CN104290902A - Rocking arm-type undercarriage - Google Patents
Rocking arm-type undercarriage Download PDFInfo
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- CN104290902A CN104290902A CN201410424840.0A CN201410424840A CN104290902A CN 104290902 A CN104290902 A CN 104290902A CN 201410424840 A CN201410424840 A CN 201410424840A CN 104290902 A CN104290902 A CN 104290902A
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- rocking arm
- folding
- unfolding
- hinged
- undercarriage
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Abstract
The invention relates to a rocking arm-type undercarriage, which belongs to the technical field of aviation helicopter and undercarriage. The rocking arm-type undercarriage is characterized by comprising a folding and unfolding mechanism (4) capable of being a linkage mechanism with a folding and unfolding actuator cylinder or the folding and unfolding actuator cylinder; a circular tube joint (5) hinged to an undercarriage body through a fork-form joint; and a buffer (2) having an active telescoping function. The undercarriage can realize bidirectional folding and unfolding. The rocking arm-type undercarriage has the characteristics that 1)through the contraction motion of the buffer having the active telescoping function, a rocking arm is driven for winding around a transverse tube of the circular tube joint to rotate, the undercarriage is upwardly folded; in addition, the circular tube joint and the rocking arm are driven through the motion of the folding and unfolding mechanism for winding around the undercarriage body to rotate, and the undercarriage is inwardly folded, and the folding process and unfolding process are opposite. The rocking arm-type undercarriage can realize a folding and unfolding design of a toe out-shaped large structural size rocking arm type undercarriage in a small folding and unfolding space, structure is compact, requirements for folding and unfolding space are low, folding and unfolding efficiency is high, rotation of the rocking arm at two directions can be realized by a circular tube joint design, and the transverse tube is not required, so that weight is conveniently controlled.
Description
Technical field
The invention belongs to aviation helicopter, undercarriage technical field, relate to a kind of articulated landing gear.
Background technology
For meeting anti-crash and narrow fuselage arrangement requirement, current military helicopter generally adopts outer " eight " font articulated landing gear, this configuration alighting gear will realize that folding and unfolding inwardly need complete, upwards both direction folding and unfolding campaign, conventional layout is adopted to need very large folding and unfolding space, and this and narrow fuselage arrange and contradict not possess practicality.The present invention is intended to propose a kind of novel articulated landing gear configuration scheme, to realize the folding and unfolding design of outer " eight " font macrostructure size articulated landing gear.
Summary of the invention
Object of the present invention:
Design a kind of novel articulated landing gear structure, in less folding and unfolding space to realize the folding and unfolding design of outer " eight " font macrostructure size articulated landing gear.
Technical scheme of the present invention:
A kind of articulated landing gear, comprises rocking arm 1, energy disperser 2, wheel 3, jack 4, Conduit Joint 5, and Conduit Joint 5 is hinged with fuselage; Rocking arm 1 is hinged with Conduit Joint 5, can rotate around Conduit Joint 5; Jack 4 one end and Conduit Joint 5 hinged, the other end and fuselage hinged; Energy disperser 2 one end and rocking arm 1 hinged, the other end and fuselage hinged.
Described jack 4 or can be independent retractable actuating cylinder for the connecting rod mechanism of band retractable actuating cylinder; Described Conduit Joint 5 is fork-shaped pipe gimbal structure, by fork configuration and fuselage hinged, by pipe and alighting gear rocking arm hinged hinged by forked element with fuselage.This large span fork-shaped pipe gimbal structure can realize the relative fuselage of alighting gear and upwards inwardly move simultaneously, can effectively transmit and bear the moment of flexure of the side direction of ground effects on wheel, vertical load generation.
Described scalable energy disperser 2 is connected with fuselage, rocking arm and all adopts wide-angle oscillating bearing to connect, when energy disperser compression, elongation and alighting gear are inwardly packed up, the joint ball head of oscillating bearing freely can rotate in its outer ring, avoids and constructive interference when there is larger swing when energy disperser can be made in folding and unfolding or land; Energy disperser Oil-gas Separation is by injecting or getting rid of fluid mode controller buffer length, and be that energy disperser is in full elongation state by oiling, energy disperser possesses cushion characteristic effect, can shorten buffer length by oil extraction, can play retractable actuating cylinder effect.
Its folding and unfolding principle of work is as follows: will pack up the motion that procedure decomposition is rocking arm both direction.One is the contractile motion of energy disperser by having initiatively Telescopic, and drive rocking arm to rotate around Conduit Joint transverse tube, alighting gear is upwards packed up, as shown in Figure 2; Additionally by jack motion, drive Conduit Joint to rotate around fuselage together with rocking arm, alighting gear is inwardly packed up as shown in Figure 2.Effect after gear up as shown in Figure 4.Put down process contrary with the process of packing up.
Key point of the present invention:
A) two-way multi-aspect space folding and unfolding.
B) scalable energy disperser.
C) realize rocking arm by Conduit Joint design to rotate around both direction.
Beneficial effect of the present invention:
Patent of the present invention achieves the folding and unfolding design of outer " eight " font macrostructure size articulated landing gear, and its compact conformation is extremely low to folding and unfolding space requirement; Folding and unfolding efficiency is high; Conduit Joint design realizes rocking arm and rotates around both direction, does not need transverse tube to be conducive to weight control.
Accompanying drawing explanation
Fig. 1 is a kind of overall installation figure of this invention
Fig. 2 is this invention upwards folding and unfolding schematic diagram
Fig. 3 is the inside folding and unfolding schematic diagram of this invention
Fig. 4 is the two-way folding and unfolding schematic diagram of this invention
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further details.Plant articulated landing gear, comprise rocking arm 1, energy disperser 2, wheel 3, jack 4, Conduit Joint 5, Conduit Joint 5 is hinged with fuselage; Rocking arm 1 is hinged with Conduit Joint 5, can rotate around Conduit Joint 5; Jack 4 one end and Conduit Joint 5 hinged, the other end and fuselage hinged; Energy disperser 2 one end and rocking arm 1 hinged, the other end and fuselage hinged.
During installation, first wheel 3, Conduit Joint 5 are connected with rocking arm 1, then Conduit Joint 5 are connected with fuselage by bolt.Energy disperser, jack 4 are then installed successively.When installing energy disperser 2, now energy disperser top connection and fuselage are bolted, then swing energy disperser and rocking arm make it mounting hole alignment, are being bolted.When jack 4 is installed, first jack 4 and fuselage are bolted, then by regulating the length of jack 4, make it corresponding mounting hole and aliging with Conduit Joint 5 mounting hole, being bolted.
Claims (4)
1. an articulated landing gear, it is characterized in that, comprise rocking arm (1), energy disperser (2), wheel (3), jack (4), Conduit Joint (5), Conduit Joint (5) is hinged with fuselage; Rocking arm (1) is hinged with Conduit Joint (5), can rotate around Conduit Joint (5); Jack (4) one end and Conduit Joint (5) hinged, the other end and fuselage hinged; Energy disperser (2) one end and rocking arm (1) hinged, the other end and fuselage hinged.
2. articulated landing gear according to claim 1, is characterized in that, described jack (4) or can be independent retractable actuating cylinder for the connecting rod mechanism of band retractable actuating cylinder.
3. articulated landing gear according to claim 1, it is characterized in that, described Conduit Joint (5) is fork-shaped pipe gimbal structure, by fork configuration and fuselage hinged, by pipe and alighting gear rocking arm hinged hinged by forked element with fuselage.
4. articulated landing gear according to claim 1, it is characterized in that, scalable energy disperser (2) is connected with fuselage, rocking arm and all adopts wide-angle oscillating bearing to connect, when energy disperser compression, elongation and alighting gear are inwardly packed up, the joint ball head of oscillating bearing freely can rotate in its outer ring, avoids and constructive interference when there is larger swing when making energy disperser in folding and unfolding or land; Energy disperser Oil-gas Separation is by injecting or getting rid of fluid mode controller buffer length, and be that energy disperser is in full elongation state by oiling, energy disperser possesses cushion characteristic effect, can shorten buffer length by oil extraction, plays retractable actuating cylinder effect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410424840.0A CN104290902A (en) | 2014-08-26 | 2014-08-26 | Rocking arm-type undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410424840.0A CN104290902A (en) | 2014-08-26 | 2014-08-26 | Rocking arm-type undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104290902A true CN104290902A (en) | 2015-01-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410424840.0A Pending CN104290902A (en) | 2014-08-26 | 2014-08-26 | Rocking arm-type undercarriage |
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| CN (1) | CN104290902A (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105000197A (en) * | 2015-08-11 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Rotating part loading mechanism |
| CN106111765A (en) * | 2016-08-24 | 2016-11-16 | 泉州市双塔汽车零件有限公司 | A kind of oil gauge pipe channelling machine |
| CN106965922A (en) * | 2016-01-13 | 2017-07-21 | 哈尔滨飞机工业集团有限责任公司 | A kind of arm-type undercarriage of Novel remote |
| CN108082458A (en) * | 2017-11-29 | 2018-05-29 | 中国直升机设计研究所 | A kind of adaptive undercarriage |
| CN108128443A (en) * | 2017-12-28 | 2018-06-08 | 成都优艾维智能科技有限责任公司 | Non-virtual position impact-resistant quick-release type electric retractable undercarriage |
| CN109774926A (en) * | 2019-01-22 | 2019-05-21 | 南京航空航天大学 | Hypersonic vehicle wheel-ski combines lifting gear |
| CN109835470A (en) * | 2019-02-22 | 2019-06-04 | 武汉科技大学 | The undercarriage of novel tilt cylinder driving |
| CN110683062A (en) * | 2019-09-29 | 2020-01-14 | 中国直升机设计研究所 | Helicopter tail protection device |
| CN110834719A (en) * | 2018-08-17 | 2020-02-25 | 中国飞机强度研究所 | Bionic leg undercarriage system |
| CN112224389A (en) * | 2020-10-09 | 2021-01-15 | 南京航空航天大学 | Retractable main landing gear capable of meeting requirements of different specifications and layouts |
| CN112407256A (en) * | 2020-12-01 | 2021-02-26 | 中航飞机起落架有限责任公司 | Slide rail formula undercarriage |
| CN114030598A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Retractable rocker arm type undercarriage |
| WO2024124598A1 (en) * | 2022-12-16 | 2024-06-20 | 江西洪都航空工业集团有限责任公司 | Active leg retraction main landing gear having compact space |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2392892A (en) * | 1942-07-18 | 1946-01-15 | Lockheed Aircraft Corp | Retractable landing gear |
| US3951361A (en) * | 1975-06-23 | 1976-04-20 | Pneumo Corporation | Articulated main landing gear |
| US4189117A (en) * | 1977-03-08 | 1980-02-19 | Messier-Hispano-Bugatti | Retractable fuselage mounted undercarriage |
| CN102905973A (en) * | 2010-01-19 | 2013-01-30 | 梅西耶-布加蒂-道提公司 | Aircraft landing gear of the rocker-arm and deformable-parallelogram type |
-
2014
- 2014-08-26 CN CN201410424840.0A patent/CN104290902A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2392892A (en) * | 1942-07-18 | 1946-01-15 | Lockheed Aircraft Corp | Retractable landing gear |
| US3951361A (en) * | 1975-06-23 | 1976-04-20 | Pneumo Corporation | Articulated main landing gear |
| US4189117A (en) * | 1977-03-08 | 1980-02-19 | Messier-Hispano-Bugatti | Retractable fuselage mounted undercarriage |
| CN102905973A (en) * | 2010-01-19 | 2013-01-30 | 梅西耶-布加蒂-道提公司 | Aircraft landing gear of the rocker-arm and deformable-parallelogram type |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105000197A (en) * | 2015-08-11 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Rotating part loading mechanism |
| CN106965922A (en) * | 2016-01-13 | 2017-07-21 | 哈尔滨飞机工业集团有限责任公司 | A kind of arm-type undercarriage of Novel remote |
| CN106965922B (en) * | 2016-01-13 | 2020-06-09 | 哈尔滨飞机工业集团有限责任公司 | Novel rocker arm type undercarriage |
| CN106111765A (en) * | 2016-08-24 | 2016-11-16 | 泉州市双塔汽车零件有限公司 | A kind of oil gauge pipe channelling machine |
| CN106111765B (en) * | 2016-08-24 | 2019-11-12 | 泉州市双塔汽车零件有限公司 | A kind of oil gauge pipe channelling machine |
| CN108082458B (en) * | 2017-11-29 | 2021-03-30 | 中国直升机设计研究所 | Self-adaptive undercarriage |
| CN108082458A (en) * | 2017-11-29 | 2018-05-29 | 中国直升机设计研究所 | A kind of adaptive undercarriage |
| CN108128443A (en) * | 2017-12-28 | 2018-06-08 | 成都优艾维智能科技有限责任公司 | Non-virtual position impact-resistant quick-release type electric retractable undercarriage |
| CN108128443B (en) * | 2017-12-28 | 2023-12-05 | 成都优艾维智能科技有限责任公司 | Virtual-position-free impact-resistant quick-release type electric retractable landing gear |
| CN110834719A (en) * | 2018-08-17 | 2020-02-25 | 中国飞机强度研究所 | Bionic leg undercarriage system |
| CN109774926A (en) * | 2019-01-22 | 2019-05-21 | 南京航空航天大学 | Hypersonic vehicle wheel-ski combines lifting gear |
| CN109835470A (en) * | 2019-02-22 | 2019-06-04 | 武汉科技大学 | The undercarriage of novel tilt cylinder driving |
| CN110683062A (en) * | 2019-09-29 | 2020-01-14 | 中国直升机设计研究所 | Helicopter tail protection device |
| CN110683062B (en) * | 2019-09-29 | 2023-04-18 | 中国直升机设计研究所 | Helicopter tail protection device |
| CN112224389A (en) * | 2020-10-09 | 2021-01-15 | 南京航空航天大学 | Retractable main landing gear capable of meeting requirements of different specifications and layouts |
| CN112407256A (en) * | 2020-12-01 | 2021-02-26 | 中航飞机起落架有限责任公司 | Slide rail formula undercarriage |
| CN114030598A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Retractable rocker arm type undercarriage |
| CN114030598B (en) * | 2021-11-19 | 2023-09-08 | 中国直升机设计研究所 | Retractable rocker arm type landing gear |
| WO2024124598A1 (en) * | 2022-12-16 | 2024-06-20 | 江西洪都航空工业集团有限责任公司 | Active leg retraction main landing gear having compact space |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150121 |
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| WD01 | Invention patent application deemed withdrawn after publication |