CN104210652A - Landing gear connecting structure - Google Patents

Landing gear connecting structure Download PDF

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Publication number
CN104210652A
CN104210652A CN201410425019.0A CN201410425019A CN104210652A CN 104210652 A CN104210652 A CN 104210652A CN 201410425019 A CN201410425019 A CN 201410425019A CN 104210652 A CN104210652 A CN 104210652A
Authority
CN
China
Prior art keywords
split bushing
bushing
hole
alighting gear
flange
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
Application number
CN201410425019.0A
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Chinese (zh)
Other versions
CN104210652B (en
Inventor
汪兰明
徐渊
蔡金金
苗红涛
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
China Helicopter Research and Development Institute
Original Assignee
China Helicopter Research and Development Institute
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Filing date
Publication date
Application filed by China Helicopter Research and Development Institute filed Critical China Helicopter Research and Development Institute
Priority to CN201410425019.0A priority Critical patent/CN104210652B/en
Publication of CN104210652A publication Critical patent/CN104210652A/en
Application granted granted Critical
Publication of CN104210652B publication Critical patent/CN104210652B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Abstract

The invention relates to a landing gear connecting structure and belongs to a design technology of a helicopter landing gear. The landing gear connecting structure is characterized by comprising a first bolt, a washer, a spring check ring, a flange plate, a crack bushing, a tapered bushing and a stud, wherein a circular inner hole is formed in the middle of the flange plate, through holes are formed in two sides of the flange plate, and bulges are arranged inwards in the inner hole and used for fixing the crack bushing; the inner hole of the crack bushing is tapered, a circular groove is formed in the outer edge of one end and used for installing the spring check ring and the flange plate; the outer surface of the tapered bushing is tapered, the inner hole of the tapered bushing is a threaded hole, and a threaded hole formed in the outer surface of the tapered bushing is used for mounting the stud. The landing gear connecting structure has the beneficial effects that the landing gear connecting structure belongs to circular conical surface interference connection, interference combination can be obtained by compression and assembling of a containing part and a contained part relative to axial displacement, the axial displacement and the compression can be realized by virtue of bolt connection, the press-fit distance of the circular conical surface interference connection is short, the mounting and dismounting are convenient, the mating surface is not easily bruised during mounting and dismounting and the landing gear connecting structure can be repeatedly mounted and dismounted.

Description

A kind of connection structure of alighting gear
Technical field
The invention belongs to alighting gear technology, relate to a kind of connection structure.
Background technology
Helicopter mast formula alighting gear and airframe structure are installed and are belonged to axle and be connected with axle, and bindiny mechanism needs can by damper leg dynamic changes process on airframe structure.Alighting gear connection member is power transmission critical parts.Alighting gear needs being dismounted for multiple times when safeguarding.Common interference connects and generally adopts at normal temperatures directly pressing-in method or temperature differential method press-in assembling, and the direct pressing-in method technique of normal temperature is simple, but because of in fitting process mating surfaces be scratched, thus decrease the magnitude of interference, reduce Joint strenght, should not being dismounted for multiple times; And though temperature differential method is without above-mentioned shortcoming, its technique is more complicated, makes troubles to using, safeguarding.
Summary of the invention
Object of the present invention:
This connection structure is used for helicopter landing gear and is connected with the installation of airframe structure, can meet the quick-detachment of alighting gear, installation requirement; Dismounting, mating surfaces is not easily scratched when installing, can being dismounted for multiple times; And can reliable operation under shock and vibration load.Solve alighting gear quick-detachment, installation question.
Technical scheme of the present invention:
A kind of connection structure of alighting gear, it is characterized in that, comprise the first bolt 1, packing ring 2, trip ring 5, flange 6, split bushing 7, cone bush 8 and stud 9, circular inner hole is had in the middle of flange 6, both sides have a through hole, endoporus inwardly has a projection, for fixing split bushing 7; Split bushing 7 endoporus is taper, and an outer, end has annular groove, for mounting spring back-up ring 5 and flange 6; Cone bush 8 outside face is taper, and endoporus is tapped bore, and outside face opens a tapped bore for installing Luo stake 9;
Cone bush 8 is fixedly connected with stud 9 by the tapped bore of its outside face, cone bush 8 is inserted in split bushing 7, the breach of split bushing 7 is snapped in by stud 9, prevent the axial rotation of split bushing 7 and cone bush 8 in installation process, flange 6, trip ring 5 load the annular groove part of split bushing 7 successively, and bolt 1 is fastenedly connected by the endoporus of packing ring 2, trip ring 5, flange 6 and cone bush 8 and cone bush 8 successively; Flange 6 is bolted on framing member.
Beneficial effect of the present invention:
This alighting gear connection structure belongs to circular conical surface interference and connects, external member and internal member displacement compression fit is to axial utilized to combine to obtain interference, its longitudinal travel and compression are bolted to realize, because the pressing of circular conical surface interference connection is apart from short, easy to loading and unloading, and during handling, mating surfaces is not easily scratched, and can repeatedly install and remove.
Accompanying drawing explanation
Fig. 1 is a kind of overall installation figure of this invention
Fig. 2 is the cutaway view of the upper and lower clamp assemblies of this invention
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further details: alighting gear is placed on installation site, rotate alighting gear until the hole in the lower adaptor that is connected with alighting gear of main body mechanism and the hole on damper leg urceolus are aimed at, fix with technique lock pin, stud 9 is installed in the tapped bore of cone bush 8 outside face, then cone bush 8 is arranged on split bushing 7, stud 9 snaps in the breach of split bushing 7, successively by flange 6, trip ring 5 is arranged on split bushing 7, dismantle processes pin installs split bushing 7, the crack of the split bushing 7 in expansion pin assembly is protected with HM109 sealant, hold-down bolt 1 is tightened and is applied certain moment, hold-down bolt 4.
Embodiment:
A kind of connection structure of alighting gear, comprise the first bolt 1, packing ring 2, trip ring 5, flange 6, split bushing 7, cone bush 8 and stud 9, have circular inner hole in the middle of flange 6, both sides have a through hole, endoporus inwardly has a projection, for fixing split bushing 7; Split bushing 7 endoporus is taper, and an outer, end has annular groove, for mounting spring back-up ring 5 and flange 6; Cone bush 8 outside face is taper, and endoporus is tapped bore, and outside face opens a tapped bore for installing Luo stake 9;
Alighting gear is placed on installation site, rotate alighting gear until the hole in the lower adaptor that is connected with alighting gear of main body mechanism and the hole on damper leg urceolus are aimed at, fix with technique lock pin, stud 9 is installed in the tapped bore of cone bush 8 outside face, then cone bush 8 is arranged on split bushing 7, stud 9 snaps in the breach of split bushing 7, successively by flange 6, trip ring 5 is arranged on split bushing 7, dismantle processes pin installs split bushing 7, the crack of the split bushing 7 in expansion pin assembly is protected with HM109 sealant, hold-down bolt 1 is tightened and is applied certain moment, hold-down bolt 4.
Described split bushing 7 endoporus is conical suface, cone bush 8 outside face is conical suface, interference combines to obtain to utilize external member and internal member displacement compression fit to axial, its longitudinal travel and compression are bolted to realize, when ensureing to load and unload, mating surfaces is not easily scratched, and can repeatedly install and remove.
Described flange 6 endoporus inwardly has a projection, for fixing split bushing 7, ensures that split bushing 7 can not rotate vertically.

Claims (3)

1. the connection structure of an alighting gear, it is characterized in that, comprise the first bolt (1), packing ring (2), trip ring (5), flange (6), split bushing (7), cone bush (8) and stud (9), circular inner hole is had in the middle of flange (6), both sides have a through hole, endoporus inwardly has a projection, for fixing split bushing (7); Split bushing (7) endoporus is taper, and an outer, end has annular groove, for mounting spring back-up ring (5) and flange (6); Cone bush (8) outside face is taper, and endoporus is tapped bore, and outside face opens a tapped bore for installing Luo stake (9);
Alighting gear is placed on installation site, rotate alighting gear until the hole in the lower adaptor that is connected with alighting gear of main body mechanism and the hole on damper leg urceolus are aimed at, fix with technique lock pin, stud (9) is installed in the tapped bore of cone bush (8) outside face, then cone bush (8) is arranged on split bushing (7), stud (9) snaps in the breach of split bushing (7), successively by flange (6), trip ring (5) is arranged on split bushing (7), dismantle processes pin installs split bushing (7), the crack of the split bushing (7) in expansion pin assembly is protected with HM109 sealant, hold-down bolt (1) is tightened and is applied certain moment, hold-down bolt (4).
2. the connection structure of a kind of alighting gear according to claim 1, it is characterized in that, described split bushing (7) endoporus is conical suface, cone bush (8) outside face is conical suface, external member and internal member displacement compression fit is to axial utilized to combine to obtain interference, its longitudinal travel and compression are bolted to realize, and when ensureing to load and unload, mating surfaces is not easily scratched, and can repeatedly install and remove.
3. the connection structure of a kind of alighting gear according to claim 1, it is characterized in that, described flange (6) endoporus inwardly has a projection, for fixing split bushing (7), ensures that split bushing (7) can not rotate vertically.
CN201410425019.0A 2014-08-26 2014-08-26 A kind of attachment structure of undercarriage Active CN104210652B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410425019.0A CN104210652B (en) 2014-08-26 2014-08-26 A kind of attachment structure of undercarriage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201410425019.0A CN104210652B (en) 2014-08-26 2014-08-26 A kind of attachment structure of undercarriage

Publications (2)

Publication Number Publication Date
CN104210652A true CN104210652A (en) 2014-12-17
CN104210652B CN104210652B (en) 2017-06-23

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN201410425019.0A Active CN104210652B (en) 2014-08-26 2014-08-26 A kind of attachment structure of undercarriage

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017107753A1 (en) * 2015-12-24 2017-06-29 广州亿航智能技术有限公司 Drone

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4544116A (en) * 1983-11-14 1985-10-01 Shwayder Warren M Helicopter landing skid shoe pad
CN103303472A (en) * 2013-06-24 2013-09-18 中国科学院长春光学精密机械与物理研究所 Free deflection lag-damping type nose landing gear of small unmanned air vehicle
CN203473239U (en) * 2013-07-15 2014-03-12 中国民用航空飞行学院 Mounting base for main landing gear of TB20 airplane
CN203738183U (en) * 2014-06-13 2014-07-30 成都敏捷制造工程有限公司 Device capable of achieving accurate positioning and clamping repeatedly

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4544116A (en) * 1983-11-14 1985-10-01 Shwayder Warren M Helicopter landing skid shoe pad
CN103303472A (en) * 2013-06-24 2013-09-18 中国科学院长春光学精密机械与物理研究所 Free deflection lag-damping type nose landing gear of small unmanned air vehicle
CN203473239U (en) * 2013-07-15 2014-03-12 中国民用航空飞行学院 Mounting base for main landing gear of TB20 airplane
CN203738183U (en) * 2014-06-13 2014-07-30 成都敏捷制造工程有限公司 Device capable of achieving accurate positioning and clamping repeatedly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017107753A1 (en) * 2015-12-24 2017-06-29 广州亿航智能技术有限公司 Drone

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