GB2493744A - Improved Aircraft Landing Gear Assembly and Method of Manufacture - Google Patents

Improved Aircraft Landing Gear Assembly and Method of Manufacture Download PDF

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Publication number
GB2493744A
GB2493744A GB1114157.9A GB201114157A GB2493744A GB 2493744 A GB2493744 A GB 2493744A GB 201114157 A GB201114157 A GB 201114157A GB 2493744 A GB2493744 A GB 2493744A
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GB
United Kingdom
Prior art keywords
sub
component
components
landing gear
text
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
GB1114157.9A
Other versions
GB2493744B (en
GB201114157D0 (en
Inventor
Andraz Vatovec
Germain Forgeoux
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
Priority to GB1114157.9A priority Critical patent/GB2493744B/en
Publication of GB201114157D0 publication Critical patent/GB201114157D0/en
Priority to PCT/GB2012/051903 priority patent/WO2013024256A2/en
Publication of GB2493744A publication Critical patent/GB2493744A/en
Application granted granted Critical
Publication of GB2493744B publication Critical patent/GB2493744B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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 
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K15/00—Electron-beam welding or cutting
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
    • B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
    • B23K20/122—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding using a non-consumable tool, e.g. friction stir welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/08—Non-ferrous metals or alloys
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/08—Non-ferrous metals or alloys
    • B23K2103/10—Aluminium or alloys thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/08—Non-ferrous metals or alloys
    • B23K2103/14—Titanium or alloys thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/18—Dissimilar materials

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • Welding Or Cutting Using Electron Beams (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)

Abstract

Embodiments of the present invention provide a method of manufacturing an aircraft landing gear component having a plurality of sub-components, the method comprising forming first and second sub-components from dissimilar materials and welding said sub-components together to form the landing gear component. The welding technique may be friction welding or electron beam welding

Description

Improved Aircraft Landing Gear Assembly and Method of Manufacture
Background to the Invention.
Aircraft landing gear assemblies are typically subjected to high loading conditions during normal use, i.e. during aircraft landings and ground operations. The larger and heavier the aircraft the greater these loadings are. Consequently high strength/performance materials, such as aluminium and/or titanium alloys, are used for some of the landing gear components. Large components, such as bogie beams or sliders, are subsequently typically produced from large mono-block forgings, where the entire component is manufactured from the same material, or alternatively manufactured as several sub-components joined by mechanical joints.
Both of the methods of manufacture mentioned above have disadvantages. For large components made from mono-block forgings the most stressed portion of the component when the gear is in use drives the selection of the high performance material for that forging. The same material must therefore be used for the entirety of the component, regardless of the stress requirements/expectations of the rest of the component. More of the high performance, and therefore expensive, material is therefore used than is strictly necessary. To subsequently minimise the cost and weight of the mono-block forgings the component design typically includes complex design features that may present difficulties in subsequent machining and manufacturing processes. The joining of multiple sub-components using mechanical joints tends to increase the overall weight of the final component because of the additional material required to form the mechanical joints whilst maintaining the desired overall strength of the component. The mechanical joints also tend to be relatively complex and elaborate to manufacture.
It has also been known to manufacture landing gear assemblies by manufacturing several sub-components from the same material and subsequently welding the sub-components together, the same material being used for all sub-components to facilitate the welding process. However, as with the mono-block forgings, the use of the same material, that material being selected as a function of the highest expected stresses of any of the sub-components, does not allow the selection of the optimum material for each sub-component. Subsequently, the majority of the sub-components are over engineered and therefore more expensive than strictly required.
There therefore remains a requirement to manufacture a landing gear assembly in which the optimum material for each sub-component may be selected, whilst reducing or overcoming the disadvantages mentioned above.
Summary of the Invention.
According to a first aspect of the present invention there is provided a method of manufacturing an aircraft landing gear component having a plurality of sub-components, the method comprising forming first and second sub-components from dissimilar materials and welding said sub-components together to form the landing gear component.
The sub-components are preferably welded together using any one of rotary friction welding and electron beam welding, although other welding techniques known to the skilled person may be used.
At least one of the sub-components may be machined prior to welding.
In preferred embodiments, the material for each sub-component is selected in dependence on one or more of the desired mechanical properties of said sub-component and cost of the material.
According to a second aspect of the present invention there is further provided an aircraft landing gear assembly comprising a first sub-component of a first material and a second sub-component of a second, dissimilar, material, the first and second sub-components being welded together.
Preferably the material for each sub-component is selected in dependence on one or more of the desired mechanical properties of said sub-component and cost of the material.
The sub-components may be welded together using any one of rotary friction welding and electron beam welding, or any other known welding technique.
The landing gear assembly may comprise a side stay in which the first component comprises at least one lug arranged to be pivotably connected to a further section of an aircraft and the second component comprises an elongate body element.
Brief Description of the Figures
Embodiments of the present invention are described below by way of non-limiting examples only with reference to the accompanying figures, of which: Figure 1 illustrates a method of manufacture of an aircraft landing gear assembly according to an embodiment of the present invention.
Detailed Description of Embodiments of the nvention.
Figure 1 schematically illustrates individual steps in the manufacture of an aircraft landing gear assembly in accordance with an embodiment of the present invention.
In the example illustrated, the landing gear assembly 2 has two sub-components 4, 6. However, it will be appreciated that the method of the present invention is equally applicable to assemblies having a greater number of sub-components and the example illustrated is of minimal complexity to aid the understanding of the reader.
First, the individual sub-components 4, 6 are individually manufactured, for example as simple forgings, castings or taken from stock items (such as stock tubes). The material for each subcomponent is selected according to the desired physical properties for that individual sub-component. Examples of the physical properties used in selecting the material for each sub-component include cost, strength, weight, fatigue resistance, stiffness andcorrosion resistance. The individual sub-components replace one large and complex element in the prior art.
Next, simple machining operations are optionally performed on one or more of the sub-components as required such that each sub-component is machined to final or near final shape 4a, 6a. The machining operations for each sub-component is less complex to achieve than for prior art single, larger, components due to their reduced size and complexity of basic shape. Additionally, the reduced complexity of the machining required means that smaller, less complex machining units can be used that are typically cheaper to purchase and maintain (and possibly cheaper to operate). In some embodiments of the present invention, depending on the complexity of the desired final shape of a sub-component the machining operation can be omitted. Next, the individual sub-components 4a, 6a are welded together to form the final landing gear assembly 2a. In preferred embodiments the welding techniques used include friction welding, and in particular rotary friction welding, and electron beam welding. Both of these techniques, which are techniques known in the general art of welding and are therefore not described in detail here, are particularly suitable for the welding of dissimilar materials. However, other techniques for welding dissimilar materials may be used within the scope of the present invention.
By the use of multiple sub-components welded together single landing gear assemblies can be produced from multiple materials, thus allowing each section (sub-component) to be manufactured from the most suitable material for that particular section in terms of material characteristics and/or cost. The simplification of the optionally required machining steps of the individual sub-components, due to their reduced size in comparison with the final assembly, also reduces the manufacturing cost. For example, a side stay may be produced in accordance with embodiments of the present invention in which the stay includes separate end sections in which the (pivotable) attachment lugs are formed from a high strength/quality material (as the lugs may experience high stresses in use), with the lugs being welded to either end of the main elongate stay body that is manufactured from a second, dissimilar, material of lower strength, The main body of the stay tends not to experience the levels of stress that the lugs do and need not, therefore, be manufactured from the same high strength (and high cost) material as the lugs.
The use of welds, facilitated by the use of techniques suitable for welding dissimilar materials, eliminates the requirement for mechanical joints that would otherwise be required to join multiple sub-components and which would in themselves undesirably increase the mass of material needed for each sub-component (to form the mechanical joint) and therefore their weight and cost.

Claims (8)

  1. <claim-text>Claims.1. A method of manufacturing an aircraft landing gear component having a plurality of sub-components, the method comprising: forming first and second sub-components from dissimilar materials; and welding said sub-components together to form the landing gear component.</claim-text> <claim-text>2. A method of manufacture according to claim 1, wherein said sub-components are welded together using any one of rotary friction welding and electron beam welding.</claim-text> <claim-text>3. A method of manufacture according to claim 1 or 2, wherein at least one of the sub-components is machined prior to welding.</claim-text> <claim-text>4. A method of manufacture according to any preceding claim, wherein the material for each sub-component is selected in dependence on one or more of the desired mechanical properties of said sub-component and cost of the material.</claim-text> <claim-text>5. An aircraft landing gear assembly comprising a first sub-component of a first material and a second sub-component of a second, dissimilar, material, the first and second sub-components being welded together.</claim-text> <claim-text>6. An aircraft landing gear assembly according to claim 5, wherein the material for each sub-component is selected in dependence on one or more of the desired mechanical properties of said sub-component and cost of the material.</claim-text> <claim-text>7. An aircraft landing gear assembly according to claim 5 or 6, wherein said sub-components are welded together using any one of rotary friction welding and electron beam welding.</claim-text> <claim-text>8. An aircraft landing gear assembly according to any one of claims 5 to 7 comprising a side stay in which said first component comprises at least one lug arranged to be pivotably connected to a further section of an aircraft and said second component comprises an elongate body element.SAMENDMENTS TO THE CLAIMS HAVE BEEN FILED AS FOLLOWS1. A method of manufacturing a complex aircraft landing gear component having a plurality of sub-components, the method comprising: forming first and second sub-components from dissimilar materials, wherein each sub-component is formed to final or near final shape; and welding said sub-components together to form the complex aircraft landing gear component.
  2. 2. A method of manufacture according to claim 1, wherein said sub-components are welded together using any one of rotary friction welding and electron beam welding.
  3. 3. A method of manufacture according to claim 1 or 2, wherein at least one of the sub-components is machined prior to welding.LIt)
  4. 4. A method of manufacture according to any preceding claim, wherein the C material for each sub-component is selected in dependence on one or more of the desired mechanical properties of said sub-component and cost of the r 20 material.
  5. 5. An aircraft landing gear assembly comprising a first sub-component of a first material and a second sub-component of a second, dissimilar, material, the first and second sub-components being welded together.
  6. 6. An aircraft landing gear assembly according to claim 5, wherein the material for each sub-component is selected in dependence on one or more of the desired mechanical properties of said sub-component and cost of the material.
  7. 7. An aircraft landing gear assembly according to claim 5 or 6, wherein said sub-components are welded together using any one of rotary friction welding and electron beam welding.
  8. 8. An aircraft landing gear assembly according to any one of claims 5 to 7 comprising a side stay in which said first component comprises at least one lug arranged to be pivotably connected to a further section of an aircraft and said second component comprises an elongate body element. (4 rLID</claim-text>
GB1114157.9A 2011-08-17 2011-08-17 Improved aircraft landing gear assembly and method of manufacture Active GB2493744B (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB1114157.9A GB2493744B (en) 2011-08-17 2011-08-17 Improved aircraft landing gear assembly and method of manufacture
PCT/GB2012/051903 WO2013024256A2 (en) 2011-08-17 2012-08-06 Improved aircraft landing gear assembly and method of manufacture

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1114157.9A GB2493744B (en) 2011-08-17 2011-08-17 Improved aircraft landing gear assembly and method of manufacture

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GB201114157D0 GB201114157D0 (en) 2011-10-05
GB2493744A true GB2493744A (en) 2013-02-20
GB2493744B GB2493744B (en) 2014-08-27

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WO (1) WO2013024256A2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2983829B1 (en) * 2011-12-07 2014-01-31 Messier Bugatti Dowty LANDING ROD FOR AIRCRAFT

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GB1467163A (en) * 1973-06-18 1977-03-16 Hitachi Ltd Method for joining together members of dissimilar metals
SU1357169A1 (en) * 1986-01-03 1987-12-07 Днепропетровский Металлургический Институт Им.Л.И.Брежнева Method of friction welding of heterogeneous materials
EP0627276A2 (en) * 1993-05-20 1994-12-07 The Welding Institute Friction joining
US6291086B1 (en) * 1997-04-04 2001-09-18 Xuan Nguyen-Dinh Friction welding interlayer and method for joining gamma titanium aluminide to steel, and turbocharger components thereof
WO2002052053A1 (en) * 2000-12-21 2002-07-04 Alcoa Inc. Aluminum alloy products and artificial aging nethod
JP2002224857A (en) * 2001-02-02 2002-08-13 Jidosha Buhin Kogyo Co Ltd Joining structure and joining method between hollow members made of respectively different kinds of metal
JP2002336975A (en) * 2001-05-11 2002-11-26 Mitsubishi Automob Eng Co Ltd Method for friction-welding pipe members made of dissimilar materials
US20050045694A1 (en) * 2003-08-29 2005-03-03 Subramanian Pazhayannur Ramanathan Friction stir welding apparatus and associated thermal management systems and methods
JP2005111489A (en) * 2003-10-03 2005-04-28 Toyota Motor Corp Structure and method for joining dissimilar material
JP2005279744A (en) * 2004-03-30 2005-10-13 Nissan Motor Co Ltd Butt welding method of different kind of material using high energy beam
JP2006193129A (en) * 2004-12-16 2006-07-27 Hitachi Ltd Method for manufacturing truck frame for rolling stock, and truck frame
WO2008027474A2 (en) * 2006-08-30 2008-03-06 Fluor Technologies Corporation Compositions and methods for dissimilar material welding
JP2009202212A (en) * 2008-02-28 2009-09-10 Mitsubishi Heavy Ind Ltd Method and apparatus for joining different kinds of material
US20100129684A1 (en) * 2005-12-06 2010-05-27 Nissan Motor Co., Ltd. Joining method, joining machine, and joint structure of dissimilar material
CN101913022A (en) * 2010-09-10 2010-12-15 哈尔滨工业大学 Method for welding dissimilar materials of TA15 titanium alloy and chromium bronze through electron beams
WO2011075044A1 (en) * 2009-12-16 2011-06-23 Sapa Ab Composite conductive component and method for making it

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US5547148A (en) * 1994-11-18 1996-08-20 United Technologies Corporation Crashworthy landing gear
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FR2933016B1 (en) * 2008-06-30 2010-12-24 Alcan Rhenalu PULSE MIXING FRICTION WELDING PROCESS
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB467658A (en) * 1935-07-01 1937-06-14 Martha Horn Improvements in aeroplane parts formed of metal
GB1467163A (en) * 1973-06-18 1977-03-16 Hitachi Ltd Method for joining together members of dissimilar metals
SU1357169A1 (en) * 1986-01-03 1987-12-07 Днепропетровский Металлургический Институт Им.Л.И.Брежнева Method of friction welding of heterogeneous materials
EP0627276A2 (en) * 1993-05-20 1994-12-07 The Welding Institute Friction joining
US6291086B1 (en) * 1997-04-04 2001-09-18 Xuan Nguyen-Dinh Friction welding interlayer and method for joining gamma titanium aluminide to steel, and turbocharger components thereof
WO2002052053A1 (en) * 2000-12-21 2002-07-04 Alcoa Inc. Aluminum alloy products and artificial aging nethod
JP2002224857A (en) * 2001-02-02 2002-08-13 Jidosha Buhin Kogyo Co Ltd Joining structure and joining method between hollow members made of respectively different kinds of metal
JP2002336975A (en) * 2001-05-11 2002-11-26 Mitsubishi Automob Eng Co Ltd Method for friction-welding pipe members made of dissimilar materials
US20050045694A1 (en) * 2003-08-29 2005-03-03 Subramanian Pazhayannur Ramanathan Friction stir welding apparatus and associated thermal management systems and methods
JP2005111489A (en) * 2003-10-03 2005-04-28 Toyota Motor Corp Structure and method for joining dissimilar material
JP2005279744A (en) * 2004-03-30 2005-10-13 Nissan Motor Co Ltd Butt welding method of different kind of material using high energy beam
JP2006193129A (en) * 2004-12-16 2006-07-27 Hitachi Ltd Method for manufacturing truck frame for rolling stock, and truck frame
US20100129684A1 (en) * 2005-12-06 2010-05-27 Nissan Motor Co., Ltd. Joining method, joining machine, and joint structure of dissimilar material
WO2008027474A2 (en) * 2006-08-30 2008-03-06 Fluor Technologies Corporation Compositions and methods for dissimilar material welding
JP2009202212A (en) * 2008-02-28 2009-09-10 Mitsubishi Heavy Ind Ltd Method and apparatus for joining different kinds of material
WO2011075044A1 (en) * 2009-12-16 2011-06-23 Sapa Ab Composite conductive component and method for making it
CN101913022A (en) * 2010-09-10 2010-12-15 哈尔滨工业大学 Method for welding dissimilar materials of TA15 titanium alloy and chromium bronze through electron beams

Also Published As

Publication number Publication date
GB2493744B (en) 2014-08-27
WO2013024256A3 (en) 2013-11-28
WO2013024256A2 (en) 2013-02-21
GB201114157D0 (en) 2011-10-05

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