US20090007774A1 - Aircraft actuator piston - Google Patents
Aircraft actuator piston Download PDFInfo
- Publication number
- US20090007774A1 US20090007774A1 US12/166,543 US16654308A US2009007774A1 US 20090007774 A1 US20090007774 A1 US 20090007774A1 US 16654308 A US16654308 A US 16654308A US 2009007774 A1 US2009007774 A1 US 2009007774A1
- Authority
- US
- United States
- Prior art keywords
- piston
- piece
- set forth
- stem
- cap
- 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.)
- Abandoned
Links
- 239000000463 material Substances 0.000 claims description 8
- 229910045601 alloy Inorganic materials 0.000 claims description 7
- 239000000956 alloy Substances 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 5
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 150000002739 metals Chemical class 0.000 claims description 4
- 239000010935 stainless steel Substances 0.000 claims description 4
- 229910001220 stainless steel Inorganic materials 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 2
- 238000003754 machining Methods 0.000 claims 1
- 238000005304 joining Methods 0.000 abstract description 2
- 230000007704 transition Effects 0.000 abstract 1
- 230000033001 locomotion Effects 0.000 description 8
- 238000003466 welding Methods 0.000 description 5
- 230000008901 benefit Effects 0.000 description 3
- 239000000945 filler Substances 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 229910018100 Ni-Sn Inorganic materials 0.000 description 1
- 229910018532 Ni—Sn Inorganic materials 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000007596 consolidation process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
Images
Classifications
-
- 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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J1/00—Pistons; Trunk pistons; Plungers
- F16J1/01—Pistons; Trunk pistons; Plungers characterised by the use of particular materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
- F15B15/08—Characterised by the construction of the motor unit
- F15B15/14—Characterised by the construction of the motor unit of the straight-cylinder type
- F15B15/1423—Component parts; Constructional details
- F15B15/1447—Pistons; Piston to piston rod assemblies
-
- 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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J10/00—Engine or like cylinders; Features of hollow, e.g. cylindrical, bodies in general
- F16J10/02—Cylinders designed to receive moving pistons or plungers
- F16J10/04—Running faces; Liners
Definitions
- a piston for use in an aircraft actuator to motivate movement of a control surface is provided.
- An aircraft can comprise an actuator for selectively moving a control surface, such as a spoiler, during flight.
- Control-surface movement can be motivated by an actuator comprising a piston and an associated cylinder barrel containing working fluid (e.g., oil).
- the piston can comprise a shaft, a head and a transitional corner therebetween. One end of the shaft is connected (either directly or through linkage) to the control surface and the other end of the shaft is connected to the piston head.
- the piston head is positioned within the barrel and, in response to fluid pressure, slides to thereby push or pull the piston shaft in a linear fashion.
- a piston is provided that provides both stress-free-interface features found in single-piece-piston designs (wherein the entire piston is machined from a solid cylindrical blank) and material-saving advantages afforded by two-piece-piston designs (wherein the shaft blank need not be as radially wide as the head blank).
- the piston is formed from a two-piece piston blank in such a manner that the interface does not intersect with the transitional corner between the shaft and the head. In two-piece-piston designs, this transitional corner is often the area of maximum axial and bending stress as the device performs its pushing and pulling motions. By locating the interface outside this high-stress area, a stronger piston can be provided with conventional materials and without resorting to a single-piece design.
- the pieces of the piston blank can be inertia welded together at the interface.
- the two blank pieces can be rotated relative to each other to generate sufficient heat to energy to plasticize the pieces at the interface and thereby cause consolidation.
- the formation of the interface joint is autogenous and does not require a “filler” material as necessary in conventional welding processes.
- the blank pieces can be made from dissimilar materials (e.g., different metals).
- the blank piece forming the piston's shaft can be made of stainless steel.
- the blank piece forming the outer surface of the piston's head can be made of galling-resistant alloy.
- FIG. 1 is a schematic drawing of an aircraft having a control surface for selective movement during flight.
- FIGS. 2A-2C are schematic drawings of an actuator wherein a piston motivates movement of the control surface.
- FIGS. 3A-3G are various views of a blank (and pieces thereof from which the piston can be formed.
- FIGS. 4A-4B are side and sectional views of the piston.
- an aircraft 10 having spoilers 12 for selective movement during flight. As shown schematically in FIGS. 2A-2C , this movement can be facilitated by an actuator 14 comprising a piston 16 and an associated cylinder barrel 18 , along with linkages 20 and 22 .
- the piston 16 can be formed from a two-piece blank 30 such as is shown in the 3 rd set of drawings.
- the blank 30 can comprise a stem piece 32 and a cap piece 34 joined together at an interface 36 .
- the stem piece 32 need not be as radially wide as the cap piece 34 .
- the stem piece 32 can have an elongated generally cylindrical shape comprising a cap-side axial end 40 and an opposite axial end 42 .
- An interfacing projection 44 is defined by an exterior wall 46 that tapers towards and to the axial end 40 .
- the remaining (“non-interfacing”) portion 48 of the stem piece 32 can be non-tapering.
- the cap piece 34 can have a generally disk-like shape with a stem-side axial face 50 and an opposite axial face 52 .
- An interfacing pocket 54 is defined by an interior wall 56 that tapers away from its stem-side face 50 .
- a basement 58 (or sub-pocket) can be positioned at the floor of the pocket 54 if, for example, it was used during fabrication of the cap piece 34 .
- the stem's projection 44 is positioned within the cap's pocket 54 thereby providing the interface 36 between the exterior wall 46 and the interior wall 56 .
- the stem piece 32 and the cap piece 34 are joined together at this interface 36 , preferably by inertia welding. If the pieces 32 and 34 are joined by inertia welding, the blank 30 (and/or the piston 16 ) can be characterized by the absence of filler material in the interface 36 and/or by the absence of mechanical connections (such as nuts, bolts, etc.).
- the stem piece 32 and the cap piece 34 can be made from dissimilar materials (e.g., dissimilar metals).
- the stem piece can be made stainless steel and/or the cap piece can be made from a gall-resistant alloy (e.g., CU—Ni—Sn alloy, BeCu alloy, Nitronic 60 alloy). While in the illustrated embodiment, the pieces 32 and 34 are essentially solid (except for the pockets 54 / 56 in the cap piece 34 ), cavities or grooves could be formed in the blank pieces prior to joining them together.
- the interface 36 (and thus the walls 46 and 56 ) can have a truncated-cone shape.
- the taper angle can be, for example, between 20° and 40°, and/or between 25° and 35°, and/or about 30°.
- This conical geometry may be compatible with inertia welding steps and/or of the placement of the interface 36 in the completed piston 16 .
- the piston 16 formed from the piston blank 30 is shown.
- the piston 16 comprises a shaft 60 , a head 62 , and a transitional corner 64 therebetween.
- the transitional corner 64 can be considered the stress-critical area of the piston 16 and, significantly, the interface 36 does not intersect this area. Instead, in the illustrated embodiment, the interface 36 is positioned radially outward from the corner 64 on a ledge 66 projecting outward therefrom.
- the piston shaft 60 is formed (e.g., machined) from the non-interfacing portion 48 of the stem piece 32 .
- the piston head 62 is formed (e.g., machined) from the stem's projection 56 and the cap piece 34 .
- the transitional corner 64 is formed only by the stem piece 32 and the outer radial surface of the head 62 is formed only by the cap piece 34 .
- Interior cavities 70 , grooves 72 , attachment nubs 74 , and/or mounting studs 76 can also be formed (e.g., machined) into the pieces 32 and 34 .
- the aircraft 10 the control surface 12 , actuator 14 , the piston 16 , the blank 30 , the pieces 32 / 34 and/or related methods and steps have been shown and described with respect to a certain embodiment or embodiments, it is obvious that equivalent alterations and modifications will occur to others skilled in the art upon the reading and understanding of this specification and the annexed drawings.
- the actuator 14 need not be used in an aircraft
- the piston 16 need not motivate movement of a control surface
- the piston 16 need not be used in an actuator (and/or with a barrel cylinder).
- the piston 16 would be welcomed in many other applications as its advantages transcend aircraft and/or actuator settings.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Pistons, Piston Rings, And Cylinders (AREA)
Abstract
A piston (16) comprising a shaft (60), a head (62) and a transition corner (64) therebetween. The piston (16) can be formed from a two-piece blank with an inertia-welded interface (36) joining the pieces. The interface (36) does not intersect the transitional corner (64) and is instead positioned radially outward therefrom.
Description
- This application claims priority under 35 U.S.C. 119(e) to U.S. Provisional Patent Application No. 60/947,461 filed on Jul. 2, 2007. The entire disclosure of this provisional application is hereby incorporated by reference. If incorporated-by-reference subject matter is inconsistent with subject matter expressly set forth in the written specification and drawings of this application, the present disclosure governs to the extent necessary to eliminate indefiniteness and/or clarity-lacking issues.
- A piston for use in an aircraft actuator to motivate movement of a control surface.
- An aircraft can comprise an actuator for selectively moving a control surface, such as a spoiler, during flight. Control-surface movement can be motivated by an actuator comprising a piston and an associated cylinder barrel containing working fluid (e.g., oil). The piston can comprise a shaft, a head and a transitional corner therebetween. One end of the shaft is connected (either directly or through linkage) to the control surface and the other end of the shaft is connected to the piston head. The piston head is positioned within the barrel and, in response to fluid pressure, slides to thereby push or pull the piston shaft in a linear fashion.
- A piston is provided that provides both stress-free-interface features found in single-piece-piston designs (wherein the entire piston is machined from a solid cylindrical blank) and material-saving advantages afforded by two-piece-piston designs (wherein the shaft blank need not be as radially wide as the head blank). The piston is formed from a two-piece piston blank in such a manner that the interface does not intersect with the transitional corner between the shaft and the head. In two-piece-piston designs, this transitional corner is often the area of maximum axial and bending stress as the device performs its pushing and pulling motions. By locating the interface outside this high-stress area, a stronger piston can be provided with conventional materials and without resorting to a single-piece design.
- Additionally or alternatively, the pieces of the piston blank can be inertia welded together at the interface. Specifically, for example, the two blank pieces can be rotated relative to each other to generate sufficient heat to energy to plasticize the pieces at the interface and thereby cause consolidation. The formation of the interface joint is autogenous and does not require a “filler” material as necessary in conventional welding processes.
- One significant advantage of inertia welding is that the blank pieces can be made from dissimilar materials (e.g., different metals). For example, the blank piece forming the piston's shaft can be made of stainless steel. And the blank piece forming the outer surface of the piston's head can be made of galling-resistant alloy. By making the piston-head material inherently resistant, conventional (and expensive and troublesome) coatings and platings can be eliminated.
- These and other features of the piston blank, the blank pieces, and/or the piston are fully described and particularly pointed out in the claims. The following description and annexed drawings set forth in detail certain illustrative embodiments, these embodiments being indicative of but a few of the various ways in which the principles may be employed.
-
FIG. 1 is a schematic drawing of an aircraft having a control surface for selective movement during flight. -
FIGS. 2A-2C are schematic drawings of an actuator wherein a piston motivates movement of the control surface. -
FIGS. 3A-3G are various views of a blank (and pieces thereof from which the piston can be formed. -
FIGS. 4A-4B are side and sectional views of the piston. - Referring now to the drawings, and initially to
FIG. 1 , anaircraft 10 is shown havingspoilers 12 for selective movement during flight. As shown schematically inFIGS. 2A-2C , this movement can be facilitated by anactuator 14 comprising apiston 16 and an associatedcylinder barrel 18, along withlinkages - The
piston 16 can be formed from a two-piece blank 30 such as is shown in the 3rd set of drawings. The blank 30 can comprise astem piece 32 and acap piece 34 joined together at aninterface 36. Thestem piece 32 need not be as radially wide as thecap piece 34. - The
stem piece 32 can have an elongated generally cylindrical shape comprising a cap-sideaxial end 40 and an oppositeaxial end 42. Aninterfacing projection 44 is defined by anexterior wall 46 that tapers towards and to theaxial end 40. The remaining (“non-interfacing”)portion 48 of thestem piece 32 can be non-tapering. - The
cap piece 34 can have a generally disk-like shape with a stem-sideaxial face 50 and an oppositeaxial face 52. Aninterfacing pocket 54 is defined by aninterior wall 56 that tapers away from its stem-side face 50. A basement 58 (or sub-pocket) can be positioned at the floor of thepocket 54 if, for example, it was used during fabrication of thecap piece 34. - The stem's
projection 44 is positioned within the cap'spocket 54 thereby providing theinterface 36 between theexterior wall 46 and theinterior wall 56. Thestem piece 32 and thecap piece 34 are joined together at thisinterface 36, preferably by inertia welding. If thepieces interface 36 and/or by the absence of mechanical connections (such as nuts, bolts, etc.). - The
stem piece 32 and thecap piece 34 can be made from dissimilar materials (e.g., dissimilar metals). For example, the stem piece can be made stainless steel and/or the cap piece can be made from a gall-resistant alloy (e.g., CU—Ni—Sn alloy, BeCu alloy, Nitronic 60 alloy). While in the illustrated embodiment, thepieces pockets 54/56 in the cap piece 34), cavities or grooves could be formed in the blank pieces prior to joining them together. - The interface 36 (and thus the
walls 46 and 56) can have a truncated-cone shape. The taper angle can be, for example, between 20° and 40°, and/or between 25° and 35°, and/or about 30°. This conical geometry may be compatible with inertia welding steps and/or of the placement of theinterface 36 in the completedpiston 16. - Referring now to
FIGS. 4A and 4B , thepiston 16 formed from the piston blank 30 is shown. Thepiston 16 comprises ashaft 60, ahead 62, and atransitional corner 64 therebetween. Thetransitional corner 64 can be considered the stress-critical area of thepiston 16 and, significantly, theinterface 36 does not intersect this area. Instead, in the illustrated embodiment, theinterface 36 is positioned radially outward from thecorner 64 on a ledge 66 projecting outward therefrom. - The
piston shaft 60 is formed (e.g., machined) from thenon-interfacing portion 48 of thestem piece 32. Thepiston head 62 is formed (e.g., machined) from the stem'sprojection 56 and thecap piece 34. Thetransitional corner 64 is formed only by thestem piece 32 and the outer radial surface of thehead 62 is formed only by thecap piece 34.Interior cavities 70,grooves 72,attachment nubs 74, and/ormounting studs 76 can also be formed (e.g., machined) into thepieces - Although the
aircraft 10, thecontrol surface 12,actuator 14, thepiston 16, the blank 30, thepieces 32/34 and/or related methods and steps have been shown and described with respect to a certain embodiment or embodiments, it is obvious that equivalent alterations and modifications will occur to others skilled in the art upon the reading and understanding of this specification and the annexed drawings. For example, theactuator 14 need not be used in an aircraft, thepiston 16 need not motivate movement of a control surface, and/or thepiston 16 need not be used in an actuator (and/or with a barrel cylinder). In fact, thepiston 16 would be welcomed in many other applications as its advantages transcend aircraft and/or actuator settings. - In regard to the various functions performed by the above described elements (e.g., components, assemblies, systems, devices, compositions, etc.), the terms (including a reference to a “means”) used to describe such elements are intended to correspond, unless otherwise indicated, to any element which performs the specified function of the described element (i.e., that is functionally equivalent), even though not structurally equivalent to the disclosed structure which performs the function. In addition, while a particular feature of the invention may have been described above with respect to only one or more of several illustrated embodiments, such feature may be combined with one or more other features of the other embodiments, as may be desired and advantageous for any given or particular application.
Claims (20)
1. A piston blank comprising:
a stem piece having a cap-side axial end and a projection defined by an exterior wall that tapers to its cap-adjacent axial end; and
a cap piece having a stem-side axial face and a pocket defined by an interior wall tapering from its stem-adjacent axial face;
wherein the stem projection is positioned within the cap pocket thereby providing an interface between the projection-defining exterior wall and the pocket-defining interior wall; and
wherein the stem piece and the cap piece are joined together at this interface.
2. A piston blank as set forth in claim 1 , wherein the stem piece and the cap piece are inertia welded together at this interface.
3. A piston blank as set forth in claim 2 , wherein the stem piece and the cap piece are made from dissimilar materials.
4. A piston blank as set forth in claim 3 , wherein the stem piece and the cap piece are made from dissimilar metals.
5. A piston blank as set forth in claim 4 , wherein the stem piece is made from stainless steel.
6. A piston blank as set forth in claim 5 , wherein the cap piece is made from a gall-resistant alloy.
7. A piston blank as set forth in claim 2 , wherein the interface has a truncated-cone shape.
8. A piston formed from the piston blank set forth in claim 1 , the piston comprising:
a shaft, a head, and a transitional corner therebetween; wherein:
a shaft formed from a non-pocketed portion of the stem piece;
a head formed from the cap-interfacing projection of the stem piece and the cap piece; and
a transitional corner between the shaft and the head;
wherein the interface does not intersect with this transitional corner.
9. A piston as set forth in claim 8 , wherein the transitional corner is formed only by the stem piece.
10. A piston as set forth in claim 9 , wherein the head forms a ledge projecting radially outward from the transitional corner and surrounding the shaft, and wherein the interface intersects with the ledge radially outward from the transitional corner.
11. A piston as set forth in claim 10 , wherein the stem piece and the cap piece are inertia welded together at the interface.
12. A piston as set forth in claim 11 , wherein the stem piece and the cap piece are made from dissimilar materials.
13. A piston as set forth in claim 12 , wherein the stem piece and the cap piece are made from dissimilar metals.
14. A piston as set forth in claim 13 , wherein the stem piece is made from stainless steel.
15. A piston as set forth in claim 13 , wherein the cap piece is made from a gall-resistant alloy.
16. A piston as set forth in claim 11 , wherein the interface has a truncated-cone shape.
17. A method of making a piston from the piston blank set forth in claim 1 , said method comprising the steps of:
forming a shaft from a non-pocketed portion of the stem piece; and
forming a head from the stem projection and the cap piece;
wherein said forming steps are performed such that the interface does not intersect with a transitional corner between the shaft and the head.
18. A method as set forth in claim 1 , wherein said forming steps comprise machining the stem piece and the cap piece.
19. A method as set forth in claim 18 , wherein said forming steps are performed such that the head forms a ledge projecting radially outward from the transitional corner and surrounding the shaft, and wherein the interface intersects with the ledge radially outward from the transitional corner.
20. An aircraft hydraulic actuator comprising the piston set forth in claim 8 .
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/166,543 US20090007774A1 (en) | 2007-07-02 | 2008-07-02 | Aircraft actuator piston |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US94746107P | 2007-07-02 | 2007-07-02 | |
US12/166,543 US20090007774A1 (en) | 2007-07-02 | 2008-07-02 | Aircraft actuator piston |
Publications (1)
Publication Number | Publication Date |
---|---|
US20090007774A1 true US20090007774A1 (en) | 2009-01-08 |
Family
ID=40220445
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/166,543 Abandoned US20090007774A1 (en) | 2007-07-02 | 2008-07-02 | Aircraft actuator piston |
Country Status (1)
Country | Link |
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US (1) | US20090007774A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105509992A (en) * | 2015-11-27 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | External store model system excitation method for flutter wind tunnel test |
US10520012B1 (en) | 2015-04-14 | 2019-12-31 | Roller Bearing Company Of America, Inc. | Rod end having wear mitigation features for an augmenter nozzle on a jet engine turbine |
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US2216987A (en) * | 1936-11-17 | 1940-10-08 | Waterbury Tool Co | Power transmission |
US3263311A (en) * | 1964-02-21 | 1966-08-02 | Brueninghaus Gmbh Stahlwerke | Process for assembling pistons and connecting rods of axial piston machines |
US3485143A (en) * | 1967-10-09 | 1969-12-23 | Caterpillar Tractor Co | Friction welded internally cooled piston |
US3609840A (en) * | 1967-10-09 | 1971-10-05 | Caterpillar Tractor Co | Process for frictionally welding an internally cooled piston |
US3631585A (en) * | 1966-10-17 | 1972-01-04 | North American Rockwell | Method of making a friction-welded drive axle shaft having an annular section of flash metal |
US4087038A (en) * | 1975-12-19 | 1978-05-02 | Harima Sargyo Kabushiki Kaisha | Frictional welding method |
US4651631A (en) * | 1984-05-30 | 1987-03-24 | Ae Plc | Manufacture of pistons |
US5259294A (en) * | 1951-03-27 | 1993-11-09 | Ringsdorff-Werke Gmbh | Shock-absorbing piston made up of dissimilar joined parts, blank for the piston and method for manufacturing the piston |
US5309818A (en) * | 1990-10-18 | 1994-05-10 | Metal Leve S/A Industria E. Comercio | Method for the manufacture of a cooled piston |
US5477771A (en) * | 1993-08-10 | 1995-12-26 | Black; Philip B. | Hydraulic cylinder assembly |
US6279455B1 (en) * | 1998-10-06 | 2001-08-28 | Caterpillar Inc. | Method and apparatus for making a two piece unitary piston |
US6431051B1 (en) * | 2000-03-31 | 2002-08-13 | Sauer-Danfoss Inc. | Closed cavity hydraulic piston and method of making the same |
US6491206B2 (en) * | 2000-11-27 | 2002-12-10 | Sauer-Danfoss, Inc. | Method of making closed cavity pistons |
US6780525B2 (en) * | 2001-12-26 | 2004-08-24 | The Boeing Company | High strength friction stir welding |
US7513191B2 (en) * | 2006-01-10 | 2009-04-07 | Ls Mtron Ltd. | Piston head for hydraulic injection molding machine |
-
2008
- 2008-07-02 US US12/166,543 patent/US20090007774A1/en not_active Abandoned
Patent Citations (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2216987A (en) * | 1936-11-17 | 1940-10-08 | Waterbury Tool Co | Power transmission |
US5259294A (en) * | 1951-03-27 | 1993-11-09 | Ringsdorff-Werke Gmbh | Shock-absorbing piston made up of dissimilar joined parts, blank for the piston and method for manufacturing the piston |
US3263311A (en) * | 1964-02-21 | 1966-08-02 | Brueninghaus Gmbh Stahlwerke | Process for assembling pistons and connecting rods of axial piston machines |
US3631585A (en) * | 1966-10-17 | 1972-01-04 | North American Rockwell | Method of making a friction-welded drive axle shaft having an annular section of flash metal |
US3485143A (en) * | 1967-10-09 | 1969-12-23 | Caterpillar Tractor Co | Friction welded internally cooled piston |
US3609840A (en) * | 1967-10-09 | 1971-10-05 | Caterpillar Tractor Co | Process for frictionally welding an internally cooled piston |
US4087038A (en) * | 1975-12-19 | 1978-05-02 | Harima Sargyo Kabushiki Kaisha | Frictional welding method |
US4651631A (en) * | 1984-05-30 | 1987-03-24 | Ae Plc | Manufacture of pistons |
US5309818A (en) * | 1990-10-18 | 1994-05-10 | Metal Leve S/A Industria E. Comercio | Method for the manufacture of a cooled piston |
US5477771A (en) * | 1993-08-10 | 1995-12-26 | Black; Philip B. | Hydraulic cylinder assembly |
US6279455B1 (en) * | 1998-10-06 | 2001-08-28 | Caterpillar Inc. | Method and apparatus for making a two piece unitary piston |
US6431051B1 (en) * | 2000-03-31 | 2002-08-13 | Sauer-Danfoss Inc. | Closed cavity hydraulic piston and method of making the same |
US6491206B2 (en) * | 2000-11-27 | 2002-12-10 | Sauer-Danfoss, Inc. | Method of making closed cavity pistons |
US6588321B1 (en) * | 2000-11-27 | 2003-07-08 | Sauer-Danfoss Inc. | Closed cavity piston and method of making the same |
US6780525B2 (en) * | 2001-12-26 | 2004-08-24 | The Boeing Company | High strength friction stir welding |
US7513191B2 (en) * | 2006-01-10 | 2009-04-07 | Ls Mtron Ltd. | Piston head for hydraulic injection molding machine |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10520012B1 (en) | 2015-04-14 | 2019-12-31 | Roller Bearing Company Of America, Inc. | Rod end having wear mitigation features for an augmenter nozzle on a jet engine turbine |
CN105509992A (en) * | 2015-11-27 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | External store model system excitation method for flutter wind tunnel test |
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