Patents by Inventor Farzad MOKHTARIAN
Farzad MOKHTARIAN 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: 11584506Abstract: An aircraft and an aircraft wing assembly for an aircraft. The wing assembly includes a wing body assembly including a wing body; and at least one protruding portion connected to the wing body. The protruding portion extends aftwardly from an aft side of the wing body assembly, a leading edge of the wing body assembly defining a leading edge line, a trailing edge of the wing body assembly defining a trailing edge line extending between the inboard end and the outboard end, the trailing edge including a trailing edge of the protruding portion, the trailing edge line being a smooth line, a chord distance being defined longitudinally from the leading edge line to the trailing edge line, the chord distance at a center of the protruding portion being greater than the chord distance inboard of protruding portion and outboard of the protruding portion.Type: GrantFiled: December 3, 2019Date of Patent: February 21, 2023Assignee: BOMBARDIER INC.Inventors: Fassi Kafyeke, Francois Pepin, Farzad Mokhtarian, David Leblond
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Patent number: 11174003Abstract: A flap and spoiler system of an aircraft wing including a spoiler having a spoiler leading edge and a spoiler trailing edge. The flap and spoiler system also includes a flap having a flap leading edge and a flap trailing edge, an axis of rotation through the flap, and a top surface portion above the axis of rotation. The top surface portion has a first semi-circular shape such that, when the flap rotates about the axis of rotation, the spoiler trailing edge remains substantially stationary. When the spoiler trailing edge remains substantially stationary the spoiler is not driven by a spoiler drive.Type: GrantFiled: June 20, 2019Date of Patent: November 16, 2021Inventor: Farzad Mokhtarian
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Patent number: 11155329Abstract: A variable camber system for an aircraft wing including a wing bracket extending downward from a wing, a flap bracket pivotably coupled to the wing bracket, and a flap pivotably coupled to the flap bracket such that the flap pivots around an axis of rotation through the flap. The variable camber system is configured to adjust position of both the flap and the flap bracket relative to the wing while maintaining position of the flap relative to the flap bracket. The variable camber system is also configured to adjust position of the flap relative to the flap bracket.Type: GrantFiled: June 20, 2019Date of Patent: October 26, 2021Inventor: Farzad Mokhtarian
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Patent number: 11027825Abstract: The present disclosure provides methods and system for controlling the operation of an aircraft aileron which comprises an inboard portion and an outboard portion. A velocity of the aircraft is determined. Then, based on the velocity of the aircraft, the aileron is caused to move in certain ways. Below a first velocity threshold, the inboard aileron portion and the outboard aileron portion are caused to move substantially in unison. Between the first velocity threshold and a second, greater, velocity threshold, the outboard portion of the aileron is caused to lock and the inboard portion of the aileron is caused to move independently from the outboard portion. Above the second velocity threshold, the inboard portion is caused to move substantially opposite from the outboard portion.Type: GrantFiled: June 23, 2017Date of Patent: June 8, 2021Assignee: BOMBARDIER INC.Inventors: Thomas Ahn, Grace Shwu Jen Tang, Farzad Mokhtarian, Gerardus Herbertus de Kok, Sebastien Eric Benoit Vigneron
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Publication number: 20200398970Abstract: Wing to fuse junction shaping, and associated systems and methods are disclosed herein. An aircraft includes: a fuselage, a wing, and a fairing that covers a junction between the wing and the fuselage. The fairing is configured to receive an inboard section of the wing. An outer surface of the fairing includes an upstream bump proximate to a leading edge of the wing, a midsection sculpting, and a downstream bump proximate to a trailing edge of the wing.Type: ApplicationFiled: June 24, 2020Publication date: December 24, 2020Applicant: Bombardier Inc.Inventors: Pascal Bochud, Farzad Mokhtarian, François Pepin, Fassi Kafyeke
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Publication number: 20200247536Abstract: A vertical takeoff and landing (VTOL) aircraft comprises a fuselage. A pair of wings is fixedly connected to the fuselage. A pair of horizontal stabilizers is fixedly connected to the fuselage and spaced from the pair of wings along a longitudinal axis. At least one fan is ducted within each wing of the pair of wings and within each horizontal stabilizer. The at least one fan has a fan axis defined by a fan hub. The fan axis has a fan axis orientation defined in a frame of reference of the VTOL aircraft. The fan axis orientation is invariable in the frame of reference. At least one thrust unit is mounted to the fuselage. The at least one thrust unit has a thrust unit axis defined by the thrust unit hub.Type: ApplicationFiled: December 17, 2019Publication date: August 6, 2020Inventors: Farzad MOKHTARIAN, Alexandre GALIN
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Publication number: 20200239126Abstract: An aircraft and an aircraft wing assembly for an aircraft. The wing assembly includes a wing body assembly including a wing body; and at least one protruding portion connected to the wing body. The protruding portion extends aftwardly from an aft side of the wing body assembly, a leading edge of the wing body assembly defining a leading edge line, a trailing edge of the wing body assembly defining a trailing edge line extending between the inboard end and the outboard end, the trailing edge including a trailing edge of the protruding portion, the trailing edge line being a smooth line, a chord distance being defined longitudinally from the leading edge line to the trailing edge line, the chord distance at a center of the protruding portion being greater than the chord distance inboard of protruding portion and outboard of the protruding portion.Type: ApplicationFiled: December 3, 2019Publication date: July 30, 2020Inventors: Fassi KAFYEKE, Francois PEPIN, Farzad MOKHTARIAN, David LEBLOND
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Publication number: 20190389558Abstract: A variable camber system for an aircraft wing including a wing bracket extending downward from a wing, a flap bracket pivotably coupled to the wing bracket, and a flap pivotably coupled to the flap bracket such that the flap pivots around an axis of rotation through the flap. The variable camber system is configured to adjust position of both the flap and the flap bracket relative to the wing while maintaining position of the flap relative to the flap bracket. The variable camber system is also configured to adjust position of the flap relative to the flap bracket.Type: ApplicationFiled: June 20, 2019Publication date: December 26, 2019Inventor: Farzad Mokhtarian
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Publication number: 20190389561Abstract: A flap and spoiler system of an aircraft wing including a spoiler having a spoiler leading edge and a spoiler trailing edge. The flap and spoiler system also includes a flap having a flap leading edge and a flap trailing edge, an axis of rotation through the flap, and a top surface portion above the axis of rotation. The top surface portion has a first semi-circular shape such that, when the flap rotates about the axis of rotation, the spoiler trailing edge remains substantially stationary. When the spoiler trailing edge remains substantially stationary the spoiler is not driven by a spoiler drive.Type: ApplicationFiled: June 20, 2019Publication date: December 26, 2019Inventor: Farzad Mokhtarian
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Publication number: 20190322356Abstract: The present disclosure provides methods and system for controlling the operation of an aircraft aileron which comprises an inboard portion and an outboard portion. A velocity of the aircraft is determined. Then, based on the velocity of the aircraft, the aileron is caused to move in certain ways. Below a first velocity threshold, the inboard aileron portion and the outboard aileron portion are caused to move substantially in unison. Between the first velocity threshold and a second, greater, velocity threshold, the outboard portion of the aileron is caused to lock and the inboard portion of the aileron is caused to move independently from the outboard portion. Above the second velocity threshold, the inboard portion is caused to move substantially opposite from the outboard portion.Type: ApplicationFiled: June 23, 2017Publication date: October 24, 2019Inventors: Thomas AHN, Grace Shwu Jen TANG, Farzad MOKHTARIAN, Gerardus Herbertus DE KOK, Sebastien Eric Benoit VIGNERON