outer cylinder (1), support piston bar (9), wheel tire (4),
It is characterized in that, further includes upper toggle (2) and lower toggle (3), upper toggle (2) the hinged pillar outer cylinder (1), lower torsion
Arm (3) hinged pillar piston rod (9), hinged between upper toggle (2) and lower toggle (3), wheel tire (4) is mounted on pillar
Piston rod (9) lower end.
2. a kind of detachable undercarriage contracting leg mechanism according to claim 1, which is characterized in that further include pressurized strut
(5), pressurized strut piston rod (6), pulley (7), L-type rocker arm (8), the pressurized strut (5) is on the top of pillar outer cylinder (1) along pillar
Length direction is fixedly mounted, and pressurized strut piston rod (6) can be stretched out as needed or be taken in pressurized strut (5), pressurized strut piston rod (6)
Lower end one pulley (7) is installed, which can be freely rotated around itself installation axle；The end of the L-type rocker arm (8) with it is upper
The side auricle of toggle (2) upper end is connected, after upper toggle (2) and L-type rocker arm (8) and pillar outer cylinder (1) are hingedly installed, on
Toggle (2) synchronous can be rotated with L-type rocker arm (8) around hinge hole, and the free transverse plane of L-type rocker arm (8) is located under pulley (7)
Side；When pressurized strut piston rod (6) extends downwardly, pulley (7) contacts the free transverse plane of L-type rocker arm (8), enables toggle (2) and L
Type rocker arm (8) rotation drives lower toggle (3) to shrink upwards, completes the contracting leg movement of support piston bar (9).
3. a kind of detachable undercarriage contracting leg mechanism according to claim 2, which is characterized in that upper toggle (2) are flat
Face and L-type rocker arm (8) hinged end plane form 130 ° of angle.
4. a kind of detachable undercarriage contracting leg mechanism according to claim 2, which is characterized in that L-type rocker arm (8) from
About 160 ° of angles are formed by the hinged end plane of transverse plane and L-type rocker arm (8).
5. a kind of detachable undercarriage contracting leg mechanism according to claim 2, which is characterized in that pressurized strut piston rod
(6) it can be locked in the Upper-lower Limit position in pressurized strut (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811492795.7A CN109850132B (en) | 2018-12-07 | 2018-12-07 | Separable landing gear leg-retracting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811492795.7A CN109850132B (en) | 2018-12-07 | 2018-12-07 | Separable landing gear leg-retracting mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109850132A true CN109850132A (en) | 2019-06-07 |
| CN109850132B CN109850132B (en) | 2022-08-09 |
Family
ID=66890696
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811492795.7A Active CN109850132B (en) | 2018-12-07 | 2018-12-07 | Separable landing gear leg-retracting mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109850132B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110576966A (en) * | 2019-09-29 | 2019-12-17 | 中国直升机设计研究所 | Strut type undercarriage |
| CN112623204A (en) * | 2021-02-18 | 2021-04-09 | 江西洪都航空工业集团有限责任公司 | Novel undercarriage centering mechanism |
| CN114030594A (en) * | 2021-12-17 | 2022-02-11 | 江西洪都航空工业集团有限责任公司 | Strut type undercarriage leg retracting mechanism |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB388226A (en) * | 1932-03-23 | 1933-02-23 | Leroy Randle Grumman | Improvements in retractable landing gear |
| CA1049475A (en) * | 1975-11-21 | 1979-02-27 | Messier-Hispano | Retractable fuselage mounted landing gear for an aerodyne |
| CN101519120A (en) * | 2009-04-07 | 2009-09-02 | 南京航空航天大学 | Semi-active shimmy damper of undercarriage and control method thereof |
| CN101870358A (en) * | 2010-06-23 | 2010-10-27 | 南京航空航天大学 | Toggle type nose wheel steering mechanism and work method |
| CN102020014A (en) * | 2010-12-09 | 2011-04-20 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
| CN102224072A (en) * | 2008-12-05 | 2011-10-19 | 梅西耶-道提股份有限公司 | Device for retracting aircraft landing gear |
| CN203623962U (en) * | 2012-11-12 | 2014-06-04 | 湾流航空航天公司 | Front landing gear device for aircraft and assembling method thereof |
| CN104527969A (en) * | 2014-11-19 | 2015-04-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane front wing servo acting system and servo control method thereof |
| CN106218866A (en) * | 2016-08-19 | 2016-12-14 | 中航飞机起落架有限责任公司 | A kind of backplate follower of undercarriage |
| CN206374969U (en) * | 2016-12-30 | 2017-08-04 | 万丰航空工业有限公司 | A kind of baby plane telescopic landing gear |
| CN108216599A (en) * | 2017-12-14 | 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 big nose wheel steering mechanism for manipulating angle of Double-linkage |
| 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 |
-
2018
- 2018-12-07 CN CN201811492795.7A patent/CN109850132B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB388226A (en) * | 1932-03-23 | 1933-02-23 | Leroy Randle Grumman | Improvements in retractable landing gear |
| CA1049475A (en) * | 1975-11-21 | 1979-02-27 | Messier-Hispano | Retractable fuselage mounted landing gear for an aerodyne |
| CN102224072A (en) * | 2008-12-05 | 2011-10-19 | 梅西耶-道提股份有限公司 | Device for retracting aircraft landing gear |
| CN101519120A (en) * | 2009-04-07 | 2009-09-02 | 南京航空航天大学 | Semi-active shimmy damper of undercarriage and control method thereof |
| CN101870358A (en) * | 2010-06-23 | 2010-10-27 | 南京航空航天大学 | Toggle type nose wheel steering mechanism and work method |
| CN102020014A (en) * | 2010-12-09 | 2011-04-20 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
| CN203623962U (en) * | 2012-11-12 | 2014-06-04 | 湾流航空航天公司 | Front landing gear device for aircraft and assembling method thereof |
| EP2746154A1 (en) * | 2012-11-12 | 2014-06-25 | Gulfstream Aerospace Corporation | Nose landing gear arrangement for aircraft and method of assembly |
| CN104527969A (en) * | 2014-11-19 | 2015-04-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane front wing servo acting system and servo control method thereof |
| CN106218866A (en) * | 2016-08-19 | 2016-12-14 | 中航飞机起落架有限责任公司 | A kind of backplate follower of undercarriage |
| CN206374969U (en) * | 2016-12-30 | 2017-08-04 | 万丰航空工业有限公司 | A kind of baby plane telescopic landing gear |
| CN108216599A (en) * | 2017-12-14 | 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 big nose wheel steering mechanism for manipulating angle of Double-linkage |
| 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 |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110576966A (en) * | 2019-09-29 | 2019-12-17 | 中国直升机设计研究所 | Strut type undercarriage |
| CN112623204A (en) * | 2021-02-18 | 2021-04-09 | 江西洪都航空工业集团有限责任公司 | Novel undercarriage centering mechanism |
| CN114030594A (en) * | 2021-12-17 | 2022-02-11 | 江西洪都航空工业集团有限责任公司 | Strut type undercarriage leg retracting mechanism |
| CN114030594B (en) * | 2021-12-17 | 2023-08-25 | 江西洪都航空工业集团有限责任公司 | Leg retracting mechanism of strut type landing gear |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109850132B (en) | 2022-08-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104176244B (en) | A kind of landing gear compartment door linkage draw off gear | |
| CN103387050A (en) | Landing gear for an aircraft | |
| CN104203750B (en) | A kind of trousers | |
| JP5854771B2 (en) | Hydraulic actuator for semi-lever landing gear | |
| CN102431644B (en) | Plane main undercarriage space retraction/extension mechanism and retraction/extension method | |
| CN109850132A (en) | A kind of detachable undercarriage contracting leg mechanism | |
| CN102020014B (en) | Airplane landing gear with deflected airplane wheel retraction jack | |
| US8602352B2 (en) | Method for operating a landing gear assembly with a breaker strut | |
| US9205917B2 (en) | Vertically retracting side articulating landing gear for aircraft | |
| CN106218866B (en) | A kind of backplate follower of undercarriage | |
| CN102639397B (en) | Nose gear of an aircraft comprising a single control device for retraction and steering | |
| US20110198441A1 (en) | Device for retracting aircraft landing gear | |
| DE112006003472T5 (en) | Retractable lifting blades for an aircraft | |
| DE2503177A1 (en) | SWING AIRPLANE OR SWINGING APPARATUS | |
| JPS591634B2 (en) | Syarin Hikikomi Shikichiyakuri Couch | |
| EP3681796B1 (en) | Folding landing gear | |
| CN2635519Y (en) | Device for clamping and lifting airplane wheel | |
| CN209441619U (en) | A kind of fixed wing aircraft undercarriage | |
| CN208544417U (en) | A kind of unmanned plane main landing gear | |
| CN202935587U (en) | Airplane nosewheel clamping device | |
| US4063698A (en) | Landing gear for an aerodyne | |
| US3533580A (en) | Lifting system of fuselage undercarriages with retractable wheels mounted in diabolo | |
| US2432408A (en) | Retractable landing gear | |
| DE102013006647B4 (en) | Glider or motor glider with retractable tail wheel | |
| CN115447764B (en) | Lifting rotating wheel type landing gear |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |