WO2013011324A1 - Ensemble articulation cylindrique - Google Patents

Ensemble articulation cylindrique Download PDF

Info

Publication number
WO2013011324A1
WO2013011324A1 PCT/GB2012/051736 GB2012051736W WO2013011324A1 WO 2013011324 A1 WO2013011324 A1 WO 2013011324A1 GB 2012051736 W GB2012051736 W GB 2012051736W WO 2013011324 A1 WO2013011324 A1 WO 2013011324A1
Authority
WO
WIPO (PCT)
Prior art keywords
pin
joint
joint pin
joint assembly
retaining
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.)
Ceased
Application number
PCT/GB2012/051736
Other languages
English (en)
Inventor
Chris Green
Ian Bennett
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.)
Safran Landing Systems UK Ltd
Original Assignee
Messier Dowty Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Messier Dowty Ltd filed Critical Messier Dowty Ltd
Publication of WO2013011324A1 publication Critical patent/WO2013011324A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C11/00—Pivots; Pivotal connections
    • F16C11/04—Pivotal connections
    • F16C11/045—Pivotal connections with at least a pair of arms pivoting relatively to at least one other arm, all arms being mounted on one pin
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C11/00—Pivots; Pivotal connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C25/00—Bearings for exclusively rotary movement adjustable for wear or play
    • F16C25/02—Sliding-contact bearings
    • F16C25/04—Sliding-contact bearings self-adjusting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F16C33/12—Structural composition; Use of special materials or surface treatments, e.g. for rust-proofing
    • F16C33/121—Use of special materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2326/00—Articles relating to transporting
    • F16C2326/43—Aeroplanes; Helicopters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/16—Sliding surface consisting mainly of graphite

Definitions

  • each landing gear assembly typically includes a number of pin joint assemblies that allow separate elements of the landing gear assembly to pivot about the pin joint.
  • Pin joints will typically be included in the side-stay assemblies to allow the upper and lower elements of the side-stay to pivot both with respect to one another and with respect to the main sliding tube of the landing gear and the aircraft frame itself.
  • the landing gear assembly can experience both lateral and longitudinal loadings during take-off and landing events it is normal for some deflection to occur in the lugs of the side-stays through which the pin joint passes. At present, the forces induced as a result of these lug deflections are reacted by the headed pin and nut of the pin joint assembly that passes through the lugs and allows the relative rotation of the two side-stay elements.
  • the headed pin and nut must be designed so as to be capable of carrying these deflection loads, with the necessary safety margin additionally provided.
  • To achieve this increased load carrying capability increases the weight of the pin joint assembly, typically by approximately 2.5kg per pin joint. Therefore, on a dual stay landing gear assembly with six pin joints approximately 15kg is added to the mass of each landing gear assembly simply to provide the requisite additional load carrying capability of the pin joint assemblies. In addition to the increased manufacturing cost arising from the larger pin joint assemblies, this added weight is undesirable in terms of the overall weight of the aircraft as it has a direct bearing on the fuel efficiency and fuel capacity of the aircraft. It would therefore be desirable to reduce the weight of a pin joint assembly without comprising its load carrying capability.
  • a pin joint assembly for an aircraft landing gear comprising an elongate joint pin, at least one first lug through which the joint pin passes and at least one second lug through which the joint pin passes, wherein the joint pin includes first and second retaining elements located at opposite ends t pin and arranged to maintain the location of the joint pin relative to the first and second lugs, and wherein the pin join assembly further comprises a respective resilient member located between each of the retaining elements and a respective one of the first and second lugs, each resilient element being elastically deformable.
  • One or more of the first and second retaining elements may comprise a retaining nut arranged to be in threaded engagement with the joint pin.
  • first and second retaining elements may comprise an end cap secured to the joint pin.
  • first and second retaining elements may be secured to the joint pin by means of a retaining nut threaded to a portion of the joint pin passing through the or each respective retaining element.
  • first and second retaining elements may be secured to the joint pin by means of a retaining nut threaded to a bolt passing through the or each respective retaining element and the joint pin.
  • the or each resilient member of the pin joint assembly may comprise any one of a wave spring washer, a belleville washer, a coil spring, and an O-ring.
  • Figure 1 schematically illustrates a cross-section of a pin joint assembly according to the prior art
  • Figure 2 schematically illustrates in cross-section a pin joint assembly according to an embodiment of the present invention.
  • Figure 3 schematically illustrates a pin joint assembly according to a second embodiment of the present invention.
  • a pin joint assembly according to the prior art is schematically illustrated in cross-section in Figure 1.
  • the pin joint assembly includes a pair of first lugs 2, 2a and a second lug 4 interposed between the first lugs, and a joint pin 6 passing through the first and second lugs and about which the lugs can rotate.
  • the joint pin 6 has an integral head 8 located at one end of the pin preventing the pin from passing all the way through the first and second lugs, and has a threaded portion 10 provided at the opposite end to which a retaining nut 12 is secured, thus completing the pin joint assembly.
  • any deflections in the first and second lugs 2, 2a, 4 caused by radial loading of the pin joint cause the lugs to contact either the pin head 8 or retaining nut 12 and consequently load the stiff joint pin (bolt) 6 potentially to the point where the load is so high that the pin will fail.
  • the nut 12, and also pin head 8 must be oversized so as to be able to accommodate the additional lug defection loadings over and above the normal operational loadings of the pin joint. This adds weight and cost to the pin joint assembly.
  • FIG. 2 An improved pin joint assembly according to an embodiment of the prior art is schematically illustrated in cross-section in Figure 2.
  • first and second lugs 102, 102a & 104 are provided though which a joint pin 106 extends.
  • the joint pin 106 includes a retaining element in the form of an integral pin head 108 and also includes a threaded portion onto which a retaining nut 112 is secured.
  • a resilient member 114 Located between the inner face of the pin head 108 and the outer surface of the first lug 102a is a resilient member 114, which in the particular embodiment illustrated in Figure 2 is represented as a wave spring washer.
  • a second resilient member 114a is located between the second first lug 102 and the retaining nut 112.
  • a further embodiment of a pin joint assembly according to the present invention is schematically illustrated in the cross-section of Figure 3.
  • first and second lugs 202, 202a & 204 are provided through which a joint pin 206 extends.
  • Retaining caps 208 are provided at either end of the pin joint 206 as separate elements through which a portion of the joint pin 206 extends.
  • the portions of the joint pin that extend through the retaining elements 208 are threaded and respective retaining nuts 212, 212a are fastened to the threaded portions, thereby securing the retaining elements 208 in place and maintaining the physical arrangement of the pin joint assembly.
  • a bolt 216 having threaded portions at either end passes through both the retaining elements 208 and a corresponding bore in the joint pin 206 with the retaining nuts 212, 212a being secured to the threaded portions of the bolt 216.
  • First and second resilient members 214, 214a are provided in between the inner faces of the retaining elements 208 and the outer face of the adjacent first or second lugs, as arranged and described with reference to Figure 2.
  • any combination of integral or separate end caps and retaining nuts may be provided in further embodiments of the present invention.
  • large retaining nuts 212 may be used instead, in an analogous fashion to the retaining nut 112 illustrated in Figure 2.
  • the means of securing these to the joint pin 206 may vary within the other embodiments of the present invention, i.e. other means of securing the end caps 208 t pin 206 may be utilised or the end caps may be formed as an integral part of the pin joint.
  • separate end caps may be provided as illustrated in Figure 3, but with two or more lightweight bolts and corresponding retaining nuts rather than the single bolt and paired retaining nuts shown in Figure 3.
  • the resilient members 114, 114a may be of any suitable design and elastically deformable material.
  • one or more belleville washers may be provided, as may one or more coil springs or elastomeric O-rings.
  • the resulting pin joint assembly can be significantly smaller and lighter than the corresponding prior art pin joint assemblies. For example, for a typical dual stay aircraft landing gear with six joints approximately 15kg of weight reduction can be achieved using pin joint assemblies according to the present invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
  • Bolts, Nuts, And Washers (AREA)

Abstract

L'invention concerne un ensemble articulation cylindrique pour un train d'atterrissage d'aéronef comprenant : une articulation cylindrique allongée (206) ; au moins un premier ergot (202a,202) à travers lequel passe l'articulation cylindrique ; et au moins un deuxième ergot (204) à travers lequel passe l'articulation cylindrique ; l'articulation cylindrique comprenant des premier (212) et deuxième (212a) éléments de retenue situés aux extrémités opposées de l'articulation et disposés de sorte à maintenir l'emplacement de l'articulation cylindrique par rapport aux premier et deuxième ergots, l'ensemble articulation selon l'invention comprenant également des éléments élastiques (214,214a) respectifs situés entre chaque élément de retenue et le premier ou le deuxième ergot, respectivement, chaque élément élastique pouvant se déformer élastiquement.
PCT/GB2012/051736 2011-07-21 2012-07-20 Ensemble articulation cylindrique Ceased WO2013011324A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1112544.0 2011-07-21
GB1112544.0A GB2493145A (en) 2011-07-21 2011-07-21 A pin joint assembly for an aircraft landing gear

Publications (1)

Publication Number Publication Date
WO2013011324A1 true WO2013011324A1 (fr) 2013-01-24

Family

ID=44586943

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2012/051736 Ceased WO2013011324A1 (fr) 2011-07-21 2012-07-20 Ensemble articulation cylindrique

Country Status (2)

Country Link
GB (1) GB2493145A (fr)
WO (1) WO2013011324A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3002211A1 (fr) * 2014-09-30 2016-04-06 Messier-Dowty Limited Ensemble de train d'atterrissage d'avion
EP3228539A1 (fr) * 2016-04-06 2017-10-11 Safran Landing Systems UK Limited Ensemble de train d'atterrissage d'avion
US10683085B2 (en) 2015-10-06 2020-06-16 Safran Landing Systems Uk Ltd Aircraft assembly
WO2022178348A1 (fr) * 2021-02-19 2022-08-25 Emerson Automation Solutions Final Control US LP Connexion d'étrier flottant

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105221560B (zh) * 2015-10-13 2018-05-08 重庆晟初科技有限公司 一种连接关节

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT287407B (de) * 1967-09-04 1971-01-25 Raoul Dipl Ing Joern Gelenkbuchse
US5251986A (en) * 1992-08-10 1993-10-12 Grumman Aerospace Corporation Bushing assembly
DE19731305A1 (de) * 1997-07-14 1999-02-04 Brose Fahrzeugteile Gelenkverbindung
EP2199203A1 (fr) * 2008-12-22 2010-06-23 Rolls-Royce plc Assemblage de broche de résonateur de sortie

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4932807A (en) * 1988-07-28 1990-06-12 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Clevis joint for deployable space structures
US5100083A (en) * 1990-02-13 1992-03-31 The Boeing Company Retractable landing gear with self-braced folding strut
SU1827991A1 (ru) * 1990-07-09 1996-06-10 Авиационный научно-технический комплекс им.А.Н.Туполева Узел крепления опоры шасси к каркасу летательного аппарата
US6332682B1 (en) * 2000-09-29 2001-12-25 Yoshida Industry Co., Ltd. Hinge structure for use in joining temple and front rim in eyeglasses

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT287407B (de) * 1967-09-04 1971-01-25 Raoul Dipl Ing Joern Gelenkbuchse
US5251986A (en) * 1992-08-10 1993-10-12 Grumman Aerospace Corporation Bushing assembly
DE19731305A1 (de) * 1997-07-14 1999-02-04 Brose Fahrzeugteile Gelenkverbindung
EP2199203A1 (fr) * 2008-12-22 2010-06-23 Rolls-Royce plc Assemblage de broche de résonateur de sortie

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3002211A1 (fr) * 2014-09-30 2016-04-06 Messier-Dowty Limited Ensemble de train d'atterrissage d'avion
US10683085B2 (en) 2015-10-06 2020-06-16 Safran Landing Systems Uk Ltd Aircraft assembly
US11498661B2 (en) 2015-10-06 2022-11-15 Safran Landing Systems Uk Ltd Aircraft assembly
EP3228539A1 (fr) * 2016-04-06 2017-10-11 Safran Landing Systems UK Limited Ensemble de train d'atterrissage d'avion
US20170291695A1 (en) * 2016-04-06 2017-10-12 Safran Landing Systems UK Limited Aircraft landing gear assembly
CN107264781A (zh) * 2016-04-06 2017-10-20 赛峰起落架系统英国有限公司 飞行器起落架组件
US10501172B2 (en) 2016-04-06 2019-12-10 Safran Landing Systems Uk Ltd Aircraft landing gear assembly
CN121361574A (zh) * 2016-04-06 2026-01-20 赛峰起落架系统英国有限公司 飞行器起落架组件
WO2022178348A1 (fr) * 2021-02-19 2022-08-25 Emerson Automation Solutions Final Control US LP Connexion d'étrier flottant

Also Published As

Publication number Publication date
GB2493145A (en) 2013-01-30
GB201112544D0 (en) 2011-08-31

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