Patents by Inventor Stephen R. Amorosi
Stephen R. Amorosi 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: 11352124Abstract: Continuous skin leading edge slats are disclosed. A disclosed example leading edge slat for use with an aircraft includes a single-piece nose skin defining upper and lower external surfaces of the leading edge slat, where the single-piece nose skin is to extend between a fore end and an aft end of the leading edge slat, and a box spar coupled to an inner surface of the single-piece nose skin. The box spar includes lateral walls extending away from the inner surface of the single-piece nose skin. The lateral walls define at least one compartment of the box spar.Type: GrantFiled: November 1, 2019Date of Patent: June 7, 2022Assignee: The Boeing CompanyInventors: Mark A. Barr, Stephen R. Amorosi, Matthew L. Anderson, Ramon A. Burin, Michael R. Severance
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Patent number: 11034432Abstract: A trailing edge flap actuation mechanism has a flap drive link with a first end pivotally coupled to a fore flap structure of a flap and a second end pivotally coupled to an underwing support structure. An aft tension link has a leading end pivotally coupled proximate an aft end of the underwing support structure and a trailing end coupled to a mid-section structure of the flap. An actuator, when actuated, rotates the flap drive link about a first pivot axle to move the flap between a retracted position and a deployed lowered position. The actuator, including a ball-screw drive shaft having a universal joint, is positioned in a cove above the underwing support structure whereby the extent that the underwing support structure protrudes below the wing is reduced.Type: GrantFiled: October 27, 2018Date of Patent: June 15, 2021Assignee: The Boeing CompanyInventors: Kevin R. Tsai, Bruce A. Dahl, Gregory M. Santini, Kyle A. Johnson, Seiya Sakurai, Stephen R. Amorosi
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Publication number: 20210129974Abstract: Continuous skin leading edge slats are disclosed. A disclosed example leading edge slat for use with an aircraft includes a single-piece nose skin defining upper and lower external surfaces of the leading edge slat, where the single-piece nose skin is to extend between a fore end and an aft end of the leading edge slat, and a box spar coupled to an inner surface of the single-piece nose skin. The box spar includes lateral walls extending away from the inner surface of the single-piece nose skin. The lateral walls define at least one compartment of the box spar.Type: ApplicationFiled: November 1, 2019Publication date: May 6, 2021Inventors: Mark A. Barr, Stephen R. Amorosi, Matthew L. Anderson, Ramon A. Burin, Michael R. Severance
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Publication number: 20200130809Abstract: A trailing edge flap actuation mechanism has a flap drive link with a first end pivotally coupled to a fore flap structure of a flap and a second end pivotally coupled to an underwing support structure. An aft tension link has a leading end pivotally coupled proximate an aft end of the underwing support structure and a trailing end coupled to a mid-section structure of the flap. An actuator, when actuated, rotates the flap drive link about a first pivot axle to move the flap between a retracted position and a deployed lowered position. The actuator, including a ball-screw drive shaft having a universal joint, is positioned in a cove above the underwing support structure whereby the extent that the underwing support structure protrudes below the wing is reduced.Type: ApplicationFiled: October 27, 2018Publication date: April 30, 2020Inventors: Kevin R. Tsai, Bruce A. Dahl, Gregory M. Santini, Kyle A. Johnson, Seiya Sakurai, Stephen R. Amorosi
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Patent number: 10399684Abstract: An induction heating system employs a ferromagnetic susceptor mounted proximate an exterior of flight surface of an aircraft. At least one electrically conductive coil is mounted proximate the ferromagnetic susceptor. The at least one electrically conductive coil is powered by a first power source with a first frequency. At least one compensating coil is mounted proximate the ferromagnetic susceptor having a geometry determined to provide substantially net-zero flux with respect to the at least one electrically conductive coil and positioned to induce induction heating where the first plurality of electrically conductive coils lacks induced inductive heating coverage. The at least one compensating coils is powered by a second AC power source with a second frequency.Type: GrantFiled: October 29, 2014Date of Patent: September 3, 2019Assignee: The Boeing CompanyInventors: John R. Hull, Vyacheslav Khozikov, Robert J. Miller, Stephen R. Amorosi, Rangasamy Elangovan
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Patent number: 9896190Abstract: A wing leading edge architecture designed to enable laminar flow on passenger jets or other aircraft. The embodiments disclosed herein comprise a metallic fixed leading edge skin panel that is bonded to internal support structure without fasteners except for limited fastening along side edge portions adjacent to side edge portions of adjacent leading edge skin panels and along an aft edge portion overlapping a wing skin. In addition, the embodiments disclosed herein integrate a low-drag bleed-air anti-icing (i.e., vent) system and a Krueger flap assembly (e.g., a two-position, high-height, variable-camber Krueger flap assembly).Type: GrantFiled: May 7, 2014Date of Patent: February 20, 2018Assignee: The Boeing CompanyInventors: Stephen R. Amorosi, Gregory M. Santini, Matthew Leroy Anderson, Steve C. Hinrichs, Walter J. Jarecki, Nicholas I. Bennett, Quang Minh Pham, Paul Hungwai Lai, Gregory E. Rupert, Carl F. Osaki
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Patent number: 9581146Abstract: A system for heating a shape memory alloy (SMA) actuator may include an SMA actuator, a smart susceptor, a plurality of induction coils, and a control module. The SMA actuator may have at least one layup. The SMA actuator may be selectively heated to a transition temperature. The smart susceptor may be in thermal contact with the at least one layup of the SMA actuator. The induction heating coils may be configured to receive an alternating current and generate a magnetic field based on the alternating current. The magnetic field may create an eddy current in at least one of the SMA actuator and the smart susceptor to heat the SMA actuator to the transition temperature. The control module may be configured to drive the alternating current supplied to the induction heating coils.Type: GrantFiled: October 3, 2013Date of Patent: February 28, 2017Assignee: The Boeing CompanyInventors: Moushumi Shome, Frederick T. Calkins, Stephen R. Amorosi, Flint M. Jamison, Sahrudine Apdalhaliem, Robert James Miller
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Patent number: 9463869Abstract: A wing includes a trailing edge, and a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position. The trailing edge device is located entirely within the trailing edge when stowed, and it increases lift over drag of the wing when deployed.Type: GrantFiled: June 6, 2014Date of Patent: October 11, 2016Assignee: The Boeing CompanyInventors: Flint M. Jamison, Stephen R. Amorosi, Michael K. Klein
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Patent number: 9463879Abstract: A system and method for operating an ice detection and deicing system are provided herein. The ice detection and deicing system may use changing magnetic properties of various components caused by temperature changes to detect conditions conducive to, or indicating, ice formation. The ice detection and deicing system may further use eddy currents induced in one or more layers of the system to increase the temperature of the one or more layers to reduce the amount of ice formation or reduce the probability of ice being formed.Type: GrantFiled: March 3, 2014Date of Patent: October 11, 2016Assignee: The Boeing CompanyInventors: Vyacheslav Khozikov, Robert J. Miller, Rangasamy Elangovan, Marc R. Matsen, Stephen R. Amorosi, Robert G. Albers, Michael Strasik, John R. Hull
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Publication number: 20160122025Abstract: An induction heating system employs a ferromagnetic susceptor mounted proximate an exterior of flight surface of an aircraft. At least one electrically conductive coil is mounted proximate the ferromagnetic susceptor. The at least one electrically conductive coil is powered by a first power source with a first frequency. At least one compensating coil is mounted proximate the ferromagnetic susceptor having a geometry determined to provide substantially net-zero flux with respect to the at least one electrically conductive coil and positioned to induce induction heating where the first plurality of electrically conductive coils lacks induced inductive heating coverage. The at least one compensating coils is powered by a second AC power source with a second frequency.Type: ApplicationFiled: October 29, 2014Publication date: May 5, 2016Inventors: John R. Hull, Vyacheslav Khozikov, Robert J. Miller, Stephen R. Amorosi, Rangasamy Elangovan
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Publication number: 20150353188Abstract: A wing includes a trailing edge, and a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position. The trailing edge device is located entirely within the trailing edge when stowed, and it increases lift over drag of the wing when deployed.Type: ApplicationFiled: June 6, 2014Publication date: December 10, 2015Applicant: THE BOEING COMPANYInventors: Flint M. Jamison, Stephen R. Amorosi, Michael K. Klein
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Patent number: 9180962Abstract: A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.Type: GrantFiled: September 24, 2013Date of Patent: November 10, 2015Assignee: The Boeing CompanyInventors: Matthew A. Moser, Mark J. Gardner, Michael R. Finn, Mark S. Good, Adam P. Malachowski, Monica E. Thommen, Stephen R. Amorosi, Dan Onu
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Publication number: 20150246730Abstract: A system and method for operating an ice detection and deicing system are provided herein. The ice detection and deicing system may use changing magnetic properties of various components caused by temperature changes to detect conditions conducive to, or indicating, ice formation. The ice detection and deicing system may further use eddy currents induced in one or more layers of the system to increase the temperature of the one or more layers to reduce the amount of ice formation or reduce the probability of ice being formed.Type: ApplicationFiled: March 3, 2014Publication date: September 3, 2015Applicant: The Boeing CompanyInventors: Vyacheslav Khozikov, Robert J. Miller, Rangasamy Elangovan, Marc R. Matsen, Stephen R. Amorosi, Robert G. Albers, Michael Strasik, John R. Hull
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Publication number: 20150096293Abstract: A system for heating a shape memory alloy (SMA) actuator may include an SMA actuator, a smart susceptor, a plurality of induction coils, and a control module. The SMA actuator may have at least one layup. The SMA actuator may be selectively heated to a transition temperature. The smart susceptor may be in thermal contact with the at least one layup of the SMA actuator. The induction heating coils may be configured to receive an alternating current and generate a magnetic field based on the alternating current. The magnetic field may create an eddy current in at least one of the SMA actuator and the smart susceptor to heat the SMA actuator to the transition temperature. The control module may be configured to drive the alternating current supplied to the induction heating coils.Type: ApplicationFiled: October 3, 2013Publication date: April 9, 2015Applicant: The Boeing CompanyInventors: Moushumi Shome, Frederick T. Calkins, Stephen R. Amorosi, Flint M. Jamison, Sahrudine Apdalhaliem, Robert James Miller
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Publication number: 20150083867Abstract: A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.Type: ApplicationFiled: September 24, 2013Publication date: March 26, 2015Applicant: The Boeing CompanyInventors: Matthew A. Moser, Mark J. Gardner, Michael R. Finn, Mark S. Good, Adam P. Malachowski, Monica E. Thommen, Stephen R. Amorosi, Dan Onu
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Patent number: 7992826Abstract: A method of reducing drag of a leading edge device having first and second flow surfaces includes coupling the first flow surface to an airfoil and coupling the second flow surface to the first flow surface. The leading edge device may be moved between a retracted position and an extended position. The second flow surface may be positioned generally behind the first flow surface during at least a portion of the movement of the leading edge device between the retracted and extended positions.Type: GrantFiled: October 4, 2010Date of Patent: August 9, 2011Assignee: The Boeing CompanyInventors: James M. Wheaton, Stephen R. Amorosi
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Publication number: 20110024575Abstract: A method of reducing drag of a leading edge device having first and second flow surfaces includes coupling the first flow surface to an airfoil and coupling the second flow surface to the first flow surface. The leading edge device may be moved between a retracted position and an extended position.Type: ApplicationFiled: October 4, 2010Publication date: February 3, 2011Applicant: THE BOEING COMPANYInventors: James M. Wheaton, Stephen R. Amorosi
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Patent number: 7828250Abstract: The present invention is directed generally toward leading edge flap apparatuses and corresponding methods. One aspect of the invention is directed toward an aircraft system having an airfoil, an actuator driver, and a leading edge device with two flow surfaces and six links. In a further aspect of the invention, the flow surfaces of the leading edge device are at least approximately located in the same position when the actuator driver is in two different positions. Another aspect of the invention is directed toward an aircraft system having an airfoil and a leading edge device movable between at least a retracted position and an extended position along a motion path having two segments. The second flow surface can be positioned generally behind and/or generally above the first flow surface when the first and second flow surfaces are located in the first segment of the motion path.Type: GrantFiled: July 17, 2007Date of Patent: November 9, 2010Assignee: The Boeing CompanyInventors: James M. Wheaton, Stephen R. Amorosi
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Publication number: 20100025537Abstract: The present invention is directed generally toward leading edge flap apparatuses and corresponding methods. One aspect of the invention is directed toward an aircraft system having an airfoil, an actuator driver, and a leading edge device with two flow surfaces and six links. In a further aspect of the invention, the flow surfaces of the leading edge device are at least approximately located in the same position when the actuator driver is in two different positions. Another aspect of the invention is directed toward an aircraft system having an airfoil and a leading edge device movable between at least a retracted position and an extended position along a motion path having two segments. The second flow surface can be positioned generally behind and/or generally above the first flow surface when the first and second flow surfaces are located in the first segment of the motion path.Type: ApplicationFiled: July 17, 2007Publication date: February 4, 2010Applicant: The Boeing CompanyInventors: James M. Wheaton, Stephen R. Amorosi
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Patent number: 7270305Abstract: Aircraft and leading edge apparatuses and corresponding methods are disclosed. In one embodiment, an aircraft system includes an airfoil with a leading edge device that is movable among a retracted position, at least one first extended position, and a second extended position. A first actuator can be operatively coupled to the leading edge device to move the flow surface between the retracted and the at least one first extended position. A second actuator can be operatively coupled to the leading edge device to move the flow surface between the at least one first extended position and the second extended position.Type: GrantFiled: June 15, 2004Date of Patent: September 18, 2007Assignee: The Boeing CompanyInventors: Scott N. Rampton, Stephen R. Amorosi