Patents by Inventor Eric Wildman
Eric Wildman 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: 11267554Abstract: A locking pin associated with one of a fixed wing and a wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of a longitudinal axis of the locking pin when the locking pin is received within the bush.Type: GrantFiled: January 29, 2020Date of Patent: March 8, 2022Assignee: Airbus Operations LimitedInventors: David Brakes, Eric Wildman
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Patent number: 10759514Abstract: A rotatable locking member for locking an aircraft wing with a movable wing tip device. The rotatable locking member including a U-shaped receiving portion arranged such that in an unlocked position the locking pin may be moved into and out of the U-shaped receiving portion, and in a locked position the locking pin is not able to be moved out of the U-shaped receiving portion, and the rotatable locking member is configured to be moved between the unlocked and locked position by rotational movement around the longitudinal central axis of the locking pin.Type: GrantFiled: May 16, 2017Date of Patent: September 1, 2020Assignee: Airbus Operations LimitedInventors: Eric Wildman, Matthew Harding
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Publication number: 20200164960Abstract: A locking pin associated with one of a fixed wing and a wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of a longitudinal axis of the locking pin when the locking pin is received within the bush.Type: ApplicationFiled: January 29, 2020Publication date: May 28, 2020Inventors: David BRAKES, Eric WILDMAN
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Patent number: 10569858Abstract: An aircraft wing comprises a fixed wing, and a wing tip device at the tip thereof. The wing tip device is configurable between (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground based operations. In the ground configuration with span of the wing is reduced. The wing further comprises a locking mechanism including a locking pin with a longitudinal axis, the locking pin associated with one of the fixed wing and the wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of the longitudinal axis of the locking pin when the locking pin is received within the bush.Type: GrantFiled: December 20, 2017Date of Patent: February 25, 2020Assignee: Airbus Operations LimitedInventors: David Brakes, Eric Wildman
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Patent number: 10190608Abstract: An actuator comprising: an inner cylinder received in an outer cylinder and a piston received in the inner cylinder that extends from the inner cylinder and the outer cylinder, the piston being slideable relative to the inner cylinder and the outer cylinder in response to the application of fluid pressure to cause the piston to extend further from the inner cylinder and the outer cylinder; and an auxiliary drive mechanism operable to cause the inner cylinder to extend from the outer cylinder, wherein the piston moves together with the inner cylinder relative to the outer cylinder.Type: GrantFiled: July 19, 2016Date of Patent: January 29, 2019Assignee: AIRBUS OPERATIONS LIMITEDInventor: Eric Wildman
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Publication number: 20180170519Abstract: An aircraft wing comprises a fixed wing, and a wing tip device at the tip thereof The wing tip device is configurable between (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground based operations. In the ground configuration with span of the wing is reduced. The wing further comprises a locking mechanism including a locking pin with a longitudinal axis, the locking pin associated with one of the fixed wing and the wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of the longitudinal axis of the locking pin when the locking pin is received within the bush.Type: ApplicationFiled: December 20, 2017Publication date: June 21, 2018Inventors: David BRAKES, Eric WILDMAN
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Publication number: 20170334543Abstract: A rotatable locking member for locking an aircraft wing with a movable wing tip device. The rotatable locking member including a U-shaped receiving portion arranged such that in an unlocked position the locking pin may be moved into and out of the U-shaped receiving portion, and in a locked position the locking pin is not able to be moved out of the U-shaped receiving portion, and the rotatable locking member is configured to be moved between the unlocked and locked position by rotational movement around the longitudinal central axis of the locking pin.Type: ApplicationFiled: May 16, 2017Publication date: November 23, 2017Inventors: Eric WILDMAN, Matthew HARDING
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Publication number: 20170023031Abstract: An actuator comprising: an inner cylinder received in an outer cylinder and a piston received in the inner cylinder that extends from the inner cylinder and the outer cylinder, the piston being slideable relative to the inner cylinder and the outer cylinder in response to the application of fluid pressure to cause the piston to extend further from the inner cylinder and the outer cylinder; and an auxiliary drive mechanism operable to cause the inner cylinder to extend from the outer cylinder, wherein the piston moves together with the inner cylinder relative to the outer cylinder.Type: ApplicationFiled: July 19, 2016Publication date: January 26, 2017Inventor: Eric WILDMAN
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Publication number: 20160046362Abstract: A pinned lug joint including: a first part with two first lugs projecting from a bridge which extends between them; a second part pivotally coupled to the first part, the second part including a second lug positioned between the first lugs; and a sealing member, the sealing member being mounted to the first lugs and extending between them to seal an air gap between the second lug and the bridge at least when the second part is in a first position. The pinned lug joint may be used to attach a panel assembly to part of an aircraft.Type: ApplicationFiled: August 17, 2015Publication date: February 18, 2016Inventors: Eric WILDMAN, Mohamed Saffique ABDULKADER
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Patent number: 9150302Abstract: A pinned lug joint comprising: a first part comprising two first lugs projecting from a bridge which extends between them; a second part pivotally coupled to the first part, the second part comprising a second lug positioned between the first lugs; and a sealing member, the sealing member being mounted to the first lugs and extending between them to seal an air gap between the second lug and the bridge at least when the second part is in a first position. The pinned lug joint may be used to attach a panel assembly to part of an aircraft.Type: GrantFiled: August 10, 2010Date of Patent: October 6, 2015Assignee: Airbus Operations LimitedInventors: Eric Wildman, Mohamed Saffique AdbulKader
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Patent number: 9038964Abstract: An aerodynamic control surface assembly comprising: an aerodynamic control surface (4); an actuator (10) for controlling deployment of the control surface; and a locking mechanism (30) moveable from a locked to an unlocked position. When the locking mechanism is set to the locked position, the actuator is operatively coupled to the control surface and the control surface can move in dependently of the actuator when the locking mechanism is set to the unlocked position. Such an assembly may be used in an aircraft to prevent clashing between a deployed flap (16) and a drooped spoiler (4) in the event of an actuator control systems failure.Type: GrantFiled: December 6, 2010Date of Patent: May 26, 2015Assignee: Airbus Operations LimitedInventor: Eric Wildman
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Patent number: 8757543Abstract: A support assembly for guiding a flap on an aircraft wing during deployment of the flap. The assembly includes an arcuate guide track mountable to an aircraft wing and defining a two-dimensional path, a carriage mounted on the guide track so as to slide along the track during flap deployment, a part-spherical bearing, and a shaft having one end attachable to a flap and the opposite end coupled to the carriage via said part-spherical bearing. The shaft is free to pivot relative to the carriage about a center of the part-spherical bearing in all directions, as the carriage slides along the track.Type: GrantFiled: July 14, 2010Date of Patent: June 24, 2014Assignee: Airbus Operations LimitedInventor: Eric Wildman
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Patent number: 8684309Abstract: An integrated bracket assembly for attachment to a convex outer corner surface of a torsion box of an aerofoil structure, the bracket assembly comprising a bracket strip having a plurality of brackets arranged spaced side by side, and connected by an infill rail integrally formed with the bracket strip, wherein the infill rail has a concave surface for mating with the convex surface of the torsion box. The torsion box may be of a “U-box” construction where a front spar and a rear spar are integrally formed with either an upper or lower torsion box cover to form an omega-shaped unitary component, and the other cover is attached to the omega-shaped component to provide an enclosed volume. The bracket strip may be used for attaching a leading/trailing edge structure of the aerofoil to the torsion box.Type: GrantFiled: June 13, 2012Date of Patent: April 1, 2014Assignee: Airbus Operations LimitedInventor: Eric Wildman
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Patent number: 8556214Abstract: A panel assembly for an aircraft including a panel having an upper aerodynamic surface and a leading edge, and a hinge fitting connected to an underside of the panel, defining a hinge line for the direction of rotation of the panel. The upper surface of the leading edge has an arcuate portion centered about the hinge line, and has an upturned portion forward of the arcuate portion. The panel assembly is pivotally connected to its hinge fitting to the trailing edge of the fixed wing portion and rotatable between a first position wherein the upper surfaces of the fixed wing portion and the panel are substantially flush, and a second position wherein the panel is rotated downwardly from the first position. A seal member attached to the trailing edge of the fixed wing portion, has a lower surface which seals against the upper surface of the panel during its movement.Type: GrantFiled: June 23, 2010Date of Patent: October 15, 2013Assignee: Airbus Operations LimitedInventors: Jon McAlinden, Eric Wildman
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Patent number: 8424801Abstract: A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multiple axes, and a control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support forming part of the structure of the aircraft. The assembly being configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said multiple axes to deploy and/or retract an aero surface pivotally attached to an opposite end of the primary support member along an arcuate path.Type: GrantFiled: April 13, 2011Date of Patent: April 23, 2013Assignee: Airbus Operations LimitedInventors: Eric Wildman, Simon John Parker, Anthony Bryant, Christian Folkard
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Patent number: 8360438Abstract: A seal (500) comprises a seal body (502) having a mounting portion (504), a first leg (506) and a second leg (508), a first stiffening member (514) and a second stiffening member (516) separated by an arcuate shear seal portion (529) in which the motions of the first leg (506) and second leg (508) are relatively constrained by the second stiffening member (516).Type: GrantFiled: August 25, 2009Date of Patent: January 29, 2013Assignee: Airbus Operations LimitedInventors: Eric Wildman, Simon John Parker
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Publication number: 20130001360Abstract: An integrated bracket assembly for attachment to a convex outer corner surface of a torsion box of an aerofoil structure, the bracket assembly comprising a bracket strip having a plurality of brackets arranged spaced side by side, and connected by an infill rail integrally formed with the bracket strip, wherein the infill rail has a concave surface for mating with the convex surface of the torsion box. The torsion box may be of a “U-box” construction where a front spar and a rear spar are integrally formed with either an upper or lower torsion box cover to form an omega-shaped unitary component, and the other cover is attached to the omega-shaped component to provide an enclosed volume. The bracket strip may be used for attaching a leading/trailing edge structure of the aerofoil to the torsion box.Type: ApplicationFiled: June 13, 2012Publication date: January 3, 2013Inventor: Eric WILDMAN
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Patent number: 8292236Abstract: A seal for sealing a gap between a first (252) and a second (207) component of an aircraft flight surface which has a first seal body (222) having a first sealing portion (246) arranged to seal against the first component, wherein the first seal body is movably mounted to the second component so as to seal at least part of the gap during relative movement of the first and second components. A seal is also provided with components movable relative to each other.Type: GrantFiled: March 17, 2009Date of Patent: October 23, 2012Assignee: Airbus Operations LimitedInventor: Eric Wildman
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Publication number: 20120234983Abstract: An aerodynamic control surface assembly comprising: an aerodynamic control surface (4); an actuator (10) for controlling deployment of the control surface; and a locking mechanism (30) moveable from a locked to an unlocked position. When the locking mechanism is set to the locked position, the actuator is operatively coupled to the control surface and the control surface can move in dependently of the actuator when the locking mechanism is set to the unlocked position. Such an assembly may be used in an aircraft to prevent clashing between a deployed flap (16) and a drooped spoiler (4) in the event of an actuator control systems failure.Type: ApplicationFiled: December 6, 2010Publication date: September 20, 2012Inventor: Eric Wildman
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Publication number: 20110253832Abstract: A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multiple axes, and a control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support forming part of the structure of the aircraft. The assembly being configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said multiple axes to deploy and/or retract an aero surface pivotally attached to an opposite end of the primary support member along an arcuate path.Type: ApplicationFiled: April 13, 2011Publication date: October 20, 2011Applicant: AIRBUS OPERATIONS LIMITEDInventors: Eric Wildman, Simon John Parker, Anthony Bryant, Christian Folkard