Patents by Inventor Scott A. Chasen
Scott A. Chasen 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: 11111026Abstract: A method for securing an engine using an adjustable mounting assembly is provided including adjusting an extendible element of the adjustable mounted assembly from a first position to a second position. Another extendible element of the adjustable mounting assembly is adjusted from a third position to a fourth position. The engine is mounted using the adjustable mounted assembly with the extendible element in the second position and another extendible element in the fourth position.Type: GrantFiled: October 4, 2019Date of Patent: September 7, 2021Assignee: Sikorsky Aircraft CorporationInventors: Jon McBride, Scott A. Chasen
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Patent number: 10994834Abstract: An active vibration control system for an aircraft includes a gearbox operably coupling a power source and a component rotatable about an axis. The gearbox includes a flexible region which allows flexure between a first stage and a second stage. At least one active vibration control actuator is arranged in vibrational communication with the flexible region to counteract vibrations transmitted between the power source and the rotatable component.Type: GrantFiled: February 22, 2018Date of Patent: May 4, 2021Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Stephen Johnston, Joseph Caterisano, William A. Welsh, Scott A. Chasen
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Publication number: 20200148377Abstract: A method for securing an engine using an adjustable mounting assembly is provided including adjusting an extendible element of the adjustable mounted assembly from a first position to a second position. Another extendible element of the adjustable mounting assembly is adjusted from a third position to a fourth position. The engine is mounted using the adjustable mounted assembly with the extendible element in the second position and another extendible element in the fourth position.Type: ApplicationFiled: October 4, 2019Publication date: May 14, 2020Inventors: Jon McBride, Scott A. Chasen
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Patent number: 10501198Abstract: A flexible fuel bladder assembly for an aircraft includes a flexible fuel bladder positioned at an airframe and having an opening to allow a flow of fuel into and/or out of the fuel bladder. A breakaway valve is operably connected to the fuel bladder at the opening to control a flow of fuel therethrough. A non-contacting or loose fitting reaction feature is affixed to the airframe and is interactive with the breakaway valve such that movement of the breakaway valve relative to the reaction feature results in breakage of a valve body of the breakaway valve and closure of the breakaway valve to prevent flow of fuel therethrough while also allowing for a second reaction mode to cause breakage of a valve body should the connecting hose be pulled relative to the breakaway valve.Type: GrantFiled: May 6, 2015Date of Patent: December 10, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Scott A. Chasen, Robert R. Rogstad, Chris John Biehl
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Patent number: 10479515Abstract: A strut for mounting an engine in an aircraft includes a first member and a second member. A friction material is coupled to a surface of the first member and is positioned between the first member and the second member. At least one attachment couples the first member, the second member, and the friction material. A biasing mechanism is associated with the at least one attachment. A biasing force of the biasing mechanism biases the second member into engagement with the frictional material to create a static frictional load between the first member and the second member.Type: GrantFiled: May 26, 2017Date of Patent: November 19, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Scott A. Chasen, William A. Welsh, Chris John Biehl
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Patent number: 10472079Abstract: A method for securing an engine using an adjustable mounting assembly is provided including adjusting an extendible element of the adjustable mounted assembly from a first position to a second position. Another extendible element of the adjustable mounting assembly is adjusted from a third position to a fourth position. The engine is mounted using the adjustable mounted assembly with the extendible element in the second position and another extendible element in the fourth position.Type: GrantFiled: May 1, 2015Date of Patent: November 12, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jon McBride, Scott A. Chasen
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Publication number: 20190256199Abstract: An active vibration control system for an aircraft includes a gearbox operably coupling a power source and a component rotatable about an axis. The gearbox includes a flexible region which allows flexure between a first stage and a second stage. At least one active vibration control actuator is arranged in vibrational communication with the flexible region to counteract vibrations transmitted between the power source and the rotatable component.Type: ApplicationFiled: February 22, 2018Publication date: August 22, 2019Inventors: Stephen Johnston, Joseph Caterisano, William A. Welsh, Scott A. Chasen
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Publication number: 20180044027Abstract: A strut for mounting an engine in an aircraft includes a first member and a second member. A friction material is coupled to a surface of the first member and is positioned between the first member and the second member. At least one attachment couples the first member, the second member, and the friction material. A biasing mechanism is associated with the at least one attachment. A biasing force of the biasing mechanism biases the second member into engagement with the frictional material to create a static frictional load between the first member and the second member.Type: ApplicationFiled: May 26, 2017Publication date: February 15, 2018Inventors: Scott A. Chasen, William A. Welsh, Chris John Biehl
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Publication number: 20170259932Abstract: A flexible fuel bladder assembly for an aircraft includes a flexible fuel bladder positioned at an airframe and having an opening to allow a flow of fuel into and/or out of the fuel bladder. A breakaway valve is operably connected to the fuel bladder at the opening to control a flow of fuel therethrough. A non-contacting or loose fitting reaction feature is affixed to the airframe and is interactive with the breakaway valve such that movement of the breakaway valve relative to the reaction feature results in breakage of a valve body of the breakaway valve and closure of the breakaway valve to prevent flow of fuel therethrough while also allowing for a second reaction mode to cause breakage of a valve body should the connecting hose be pulled relative to the breakaway valve.Type: ApplicationFiled: May 6, 2015Publication date: September 14, 2017Inventors: Scott A. Chasen, Robert R. Rogstad, Chris John Biehl
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Publication number: 20170217581Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly with a plurality of blades rotating in a first plane and a lower rotor assembly with a plurality of blades rotating in a second plane, each of the blades having a root end, a midpoint, and a tip end. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. The blades of the upper rotor assembly and the blades of the lower rotor assembly are indexed to improve tip end clearance between pairs of tip ends in the crossing plane as the tip ends move in respective first and second sinusoidal paths.Type: ApplicationFiled: September 29, 2015Publication date: August 3, 2017Inventors: David H. Hunter, Scott A. Chasen, Brandon Michael Cerge, Maximilian August Koessick, Michael J. Kostoss, Eric Lucien Nussenblatt, Justin Thomas, Chris P. Butler
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Patent number: 9708979Abstract: A method of securing two components to each other includes locating a mounting strip at a first mounting flange of a first component. The mounting strip is slidably affixed to the first component and includes a plurality of strip openings and a tightening ramp located at each strip opening of the plurality of strip openings. A second component is located such that a second mounting flange of the second component abuts the first mounting flange. A plurality of fasteners are located at the second mounting flange. A fastener of the plurality of fasteners extends through each strip opening of the plurality of strip openings. The mounting strip is slid in a direction to increase tension on the plurality of fasteners via an increasing height of the tightening ramp under a fastener head of the fastener, thereby securing the first mounting flange to the second mounting flange.Type: GrantFiled: November 25, 2013Date of Patent: July 18, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventor: Scott A. Chasen
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Patent number: 9586692Abstract: An engine inlet assembly includes an inlet duct having a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet duct leg extending toward a common inlet duct outlet located at an engine inlet. The first inlet duct leg and the second inlet duct leg are fixedly secured to an airframe of an aircraft at an air inlet. The duct outlet has a floating interface with the engine inlet.Type: GrantFiled: April 14, 2014Date of Patent: March 7, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Steven Bofill, Scott A. Chasen, Joseph Lawrence Simonetti, Donald William Lamb, Jr.
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Publication number: 20170050739Abstract: A method for securing an engine using an adjustable mounting assembly is provided including adjusting an extendible element of the adjustable mounted assembly from a first position to a second position. Another extendible element of the adjustable mounting assembly is adjusted from a third position to a fourth position. The engine is mounted using the adjustable mounted assembly with the extendible element in the second position and another extendible element in the fourth position.Type: ApplicationFiled: May 1, 2015Publication date: February 23, 2017Inventors: McBride Jon, Scott A. Chasen
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Publication number: 20150291288Abstract: An engine inlet assembly includes an inlet duct having a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet duct leg extending toward a common inlet duct outlet located at an engine inlet. The first inlet duct leg and the second inlet duct leg are fixedly secured to an airframe of an aircraft at an air inlet. The duct outlet has a floating interface with the engine inlet.Type: ApplicationFiled: April 14, 2014Publication date: October 15, 2015Applicant: Sikorsky Aircraft CorporationInventors: Steven Bofill, Scott A. Chasen, Joseph Lawrence Simonetti, Donald William Lamb, Jr.
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Publication number: 20150144201Abstract: A method of securing two components to each other includes locating a mounting strip at a first mounting flange of a first component. The mounting strip is slidably affixed to the first component and includes a plurality of strip openings and a tightening ramp located at each strip opening of the plurality of strip openings. A second component is located such that a second mounting flange of the second component abuts the first mounting flange. A plurality of fasteners are located at the second mounting flange. A fastener of the plurality of fasteners extends through each strip opening of the plurality of strip openings. The mounting strip is slid in a direction to increase tension on the plurality of fasteners via an increasing height of the tightening ramp under a fastener head of the fastener, thereby securing the first mounting flange to the second mounting flange.Type: ApplicationFiled: November 25, 2013Publication date: May 28, 2015Applicant: Sikorsky Aircraft CorporationInventor: Scott A. Chasen
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Patent number: 8667663Abstract: An eccentric fitting assembly includes an outer eccentric fitting which defines an outer axis, the outer eccentric fitting defines an opening offset from the outer axis and an inner eccentric fitting which defines an inner axis, the inner eccentric fitting defines a stud opening offset from the inner axis, the inner eccentric fitting receivable within the opening.Type: GrantFiled: October 26, 2009Date of Patent: March 11, 2014Assignee: Sikorsky Aircraft CorporationInventors: Robert W. Maxwell, Scott A. Chasen, Barton J. Hainsworth
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Publication number: 20110239439Abstract: An eccentric fitting assembly includes an outer eccentric fitting which defines an outer axis, the outer eccentric fitting defines an opening offset from the outer axis and an inner eccentric fitting which defines an inner axis, the inner eccentric fitting defines a stud opening offset from the inner axis, the inner eccentric fitting receivable within the opening.Type: ApplicationFiled: October 26, 2009Publication date: October 6, 2011Inventors: Rpbert W. Maxwell, Scott A. Chasen, Barton J. Hainsworth
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Patent number: 6598830Abstract: A telescoping aerial refueling probe includes a second section and a ball screw. The first section is telescopically mounted to the second section. The ball screw is rotationally mounted along the longitudinal axis of the probe. A hydraulic motor rotates the ball screw to drive a ball screw nut and attached first section relative the second section. The hydraulic motor communicates with the hydraulic system and is operated in response to a control system. A backup motor such as an electric motor alternatively drives the ball screw upon failure of the hydraulic motor. As only the backup motor is required for redundancy, minimal additional weight is added to the probe and a relatively compact system is provided.Type: GrantFiled: June 12, 2002Date of Patent: July 29, 2003Assignee: Sikorsky Aircraft CorporationInventors: Michael H. Ambrose, Anthony Zbigniew Stobiecki, Scott A. Chasen
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Patent number: 5776341Abstract: A fuel intake device (20) for a fuel system (10) having a fuel tank (14) for containing a supply of fuel (16) and an internal fuel feed line (18) which is disposed internally of the fuel tank (14) and which extends into a sump region (26) thereof. The fuel intake device (20) is characterized by a filter assembly (40) which envelopes an end portion (18.sub.E) of the internal fuel feed line (18) and which includes a lower fuel filtering portion (42) and an upper fuel bypass portion (44). The lower fuel filtering portion (42) has a plurality of fine apertures (42.sub.O) therein for facilitating a primary flow (P.sub.F) of fuel (16) therethrough and for filtering debris from the supply of fuel (16) in a normal operating mode. The upper fuel bypass portion (44) has a plurality of coarse apertures (44.sub.O) for facilitating a secondary flow (S.sub.F) of fuel therethrough in a bypass operating mode. Furthermore, the filter assembly (40) is situated about the end portion (18.sub.E) such that the inlet orifice (18.Type: GrantFiled: December 23, 1996Date of Patent: July 7, 1998Assignee: Sikorsky Aircraft CorporationInventors: Richard S. Barnard, Scott A. Chasen