Patents by Inventor Ross Salisbury
Ross Salisbury has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11772806Abstract: An aircraft engine nacelle for coupling to a wing of an aircraft is disclosed having a fore end, and an aft end that is immoveable relative to the fore end. The aft end includes a major axis Mj and a minor axis Mi, and the nacelle is configured such the minor axis Mi is closer to vertical V than the major axis Mj when the nacelle is coupled to the wing and the aircraft is stationary on the ground. An aircraft system and an aircraft are disclosed each including the aircraft engine nacelle.Type: GrantFiled: July 10, 2019Date of Patent: October 3, 2023Assignee: AIRBUS OPERATIONS LIMITEDInventors: Geoffrey Richard Williams, Ross Salisbury, Antony Peacock
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Patent number: 11613376Abstract: An aircraft wing box is disclosed having a fuel tank with a fuel-tight boundary, upper and lower covers, forward and aft spars, and a partition including an inboard portion, an outboard portion, and a third portion between the inboard and outboard portions. Each cover is attached to each spar, the inboard portion of the partition is joined to each cover and joined to one of the spars, the outboard portion of the partition is joined to each cover and joined to one of the spars, each cover is joined to the partition. The inboard part, outboard part and third part of the partition are integrally formed as a single-piece; and the single-piece provides part of the fuel-tight boundary of the fuel tank.Type: GrantFiled: March 30, 2021Date of Patent: March 28, 2023Assignee: AIRBUS OPERATIONS LIMITEDInventors: Antony Charles Peacock, Ross Salisbury, Jonathan Paisley, Phillip Scott
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Patent number: 11247766Abstract: A leading edge structure for providing an aerodynamic surface of an aircraft is disclosed having a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The disclosure is also related to an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.Type: GrantFiled: November 19, 2018Date of Patent: February 15, 2022Assignees: AIRBUS OPERATIONS LIMITED, AIRBUS OPERATIONS GmbHInventors: Llifon Williams, Ross Salisbury, Marcus Rafla, Hugh Theobald, Christopher Payne, Robert McCormick, Heinz Hansen, Timothy Evans
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Publication number: 20210316871Abstract: An aircraft engine nacelle for coupling to a wing of an aircraft is disclosed having a fore end, and an aft end that is immoveable relative to the fore end. The aft end includes a major axis Mj and a minor axis Mi, and the nacelle is configured such the minor axis Mi is closer to vertical V than the major axis Mj when the nacelle is coupled to the wing and the aircraft is stationary on the ground. An aircraft system and an aircraft are disclosed each including the aircraft engine nacelle.Type: ApplicationFiled: July 10, 2019Publication date: October 14, 2021Inventors: Geoffrey Richard WILLIAMS, Ross SALISBURY, Antony PEACOCK
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Publication number: 20210300581Abstract: An aircraft wing box is disclosed having a fuel tank with a fuel-tight boundary, upper and lower covers, forward and aft spars, and a partition including an inboard portion, an outboard portion, and a third portion between the inboard and outboard portions. Each cover is attached to each spar, the inboard portion of the partition is joined to each cover and joined to one of the spars, the outboard portion of the partition is joined to each cover and joined to one of the spars, each cover is joined to the partition. The inboard part, outboard part and third part of the partition are integrally formed as a single-piece; and the single-piece provides part of the fuel-tight boundary of the fuel tank.Type: ApplicationFiled: March 30, 2021Publication date: September 30, 2021Inventors: Antony Charles PEACOCK, Ross SALISBURY, Jonathan PAISLEY, Phillip SCOTT
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Patent number: 11001364Abstract: An assembly apparatus for forming an interfay joint during manufacture of an aircraft (10). The assembly apparatus includes an assembly jig (40) to hold a first joint component (26), and an applicator (43) configured to apply an uncured layer of shim to the first joint component. The assembly jig locates, subsequent to the uncured layer of shim being applied, a second joint component (23) in an assembled joint position spaced from the first joint component. As such the uncured layer of shim is compressed between the first and second joint components. A method of forming an interfay joint during manufacture of an aircraft, an interfay joint for an aircraft, an aircraft aerodynamic surface, an aircraft, and a shim layer applicator.Type: GrantFiled: July 12, 2018Date of Patent: May 11, 2021Assignee: Airbus Operations LimitedInventors: Paul Edwards, Ross Salisbury, Antony Peacock
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Patent number: 10730605Abstract: An aircraft joint includes a first component having an outer aerodynamic surface and an inner surface, a second component having an outer aerodynamic surface and an inner surface, and a strap assembly bridging between the inner surfaces of the first and second components. The strap assembly has a first strap part attached to the inner surface of the first component, a second strap part attached to the inner surface of the second component, and a third strap part received in the first and second strap parts in a sliding manner. The third strap part when received in the first and second strap parts constrains movement of the first component relative to the second component in a direction normal to the outer aerodynamic surfaces of the first and second components in the vicinity of the strap assembly.Type: GrantFiled: May 11, 2017Date of Patent: August 4, 2020Assignee: AIRBUS OPERATIONS LIMITEDInventor: Ross Salisbury
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Publication number: 20200130807Abstract: An elongate primary structural element 200, such as a spar or rib, for a primary structure 22 of an aircraft aerodynamic structure 20, such as a wing. The primary structural element 200 has a shear web 210 comprising a twist 211 about a longitudinal axis of the shear web 210 so that a face 220 of at least a portion of the shear web 210 is non-planar when the shear web 210 is free from a torque applied about the longitudinal axis.Type: ApplicationFiled: October 25, 2019Publication date: April 30, 2020Inventors: Antony PEACOCK, Ross SALISBURY, Geoffrey Richard WILLIAMS, Daren HEALY
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Publication number: 20190092450Abstract: A leading edge structure for providing an aerodynamic surface of an aircraft is disclosed having a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The disclosure is also related to an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.Type: ApplicationFiled: November 19, 2018Publication date: March 28, 2019Inventors: Llifon Williams, Ross Salisbury, Marcus Rafla, Hugh Theobald, Christopher Payne, Robert McCormick, Heinz Hansen, Timothy Evans
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Publication number: 20190031315Abstract: An assembly apparatus for forming an interfay joint during manufacture of an aircraft (10). The assembly apparatus includes an assembly jig (40) to hold a first joint component (26), and an applicator (43) configured to apply an uncured layer of shim to the first joint component. The assembly jig locates, subsequent to the uncured layer of shim being applied, a second joint component (23) in an assembled joint position spaced from the first joint component. As such the uncured layer of shim is compressed between the first and second joint components. A method of forming an interfay joint during manufacture of an aircraft, an interfay joint for an aircraft, an aircraft aerodynamic surface, an aircraft, and a shim layer applicator.Type: ApplicationFiled: July 12, 2018Publication date: January 31, 2019Inventors: Paul EDWARDS, Ross SALISBURY, Antony PEACOCK
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Publication number: 20170327245Abstract: An aircraft joint includes a first component having an outer aerodynamic surface and an inner surface, a second component having an outer aerodynamic surface and an inner surface, and a strap assembly bridging between the inner surfaces of the first and second components. The strap assembly has a first strap part attached to the inner surface of the first component, a second strap part attached to the inner surface of the second component, and a third strap part received in the first and second strap parts in a sliding manner. The third strap part when received in the first and second strap parts constrains movement of the first component relative to the second component in a direction normal to the outer aerodynamic surfaces of the first and second components in the vicinity of the strap assembly.Type: ApplicationFiled: May 11, 2017Publication date: November 16, 2017Inventor: Ross SALISBURY
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Publication number: 20150048207Abstract: The invention provides a leading edge structure for providing an aerodynamic surface of an aircraft, the leading edge structure comprising a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The invention also provides an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.Type: ApplicationFiled: November 22, 2012Publication date: February 19, 2015Inventors: Llifon Williams, Ross Salisbury, Marcus Rafla, Hugh Theobald, Christopher Payne, Robert McCormick, Heinz Hansen, Timothy Evans