US20180266478A1 - Anti-Rotation for Eccentric Bushings - Google Patents
Anti-Rotation for Eccentric Bushings Download PDFInfo
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- US20180266478A1 US20180266478A1 US15/986,046 US201815986046A US2018266478A1 US 20180266478 A1 US20180266478 A1 US 20180266478A1 US 201815986046 A US201815986046 A US 201815986046A US 2018266478 A1 US2018266478 A1 US 2018266478A1
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- Prior art keywords
- fitting
- eccentric bushing
- coating
- friction washer
- eccentric
- Prior art date
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- Abandoned
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- 238000000576 coating method Methods 0.000 claims abstract description 68
- 239000011248 coating agent Substances 0.000 claims abstract description 67
- 239000010432 diamond Substances 0.000 claims abstract description 23
- 229910003460 diamond Inorganic materials 0.000 claims abstract description 21
- 238000000034 method Methods 0.000 claims abstract description 19
- 125000006850 spacer group Chemical group 0.000 claims description 9
- 239000000314 lubricant Substances 0.000 abstract description 5
- 230000008901 benefit Effects 0.000 description 8
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
Images
Classifications
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- 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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B43/00—Washers or equivalent devices; Other devices for supporting bolt-heads or nuts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/18—Floors
-
- 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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B2/00—Friction-grip releasable fastenings
- F16B2/005—Means to increase the friction-coefficient
-
- 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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
- F16B5/02—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread
- F16B5/0216—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread the position of the plates to be connected being adjustable
- F16B5/0225—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread the position of the plates to be connected being adjustable allowing for adjustment parallel to the plane of the plates
-
- 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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B33/00—Features common to bolt and nut
- F16B33/002—Means for preventing rotation of screw-threaded elements
Definitions
- the embodiments described herein relate to a system and method of using an attachment system comprising eccentric bushings and coated friction washers, the coating on the friction washers prohibiting rotation of the bushings with respect to a fitting.
- Eccentric bushings may be used to connect bolted joints.
- the eccentric bushings permit the alignment of each side of the joint even when the holes through the fittings of the joint may not be perfectly aligned.
- shear loads applied to the bushings may have a tendency to rotate the bushings due to their eccentricity.
- the bushing may include splined teeth on the exterior of the bushing.
- a lock plate may be positioned around the circumference of the bushing that includes splined teeth configured to engage the teeth of the bushings.
- the lock plate is configured to engage a stop lock on the fitting that prohibits the rotation of the lock plate.
- the mating teeth between the lock plate and the bushing prohibits the rotation of the bushing.
- splined teeth increases the manufacturing cost for the components.
- the splined teeth also may increase the installation time required to connect bolted joints especially if a large number of joints need to be connected.
- an aircraft may include over forty (40) beam and frame fittings that need to be connected.
- the teeth of a bushing need to be lined up with the teeth on the lock plate.
- the lock plate needs to be aligned so that a portion of the lock engages a lock stop on the fitting, which may add to the difficulty of installing the components.
- Other disadvantages of using an eccentric bushing and lock plate with splined teeth may exist.
- the present disclosure is directed to a method and system that overcomes some of the problems and disadvantages discussed above.
- One embodiment is an attachment system comprising a first fitting having a first hole and a second fitting having a second hole, the second fitting positioned adjacent to the first fitting.
- the system comprises first and second eccentric bushings, a portion of the first eccentric bushing positioned within the first hole of the first fitting and a portion of the second eccentric bushing positioned within the second hold of the second fitting.
- the system comprises a first friction washer positioned between a portion of the first eccentric bushing and the first fitting, the first friction washer comprising a coating on an exterior.
- the system comprises a second friction washer positioned between a portion of the second eccentric bushing and the second fitting, the second friction washer comprising a coating on an exterior. The coating on the first friction washer prohibits rotation of the first eccentric bushing with respect to the first fitting and the coating on the second friction washer prohibits rotation of the second eccentric bushing with respect to the second fitting.
- the second eccentric bushing may be positioned within the first eccentric bushing with the second friction washer positioned between a portion of the second eccentric bushing and a portion of the first eccentric bushing.
- the second friction washer may comprise a coating on an exterior, wherein the coating on the second friction washer may prohibit rotation of the second eccentric bushing with respect to the first eccentric bushing.
- the coating on the first and second friction washers may be a nickel-diamond coating.
- the attachment system may comprise at least four attachment points between an aircraft floor and an aircraft fuselage. Each of the attachment points may comprise a first fitting having a first hole, a second fitting having a second hole, the second fitting positioned adjacent to the first fitting. Each of the attachment points may comprise first and second eccentric bushings, a portion of the first eccentric bushing positioned within the first hole of the first fitting and a portion of the second eccentric bushing positioned within the second hold of the second fitting. Each of the attachment points may comprise a first friction washer positioned between a portion of the first eccentric bushing and the first fitting, the first friction washer comprising a coating on an exterior.
- Each of the attachment points may comprise a second friction washer positioned between a portion of the second eccentric bushing and the second fitting, the second friction washer comprising a coating on an exterior.
- the coating on the first friction washer prohibits rotation of the first eccentric bushing with respect to the first fitting and the coating on the second friction washer prohibits rotation of the second eccentric bushing with respect to the second fitting.
- the diamond concentration of the coating may be between about 8% and 30%.
- the coating on the first and second friction washers may be approximately 6 microns to 22 microns thick.
- the coating on the first and second friction washers may have a coefficient of friction of 0.5 or greater when lubricated.
- the first fitting may be a frame fitting connected to a fuselage of an aircraft and the second fitting may be a beam fitting connected to a floor of the aircraft.
- the system may include a spacer positioned between the first and second fittings.
- the system may include a first lock plate positioned around a circumference of the first friction washer and a second lock plate positioned around a circumference of the second friction washer.
- the system may include a first lock stop on the first fitting and a second lock stop on the second fitting, wherein the first lock plate may engage the first lock stop and the second lock plate may engage the second lock stop.
- One embodiment is an attachment system comprising a first fitting have a first hole and a second fitting having a second hole, the second fitting positioned adjacent to the first fitting.
- the system comprises a first eccentric bushing and a second eccentric bushing. A portion of the first eccentric bushing is positioned within the first hole of the first fitting and a portion of the second eccentric bushing is positioned within the second hole of the second fitting.
- the first eccentric bushing comprising a coating on an exterior, wherein the coating prohibits rotation of the first bushing with respect to the first fitting.
- the second eccentric bushing comprising a coating on an exterior, wherein the coating prohibits rotation of the second bushing within respect to the second fitting.
- the coating on the first and second eccentric bushings may be a nickel-diamond coating.
- the diamond concentration of the coating may be between about 8% and 30%.
- the coating on the first and second bushings may be approximately 6 microns to 22 microns thick.
- the coating on the first and second bushings may have a coefficient of friction of 0.5 or greater when lubricated.
- the first fitting may be a frame fitting connected to a fuselage of an aircraft and the second fitting may be a beam fitting connected to a floor of the aircraft.
- the system may include a spacer positioned between the first and second fittings.
- One embodiment is a method comprising positioning a portion of a first eccentric bushing within a first hole of a first fitting and positioning a portion of a second eccentric bushing within a second hole of a second fitting.
- the method comprises positioning a first friction washer between a portion of the first eccentric bushing and the first fitting, wherein an exterior of the first friction washer comprises a nickel-diamond coating.
- the method comprises positioning a second friction washer between a portion of the second eccentric bushing and the second fitting, wherein an exterior of the second friction washer comprises a nickel-diamond coating.
- the method may comprise rotating the first and second eccentric bushing to align an opening in the first eccentric bushing with an opening in the second eccentric bushing.
- the method may comprise positioning a first lock plate around a circumference of the first friction washer and engaging the first lock plate with a lock stop on the first fitting.
- the method may comprise positioning a second lock plate around a circumference of the second friction washer and engaging the second lock plate with a lock stop on the second fitting.
- the first fitting may comprise a frame fitting connected to a fuselage of an aircraft and the second fitting may comprise a beam fitting connected to a floor of the aircraft.
- the method may comprise positioning a spacer between the first fitting and the second fitting.
- FIG. 1 shows an embodiment of an attachment system with an eccentric bushing and a coated friction washer.
- FIG. 2 shows the embodiment of FIG. 1 with a portion of the eccentric bushing positioned within a fitting.
- FIG. 3 shows the embodiment of FIG. 1 with a portion of the eccentric bushing positioned within a fitting and a fastener positioned adjacent the eccentric bushing.
- FIG. 4 is an embodiment of an eccentric bushing.
- FIG. 5 is an embodiment of a lock plate.
- FIG. 6 is an embodiment of a coated friction washer.
- FIGS. 7A-7C show the rotation of two eccentric bushings to align holes within the bushing.
- FIG. 8 is a schematic cross-section view of one embodiment of an attachment system.
- FIG. 9 is a schematic cross-section view of one embodiment of an attachment system.
- FIG. 10 is a schematic cross-section view of one embodiment of an attachment system.
- FIG. 11 is a schematic cross-section view of one embodiment of an attachment system showing a coated friction washer positioned between a lock plate and a portion of an eccentric bushing.
- FIG. 12 shows a schematic of one embodiment of an attachment system connecting the floor of an aircraft to the fuselage of the aircraft at multiple attachment points.
- FIG. 13 shows one embodiment of a prior attachment system that utilizes teeth to prohibit rotation between the bushing and the fitting.
- FIG. 14 shows a schematic cross-section view of one embodiment of an attachment system showing a coated friction washer positioned between an eccentric bushing and a fitting and a second coated friction washer positioned between two eccentric bushings.
- FIG. 15 shows a schematic front view of the attachment system of claim 14 .
- eccentric bushings may be configured with teeth to prohibit the rotation of the eccentric bushing with respect to a fitting.
- FIG. 13 shows a prior attachment system 400 for the connection of a first fitting 410 and a second fitting 420 .
- Eccentric bushings 430 (only one is shown in FIG. 13 ) are used to align the openings in the two fittings 410 and 420 as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure.
- a fastener (not shown) may be inserted into the opening 431 of the bushings 430 to secure the fittings 410 and 420 .
- the perimeter of the eccentric bushings 430 includes a plurality of teeth 432 that may be used to prohibit the rotation of the bushing 430 as described herein.
- a lock plate 450 is positioned around the perimeter of the bushing 430 .
- the lock plate 450 includes a central opening 451 having a plurality of teeth 453 , which are configured to engage the teeth 432 along the perimeter of the bushing 430 .
- the lock plate 450 includes a notch 452 that is configured to engage a lock stop 412 of the fitting 410 .
- the lock stop 412 prohibits the rotation of the lock plate 450 when the notch is engaged with the lock stop 412 .
- the teeth 453 of the lock plate 450 then prohibit the rotation of the bushing 430 when engaged with the teeth 432 of the bushing 430 .
- the installation of the bushing 430 and lock plate 450 require the alignment of the teeth, which can be time consuming. Further, the notch 452 of the lock plate 450 has to be aligned with the lock stop 412 of the fitting 410 , which may also increase the time required to install the attachment system 400 especially if there are a large number of fittings 410 and 420 that need to be connected together. In an aircraft, there may be 40 or more connections required to connect the floor beams to the fuselage frame. The intricate teeth on the components also increase the cost of the individual parts for the attachment system 400 . It would be beneficial to provide an attachment system that can be installed in less time, with less difficulty, and/or use less expensive parts.
- FIG. 1 shows one embodiment of an attachment system 100 that includes a first fitting 10 and a second fitting 20 each that include an opening 11 and 21 (shown in FIG. 8 ).
- An eccentric bushing 30 having an opening 31 may be inserted into the opening 11 in the first fitting 10 .
- a second eccentric bushing 30 may be inserted into the opening 21 of the second fitting as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure.
- a coated friction washer 40 is positioned between at least a portion of the eccentric bushing 30 and the first fitting 10 .
- the coated friction washer 40 is coated with a coating that prohibits the rotation of the bushing 30 with respect to the fitting 10 .
- “prohibits” means significantly or substantially inhibiting the rotation and/or movement of, including, but not limited to, completely preventing rotation and/or movement.
- a coated friction washer 40 may also be positioned between a second bushing 30 and the second fitting 20 to prohibit the rotation of the second bushing 30 with respect to the second fitting 20 .
- the first fitting 10 may be a frame fitting connected to the fuselage of an aircraft and the second fitting 20 may be a beam fitting connected to a floor of the aircraft.
- the attachment system 100 may be used to connect the floor beam to frame fittings of an aircraft.
- the components such as the bushing 30 does not include teeth and thus, may be installed more quickly and/or may be produced at a lower cost than the components of attachment systems that utilize teeth to prohibit rotation.
- the coating on the friction washer 40 is used to provide a high friction interface between the fittings 10 and 20 and the eccentric bushing 30 .
- the coating on the friction washer 40 may be a nickel-diamond coating that prohibits the rotation of the bushing 30 .
- the nickel-diamond coating may have a diamond concentration of between approximately 8-30%.
- the coating on the friction washer 40 may have a thickness of between approximately 6 microns and 22 microns.
- the coating may be EKAGRIP commercially offered by 3M of St. Paul, Minn.
- the coating on the friction washer 40 may ensure that the friction washer 40 has a coefficient of friction of 0.5 or greater even when lubricant, such as an oil film, is present on the surface of the friction washer 40 .
- FIG. 2 shows a portion of the bushing 30 positioned within the opening 11 of the fitting 10 with the coated friction washer 40 positioned between at least a portion of the bushing 30 and the fitting 10 .
- a lock plate 50 is positioned around the perimeter of the bushing 30 .
- the lock plate 50 is configured to engage a lock stop 12 of the fitting 10 .
- FIG. 3 shows a fastener 70 that may be used to fasten the first fitting 10 and the second fitting 20 together through the openings 31 in the two eccentric bushings 30 .
- FIG. 3 also shows that a spacer 60 may be positioned between the first and second fittings 10 and 20 .
- FIG. 4 shows one embodiment of an eccentric bushing 30 with an opening 31 .
- the use of eccentric bushings 30 permits the alignment of two holes by the rotation of the two eccentric bushings 30 as described herein in regards to FIGS. 7A-7C .
- FIG. 5 shows one embodiment of a lock plate 50 having a central opening 51 and a notch 52 configured to engage a lock stop 12 or 22 (shown in FIG. 8 ) on a fitting 10 or 20 (shown in FIG. 8 ).
- the lock stop 12 or 22 may be integral to the fitting 10 or 20 or may be a separate member connected to the fitting 10 or 20 as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure.
- FIG. 6 shows an embodiment of a coated friction washer 40 having an opening 41 .
- FIG. 11 shows a schematic of a friction washer 40 positioned between a lock plate 50 and an eccentric bushing 30 .
- the friction washer 40 includes a core 44 that is covered with a coating 42 that provides a high coefficient of friction between the friction washer 40 and the adjacent components, which in FIG. 11 may be a lock plate 50 and an eccentric bushing 30 .
- the coating 42 may be a nickel-diamond coating, which includes diamonds 43 within the coating 42 as shown in FIG. 11 .
- the diamonds 43 provide friction to prohibit the rotation of the friction washer 40 and adjoining components, such as an eccentric bushing 30 and a lock plate 50 , even if covered in a layer of grease or oil. Friction washer 40 is shown in FIG.
- a nickel-diamond coating 42 for illustrative purposes only.
- Various coatings 42 may be used to provide an interface between the components that prohibits rotation and/more movement between the components as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. Additionally, the coating 42 could be applied to the other components in addition or instead of the friction washer 40 as would be appreciated by one of ordinary skill in the art and as disclosed herein.
- FIGS. 7A-7C show the rotation of two eccentric bushings to align holes 31 within the bushings 30 .
- FIG. 7A shows a first eccentric bushing 30 A having an opening 31 A and a second eccentric bushing 30 B having an opening 31 B.
- the bushings 30 A and 30 B may be rotated as indicated by the arrows.
- FIG. 7B shows the bushings 30 A and 30 B rotated with respect to FIG. 7A , but the openings 31 A and 31 B are not yet aligned.
- FIG. 7C shows bushings 30 A and 30 B that have been rotated until the openings 31 A and 31 B are aligned.
- the use of eccentric bushings 30 permit the alignment of openings so fasteners may be inserted and connect fittings that may have openings slightly out of alignment due to acceptable tolerances.
- FIG. 8 shows a schematic cross-section of an attachment system 100 that includes a first fitting 10 and a second fitting 20 each that include an opening 11 and 21 .
- a first eccentric bushing 30 A has been inserted into the opening 11 of the first fitting 10 and a second eccentric bushing 30 B has been inserted into the opening 21 of the second fitting 20 .
- the system 100 may include a spacer 60 positioned between the first and second fittings 10 and 20 .
- one or both of the eccentric bushings 30 A and 30 B may be rotated until openings 31 A and 31 B of the eccentric bushings 30 A and 30 B are aligned.
- a first coated friction washer 40 A may be positioned between a portion, such as the head, of the first eccentric bushing 30 A and the a first lock plate 50 A and a second coated friction washer 40 B may be positioned between a portion, such as the head, of the second eccentric bushing 30 B and a second lock plate 50 B.
- the first lock plate 50 A may engage a lock stop 12 on the first fitting 10 that prohibits the rotation of the first lock plate 50 A.
- the second lock plate 50 B may engage a lock stop 22 on the second fitting 20 that prohibits the rotation of the second lock plate 50 B.
- the coating on the friction washers 40 A and 40 B and engagement of the first and second lock plates 50 A and 50 B may prohibit the rotation of the eccentric bushings 30 A and 30 B with respect to the fittings 10 and 20 .
- the coating may be nickel-diamond which will provide a sufficient coefficient of friction on the interfaces of the friction washers 40 A and 40 B even in the presence of a lubricant.
- the bushings 30 A and 30 B are eccentric may be used to align holes in two fittings.
- the attachment system 100 may be used to attach a floor to a fuselage of an aircraft.
- One or more corners of attachment points between the floor and the fuselage may be aligned and not require the use of eccentric bushings 30 .
- the eccentric bushings 30 may need to be used to align the fitting holes.
- FIG. 9 shows a schematic cross-section of an attachment system 200 that includes a first fitting 110 and a second fitting 120 each that include an opening 111 and 121 .
- a first eccentric bushing 130 A has been inserted into the opening 111 of the first fitting 110 and a second eccentric bushing 130 B has been inserted into the opening 121 of the second fitting 120 .
- the system 200 may include a spacer 160 positioned between the first and second fittings 110 and 120 .
- one or both of the eccentric bushings 130 A and 130 B may be rotated until openings 131 A and 131 B of the eccentric bushings 130 A and 130 B are aligned.
- a first coated friction washer 140 A may be positioned between a portion, such as the head, of the first eccentric bushing 130 A and the first fitting 110 and a second coated friction washer 140 B may be positioned between a portion, such as the head, of the second eccentric bushing 130 B and the second fitting 120 .
- the coating on the friction washers 140 A and 140 B may prohibit the rotation of the eccentric bushings 130 A and 130 B with respect to the fittings 110 and 120 .
- the coating may be nickel-diamond which will provide a sufficient coefficient of friction on the interfaces of the friction washers 140 A and 140 B even in the presence of a lubricant.
- the bushings 130 A and 130 B are eccentric may be used to align holes in two fittings.
- the attachment system 200 may be used to attach a floor to a fuselage of an aircraft.
- One or more corners of attachment points between the floor and the fuselage may be aligned and not require the use of eccentric bushings 130 .
- the eccentric bushings 130 may need to be used to align the fitting holes.
- FIG. 10 shows a schematic cross-section of an attachment system 300 that includes a first fitting 210 and a second fitting 220 each that include an opening 211 and 221 .
- a first eccentric bushing 230 A has been inserted into the opening 211 of the first fitting 210 and a second eccentric bushing 230 B has been inserted into the opening 221 of the second fitting 220 .
- the system 300 may include a spacer 260 positioned between the first and second fittings 210 and 220 .
- one or both of the eccentric bushings 230 A and 230 B may be rotated until openings 231 A and 231 B of the eccentric bushings 230 A and 230 B are aligned.
- Each of the eccentric bushings 230 A and 230 B may include a coating on its exterior interfacing surfaces, thrust or radial, that prohibits the rotation of the bushings 230 A and 230 B respect to the fittings 210 and 220 .
- the coating may be nickel-diamond which will provide a sufficient coefficient of friction on the interfaces of the bushings 230 A and 230 B even in the presence of a lubricant.
- the bushings 230 A and 230 B are eccentric may be used to align holes in two fittings.
- the attachment system 300 may be used to attach a floor to a fuselage of an aircraft.
- One or more corners of attachment points between the floor and the fuselage may be aligned and not require the use of eccentric bushings 230 .
- the eccentric bushings 230 may need to be used to align the fitting holes.
- FIG. 12 shows a schematic of an attachment system 100 connecting the floor 1 of an aircraft to the fuselage 2 of the aircraft.
- Stanchions 3 may provide additional connection points between the floor 1 and the fuselage 2 .
- the schematic of FIG. 12 shows an attachment system 100 A connecting the floor 1 to the fuselage 2 at a left front corner of the floor 1 and attachment system 100 B connecting the floor 1 to the fuselage 2 at a right front corner of the floor 1 .
- a plurality of attachment systems may connect the floor 1 to the fuselage 2 along the length of the floor 1 between the front and rear corners of the floor 1 as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure.
- Various embodiments of attachment systems disclosed herein may be used to connect the floor 1 to the fuselage 2 .
- the combination of eccentric bushings and friction washers may not be necessary at each attachment point along the length of the floor.
- the fitting holes of the floor and fuselage may be aligned at the midpoint of the floor not requiring the eccentric bushings to be rotated for alignment of the holes.
- the eccentric bushings in combination with the friction washers disclosed herein may be used to align the fitting holes between the floor and the fuselage.
- the initial attachment points between the floor and the fuselage may be aligned and not require the use of eccentric bushings and non-eccentric bushings may be used, or if eccentric bushings are used in the connection assembly, the eccentric bushings may not need to be rotated to align the fastener openings.
- the fastener openings may move out of alignment necessitating the use of eccentric bushings that may be rotated to align the openings as discussed herein.
- the non-eccentric bushings and/or eccentric bushings may be coated with nickel-diamond to prohibit rotation and/or nickel-diamond coated washers may be used to prohibit rotation of the eccentric bushings.
- FIG. 12 shows the use of the attachment systems disclosed herein to attach a floor to a fuselage for illustrative purposes only.
- the disclosed attachment systems may be used to secure various assemblies and not just the floor to a fuselage as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure.
- the eccentric bushings and coated friction washers permit the alignment of holes between various fittings while ensuring a tight connection. Attachment systems utilizing eccentric bushings and coated friction washers may reduce or eliminate the need to drill match holes in components during the assembly process, which may reduce the time and cost during assembly.
- FIG. 14 shows a schematic cross-section of an attachment system 500 that includes a first fitting 510 and a second fitting 520 .
- FIG. 14 shows the first fitting 510 being adjacent to the second fitting 520 for illustrative purposes only as the two fittings 510 and 520 could be separate by one or more elements as would be appreciated by one of ordinary skill in the art.
- a lug having a fastener opening could be positioned between the first and second fittings 510 and 520 .
- a first eccentric bushing 530 has been inserted into the opening of the first fitting 510 with a first coated friction washer 540 positioned between the first eccentric bushing 530 and the first fitting 510 .
- the coated friction washer 540 prohibits the rotation of the first eccentric bushing 530 with respect to the first fitting 510 as discussed herein.
- the bushings 530 and 535 may include a friction coating on their exterior interfacing surfaces, thrust or radial, to prohibit rotation.
- the attachment system 500 includes a second eccentric bushing 535 positioned within the first eccentric bushing 530 .
- a second coated friction washer 545 is positioned between the first eccentric bushing 530 and the second eccentric bushing 535 .
- the coated friction washer 545 prohibits the rotation of the second eccentric bushing 535 with respect to the first eccentric bushing 530 .
- the eccentric bushings 530 and 535 may be rotated to align openings to permit the insertion of a fastener 570 through the bushing 530 and 535 , first fitting 510 , and second fitting 520 with a nut 580 threaded onto the fastener 570 to secure the system 500 together.
- FIG. 15 shows a front view of the attachment system 500 with a first coated friction washer 540 positioned between a first fitting 510 and a first eccentric bushing 530 .
- a second coated friction washer 545 is positioned between the first eccentric bushing 530 and a second eccentric bushing 535 positioned within the first eccentric bushing 530 .
- the use of two eccentric bushing 530 and 535 may be beneficial to secure an assembly when there is limited space on one side of the assembly as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure.
Abstract
Description
- This application is a divisional of U.S. patent application Ser. No. 14/826,577, filed Aug. 14, 2015, and entitled “Anti-Rotation for Eccentric Bushings,” the disclosure of which is hereby incorporated by reference in its entirety.
- The embodiments described herein relate to a system and method of using an attachment system comprising eccentric bushings and coated friction washers, the coating on the friction washers prohibiting rotation of the bushings with respect to a fitting.
- Eccentric bushings may be used to connect bolted joints. The eccentric bushings permit the alignment of each side of the joint even when the holes through the fittings of the joint may not be perfectly aligned. However, shear loads applied to the bushings may have a tendency to rotate the bushings due to their eccentricity. In order to prohibit rotation of the bushings, the bushing may include splined teeth on the exterior of the bushing. A lock plate may be positioned around the circumference of the bushing that includes splined teeth configured to engage the teeth of the bushings. The lock plate is configured to engage a stop lock on the fitting that prohibits the rotation of the lock plate. The mating teeth between the lock plate and the bushing prohibits the rotation of the bushing.
- The use of splined teeth on the components increases the manufacturing cost for the components. The splined teeth also may increase the installation time required to connect bolted joints especially if a large number of joints need to be connected. For example, an aircraft may include over forty (40) beam and frame fittings that need to be connected. For connection of a beam fitting with a frame fitting, the teeth of a bushing need to be lined up with the teeth on the lock plate. Additionally, the lock plate needs to be aligned so that a portion of the lock engages a lock stop on the fitting, which may add to the difficulty of installing the components. Other disadvantages of using an eccentric bushing and lock plate with splined teeth may exist.
- The present disclosure is directed to a method and system that overcomes some of the problems and disadvantages discussed above.
- One embodiment is an attachment system comprising a first fitting having a first hole and a second fitting having a second hole, the second fitting positioned adjacent to the first fitting. The system comprises first and second eccentric bushings, a portion of the first eccentric bushing positioned within the first hole of the first fitting and a portion of the second eccentric bushing positioned within the second hold of the second fitting. The system comprises a first friction washer positioned between a portion of the first eccentric bushing and the first fitting, the first friction washer comprising a coating on an exterior. The system comprises a second friction washer positioned between a portion of the second eccentric bushing and the second fitting, the second friction washer comprising a coating on an exterior. The coating on the first friction washer prohibits rotation of the first eccentric bushing with respect to the first fitting and the coating on the second friction washer prohibits rotation of the second eccentric bushing with respect to the second fitting.
- The second eccentric bushing may be positioned within the first eccentric bushing with the second friction washer positioned between a portion of the second eccentric bushing and a portion of the first eccentric bushing. The second friction washer may comprise a coating on an exterior, wherein the coating on the second friction washer may prohibit rotation of the second eccentric bushing with respect to the first eccentric bushing.
- The coating on the first and second friction washers may be a nickel-diamond coating. The attachment system may comprise at least four attachment points between an aircraft floor and an aircraft fuselage. Each of the attachment points may comprise a first fitting having a first hole, a second fitting having a second hole, the second fitting positioned adjacent to the first fitting. Each of the attachment points may comprise first and second eccentric bushings, a portion of the first eccentric bushing positioned within the first hole of the first fitting and a portion of the second eccentric bushing positioned within the second hold of the second fitting. Each of the attachment points may comprise a first friction washer positioned between a portion of the first eccentric bushing and the first fitting, the first friction washer comprising a coating on an exterior. Each of the attachment points may comprise a second friction washer positioned between a portion of the second eccentric bushing and the second fitting, the second friction washer comprising a coating on an exterior. The coating on the first friction washer prohibits rotation of the first eccentric bushing with respect to the first fitting and the coating on the second friction washer prohibits rotation of the second eccentric bushing with respect to the second fitting.
- The diamond concentration of the coating may be between about 8% and 30%. The coating on the first and second friction washers may be approximately 6 microns to 22 microns thick. The coating on the first and second friction washers may have a coefficient of friction of 0.5 or greater when lubricated. The first fitting may be a frame fitting connected to a fuselage of an aircraft and the second fitting may be a beam fitting connected to a floor of the aircraft. The system may include a spacer positioned between the first and second fittings. The system may include a first lock plate positioned around a circumference of the first friction washer and a second lock plate positioned around a circumference of the second friction washer. The system may include a first lock stop on the first fitting and a second lock stop on the second fitting, wherein the first lock plate may engage the first lock stop and the second lock plate may engage the second lock stop.
- One embodiment is an attachment system comprising a first fitting have a first hole and a second fitting having a second hole, the second fitting positioned adjacent to the first fitting. The system comprises a first eccentric bushing and a second eccentric bushing. A portion of the first eccentric bushing is positioned within the first hole of the first fitting and a portion of the second eccentric bushing is positioned within the second hole of the second fitting. The first eccentric bushing comprising a coating on an exterior, wherein the coating prohibits rotation of the first bushing with respect to the first fitting. The second eccentric bushing comprising a coating on an exterior, wherein the coating prohibits rotation of the second bushing within respect to the second fitting.
- The coating on the first and second eccentric bushings may be a nickel-diamond coating. The diamond concentration of the coating may be between about 8% and 30%. The coating on the first and second bushings may be approximately 6 microns to 22 microns thick. The coating on the first and second bushings may have a coefficient of friction of 0.5 or greater when lubricated. The first fitting may be a frame fitting connected to a fuselage of an aircraft and the second fitting may be a beam fitting connected to a floor of the aircraft. The system may include a spacer positioned between the first and second fittings.
- One embodiment is a method comprising positioning a portion of a first eccentric bushing within a first hole of a first fitting and positioning a portion of a second eccentric bushing within a second hole of a second fitting. The method comprises positioning a first friction washer between a portion of the first eccentric bushing and the first fitting, wherein an exterior of the first friction washer comprises a nickel-diamond coating. The method comprises positioning a second friction washer between a portion of the second eccentric bushing and the second fitting, wherein an exterior of the second friction washer comprises a nickel-diamond coating.
- The method may comprise rotating the first and second eccentric bushing to align an opening in the first eccentric bushing with an opening in the second eccentric bushing. The method may comprise positioning a first lock plate around a circumference of the first friction washer and engaging the first lock plate with a lock stop on the first fitting. The method may comprise positioning a second lock plate around a circumference of the second friction washer and engaging the second lock plate with a lock stop on the second fitting. The first fitting may comprise a frame fitting connected to a fuselage of an aircraft and the second fitting may comprise a beam fitting connected to a floor of the aircraft. The method may comprise positioning a spacer between the first fitting and the second fitting.
-
FIG. 1 shows an embodiment of an attachment system with an eccentric bushing and a coated friction washer. -
FIG. 2 shows the embodiment ofFIG. 1 with a portion of the eccentric bushing positioned within a fitting. -
FIG. 3 shows the embodiment ofFIG. 1 with a portion of the eccentric bushing positioned within a fitting and a fastener positioned adjacent the eccentric bushing. -
FIG. 4 is an embodiment of an eccentric bushing. -
FIG. 5 is an embodiment of a lock plate. -
FIG. 6 is an embodiment of a coated friction washer. -
FIGS. 7A-7C show the rotation of two eccentric bushings to align holes within the bushing. -
FIG. 8 is a schematic cross-section view of one embodiment of an attachment system. -
FIG. 9 is a schematic cross-section view of one embodiment of an attachment system. -
FIG. 10 is a schematic cross-section view of one embodiment of an attachment system. -
FIG. 11 is a schematic cross-section view of one embodiment of an attachment system showing a coated friction washer positioned between a lock plate and a portion of an eccentric bushing. -
FIG. 12 shows a schematic of one embodiment of an attachment system connecting the floor of an aircraft to the fuselage of the aircraft at multiple attachment points. -
FIG. 13 shows one embodiment of a prior attachment system that utilizes teeth to prohibit rotation between the bushing and the fitting. -
FIG. 14 shows a schematic cross-section view of one embodiment of an attachment system showing a coated friction washer positioned between an eccentric bushing and a fitting and a second coated friction washer positioned between two eccentric bushings. -
FIG. 15 shows a schematic front view of the attachment system of claim 14. - While the disclosure is susceptible to various modifications and alternative forms, specific embodiments have been shown by way of example in the drawings and will be described in detail herein. However, it should be understood that the disclosure is not intended to be limited to the particular forms disclosed. Rather, the intention is to cover all modifications, equivalents and alternatives falling within the scope of the disclosure as defined by the appended claims.
- As discussed above, eccentric bushings may be configured with teeth to prohibit the rotation of the eccentric bushing with respect to a fitting.
FIG. 13 shows aprior attachment system 400 for the connection of afirst fitting 410 and asecond fitting 420. Eccentric bushings 430 (only one is shown inFIG. 13 ) are used to align the openings in the twofittings opening 431 of thebushings 430 to secure thefittings eccentric bushings 430 includes a plurality ofteeth 432 that may be used to prohibit the rotation of thebushing 430 as described herein. Alock plate 450 is positioned around the perimeter of thebushing 430. Thelock plate 450 includes acentral opening 451 having a plurality ofteeth 453, which are configured to engage theteeth 432 along the perimeter of thebushing 430. Thelock plate 450 includes anotch 452 that is configured to engage alock stop 412 of the fitting 410. Thelock stop 412 prohibits the rotation of thelock plate 450 when the notch is engaged with thelock stop 412. Theteeth 453 of thelock plate 450 then prohibit the rotation of thebushing 430 when engaged with theteeth 432 of thebushing 430. - The installation of the
bushing 430 andlock plate 450 require the alignment of the teeth, which can be time consuming. Further, thenotch 452 of thelock plate 450 has to be aligned with the lock stop 412 of the fitting 410, which may also increase the time required to install theattachment system 400 especially if there are a large number offittings attachment system 400. It would be beneficial to provide an attachment system that can be installed in less time, with less difficulty, and/or use less expensive parts. -
FIG. 1 shows one embodiment of anattachment system 100 that includes afirst fitting 10 and asecond fitting 20 each that include anopening 11 and 21 (shown inFIG. 8 ). Aneccentric bushing 30 having anopening 31 may be inserted into theopening 11 in thefirst fitting 10. Although not shown inFIG. 1 , a secondeccentric bushing 30 may be inserted into theopening 21 of the second fitting as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. Acoated friction washer 40 is positioned between at least a portion of theeccentric bushing 30 and thefirst fitting 10. Thecoated friction washer 40 is coated with a coating that prohibits the rotation of thebushing 30 with respect to the fitting 10. As used herein, “prohibits” means significantly or substantially inhibiting the rotation and/or movement of, including, but not limited to, completely preventing rotation and/or movement. Acoated friction washer 40 may also be positioned between asecond bushing 30 and thesecond fitting 20 to prohibit the rotation of thesecond bushing 30 with respect to thesecond fitting 20. Thefirst fitting 10 may be a frame fitting connected to the fuselage of an aircraft and thesecond fitting 20 may be a beam fitting connected to a floor of the aircraft. Theattachment system 100 may be used to connect the floor beam to frame fittings of an aircraft. The components such as thebushing 30 does not include teeth and thus, may be installed more quickly and/or may be produced at a lower cost than the components of attachment systems that utilize teeth to prohibit rotation. - The coating on the
friction washer 40 is used to provide a high friction interface between thefittings eccentric bushing 30. The coating on thefriction washer 40 may be a nickel-diamond coating that prohibits the rotation of thebushing 30. The nickel-diamond coating may have a diamond concentration of between approximately 8-30%. The coating on thefriction washer 40 may have a thickness of between approximately 6 microns and 22 microns. The coating may be EKAGRIP commercially offered by 3M of St. Paul, Minn. The coating on thefriction washer 40 may ensure that thefriction washer 40 has a coefficient of friction of 0.5 or greater even when lubricant, such as an oil film, is present on the surface of thefriction washer 40. -
FIG. 2 shows a portion of thebushing 30 positioned within theopening 11 of the fitting 10 with thecoated friction washer 40 positioned between at least a portion of thebushing 30 and the fitting 10. Alock plate 50 is positioned around the perimeter of thebushing 30. Thelock plate 50 is configured to engage alock stop 12 of the fitting 10.FIG. 3 shows afastener 70 that may be used to fasten thefirst fitting 10 and thesecond fitting 20 together through theopenings 31 in the twoeccentric bushings 30.FIG. 3 also shows that aspacer 60 may be positioned between the first andsecond fittings -
FIG. 4 shows one embodiment of aneccentric bushing 30 with anopening 31. The use ofeccentric bushings 30 permits the alignment of two holes by the rotation of the twoeccentric bushings 30 as described herein in regards toFIGS. 7A-7C .FIG. 5 shows one embodiment of alock plate 50 having acentral opening 51 and anotch 52 configured to engage alock stop 12 or 22 (shown inFIG. 8 ) on a fitting 10 or 20 (shown inFIG. 8 ). Thelock stop FIG. 6 shows an embodiment of acoated friction washer 40 having anopening 41. -
FIG. 11 shows a schematic of afriction washer 40 positioned between alock plate 50 and aneccentric bushing 30. Thefriction washer 40 includes a core 44 that is covered with acoating 42 that provides a high coefficient of friction between thefriction washer 40 and the adjacent components, which inFIG. 11 may be alock plate 50 and aneccentric bushing 30. Thecoating 42 may be a nickel-diamond coating, which includesdiamonds 43 within thecoating 42 as shown inFIG. 11 . Thediamonds 43 provide friction to prohibit the rotation of thefriction washer 40 and adjoining components, such as aneccentric bushing 30 and alock plate 50, even if covered in a layer of grease or oil.Friction washer 40 is shown inFIG. 11 as including a nickel-diamond coating 42 for illustrative purposes only.Various coatings 42 may be used to provide an interface between the components that prohibits rotation and/more movement between the components as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. Additionally, thecoating 42 could be applied to the other components in addition or instead of thefriction washer 40 as would be appreciated by one of ordinary skill in the art and as disclosed herein. -
FIGS. 7A-7C show the rotation of two eccentric bushings to alignholes 31 within thebushings 30.FIG. 7A shows a firsteccentric bushing 30A having anopening 31A and a secondeccentric bushing 30B having anopening 31B. Thebushings FIG. 7B shows thebushings FIG. 7A , but theopenings FIG. 7C showsbushings openings eccentric bushings 30 permit the alignment of openings so fasteners may be inserted and connect fittings that may have openings slightly out of alignment due to acceptable tolerances. -
FIG. 8 shows a schematic cross-section of anattachment system 100 that includes afirst fitting 10 and asecond fitting 20 each that include anopening eccentric bushing 30A has been inserted into theopening 11 of thefirst fitting 10 and a secondeccentric bushing 30B has been inserted into theopening 21 of thesecond fitting 20. Thesystem 100 may include aspacer 60 positioned between the first andsecond fittings eccentric bushings openings eccentric bushings eccentric bushing 30A and the afirst lock plate 50A and a secondcoated friction washer 40B may be positioned between a portion, such as the head, of the secondeccentric bushing 30B and asecond lock plate 50B. - The
first lock plate 50A may engage alock stop 12 on thefirst fitting 10 that prohibits the rotation of thefirst lock plate 50A. Likewise, thesecond lock plate 50B may engage alock stop 22 on thesecond fitting 20 that prohibits the rotation of thesecond lock plate 50B. The coating on thefriction washers 40A and 40B and engagement of the first andsecond lock plates eccentric bushings fittings friction washers 40A and 40B even in the presence of a lubricant. As discussed herein, thebushings attachment system 100 may be used to attach a floor to a fuselage of an aircraft. One or more corners of attachment points between the floor and the fuselage may be aligned and not require the use ofeccentric bushings 30. As the floor is attached to the fuselage at attachment points moving away from the aligned fittings theeccentric bushings 30 may need to be used to align the fitting holes. -
FIG. 9 shows a schematic cross-section of anattachment system 200 that includes afirst fitting 110 and asecond fitting 120 each that include anopening eccentric bushing 130A has been inserted into theopening 111 of thefirst fitting 110 and a secondeccentric bushing 130B has been inserted into theopening 121 of thesecond fitting 120. Thesystem 200 may include aspacer 160 positioned between the first andsecond fittings eccentric bushings openings eccentric bushings eccentric bushing 130A and thefirst fitting 110 and a secondcoated friction washer 140B may be positioned between a portion, such as the head, of the secondeccentric bushing 130B and thesecond fitting 120. The coating on thefriction washers 140A and 140B may prohibit the rotation of theeccentric bushings fittings friction washers 140A and 140B even in the presence of a lubricant. As discussed herein, thebushings attachment system 200 may be used to attach a floor to a fuselage of an aircraft. One or more corners of attachment points between the floor and the fuselage may be aligned and not require the use of eccentric bushings 130. As the floor is attached to the fuselage at attachment points moving away from the aligned fittings the eccentric bushings 130 may need to be used to align the fitting holes. -
FIG. 10 shows a schematic cross-section of anattachment system 300 that includes afirst fitting 210 and asecond fitting 220 each that include anopening eccentric bushing 230A has been inserted into theopening 211 of thefirst fitting 210 and a secondeccentric bushing 230B has been inserted into theopening 221 of thesecond fitting 220. Thesystem 300 may include aspacer 260 positioned between the first andsecond fittings eccentric bushings openings eccentric bushings eccentric bushings bushings fittings bushings bushings attachment system 300 may be used to attach a floor to a fuselage of an aircraft. One or more corners of attachment points between the floor and the fuselage may be aligned and not require the use of eccentric bushings 230. As the floor is attached to the fuselage at attachment points moving away from the aligned fittings the eccentric bushings 230 may need to be used to align the fitting holes. -
FIG. 12 shows a schematic of anattachment system 100 connecting thefloor 1 of an aircraft to the fuselage 2 of the aircraft. Stanchions 3 may provide additional connection points between thefloor 1 and the fuselage 2. The schematic ofFIG. 12 shows anattachment system 100A connecting thefloor 1 to the fuselage 2 at a left front corner of thefloor 1 andattachment system 100B connecting thefloor 1 to the fuselage 2 at a right front corner of thefloor 1. A plurality of attachment systems may connect thefloor 1 to the fuselage 2 along the length of thefloor 1 between the front and rear corners of thefloor 1 as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. Various embodiments of attachment systems disclosed herein may be used to connect thefloor 1 to the fuselage 2. The combination of eccentric bushings and friction washers may not be necessary at each attachment point along the length of the floor. For example, the fitting holes of the floor and fuselage may be aligned at the midpoint of the floor not requiring the eccentric bushings to be rotated for alignment of the holes. As the attachment points are connected moving away from the initial midpoint connections the eccentric bushings in combination with the friction washers disclosed herein may be used to align the fitting holes between the floor and the fuselage. The initial attachment points between the floor and the fuselage, whether at the midpoint, corner, or other locations, may be aligned and not require the use of eccentric bushings and non-eccentric bushings may be used, or if eccentric bushings are used in the connection assembly, the eccentric bushings may not need to be rotated to align the fastener openings. As the attachment points between the floor and the fuselage are connected moving away from the initial attachment points, the fastener openings may move out of alignment necessitating the use of eccentric bushings that may be rotated to align the openings as discussed herein. The non-eccentric bushings and/or eccentric bushings may be coated with nickel-diamond to prohibit rotation and/or nickel-diamond coated washers may be used to prohibit rotation of the eccentric bushings. -
FIG. 12 shows the use of the attachment systems disclosed herein to attach a floor to a fuselage for illustrative purposes only. For example, the disclosed attachment systems may be used to secure various assemblies and not just the floor to a fuselage as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. The eccentric bushings and coated friction washers permit the alignment of holes between various fittings while ensuring a tight connection. Attachment systems utilizing eccentric bushings and coated friction washers may reduce or eliminate the need to drill match holes in components during the assembly process, which may reduce the time and cost during assembly. -
FIG. 14 shows a schematic cross-section of anattachment system 500 that includes afirst fitting 510 and asecond fitting 520.FIG. 14 shows thefirst fitting 510 being adjacent to thesecond fitting 520 for illustrative purposes only as the twofittings second fittings eccentric bushing 530 has been inserted into the opening of thefirst fitting 510 with a firstcoated friction washer 540 positioned between the firsteccentric bushing 530 and thefirst fitting 510. Thecoated friction washer 540 prohibits the rotation of the firsteccentric bushing 530 with respect to thefirst fitting 510 as discussed herein. In lieu of coated washers, thebushings - The
attachment system 500 includes a secondeccentric bushing 535 positioned within the firsteccentric bushing 530. A secondcoated friction washer 545 is positioned between the firsteccentric bushing 530 and the secondeccentric bushing 535. Thecoated friction washer 545 prohibits the rotation of the secondeccentric bushing 535 with respect to the firsteccentric bushing 530. As discussed herein, theeccentric bushings fastener 570 through thebushing first fitting 510, andsecond fitting 520 with anut 580 threaded onto thefastener 570 to secure thesystem 500 together. -
FIG. 15 shows a front view of theattachment system 500 with a firstcoated friction washer 540 positioned between afirst fitting 510 and a firsteccentric bushing 530. A secondcoated friction washer 545 is positioned between the firsteccentric bushing 530 and a secondeccentric bushing 535 positioned within the firsteccentric bushing 530. The use of twoeccentric bushing - Although this disclosure has been described in terms of certain preferred embodiments, other embodiments that are apparent to those of ordinary skill in the art, including embodiments that do not provide all of the features and advantages set forth herein, are also within the scope of this disclosure. Accordingly, the scope of the present disclosure is defined only by reference to the appended claims and equivalents thereof.
Claims (20)
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US15/986,046 US20180266478A1 (en) | 2015-08-14 | 2018-05-22 | Anti-Rotation for Eccentric Bushings |
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US11209031B2 (en) * | 2018-09-13 | 2021-12-28 | Airbus Sas | Single shear attachment device with an eccentric axis and an eccentric sleeve, mechanical assembly including such a device and assembling process |
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US20170045080A1 (en) | 2017-02-16 |
US10001158B2 (en) | 2018-06-19 |
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