Patents by Inventor Jan A. Kordel
Jan A. Kordel 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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Publication number: 20150298793Abstract: An apparatus and method of a wing fold system may include a latch assembly rotating an unfixed portion of a wing, with respect to a fixed portion of the wing, between a flight position of the wing and a folded position of the wing. A first portion of the wing may hold a rotating portion of the latch assembly. A second portion of the wing may hold a secured portion of the latch assembly. The rotating portion of the latch assembly may rotate between an open position and a closed position. A slot in the rotating portion may receive the secured portion of the latch assembly. A securing portion of the rotating portion may secure a secured portion of the latch assembly. The latch assembly may prevent rotation of the second portion when the wing may be in the flight position.Type: ApplicationFiled: August 14, 2013Publication date: October 22, 2015Applicant: The Boeing CompanyInventors: Stephen John Fox, Jan A. Kordel, Keith Townsend, Matthew August Lassen, Mark John Gardner
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Publication number: 20150259062Abstract: Latching apparatus and methods are disclosed herein. An example apparatus includes a first latch portion including a first tooth and a first pin disposed in a first aperture defined by the first tooth and a second latch portion including a second tooth and a second pin disposed in an second aperture defined by the second tooth. The second tooth of the second latch portion is to mesh with the first tooth of the first latch portion to substantially orient the first pin and the second pin along an axis. The example apparatus further includes an actuator adjacent a first end of one of the first latch portion or the second latch portion to move the first pin and the second pin along the axis to lock the first latch portion to the second latch portion.Type: ApplicationFiled: June 1, 2015Publication date: September 17, 2015Inventors: Jan A. Kordel, Mark S. Good
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Patent number: 9108715Abstract: A rotary actuated high lift gapped aileron system and method are presented. A high lift gapped aileron couples to an airfoil at a hinge line and changes a camber of the airfoil. A rotary actuator coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door positioned under the hinge line provides an airflow over the high lift gapped aileron. A deployment linkage mechanism coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.Type: GrantFiled: May 29, 2012Date of Patent: August 18, 2015Assignee: THE BOEING COMPANYInventors: Jan A. Kordel, Seiya Sakurai
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Publication number: 20150191242Abstract: An aircraft comprising: a flight control surface and a rigid hinged panel both pivotably coupled to a wing; a drive linkage which links the flight control surface to the panel so that rotation of the former drives rotation of the latter, the drive linkage comprising first and second links, a first joint which pivotably couples the first and second links to each other, and a second joint which pivotably couples the first link to the flight control surface; and a cam track structure mounted to the wing, the cam track structure comprising first and second cam surfaces having extra run-out space at both ends thereof to prevent jamming. At least one of the links comprises a weakened portion which is designed to fail when a structural overload is produced due to jamming. Additional features can be added to the mechanism to block, shield, and shed other obstruction avenues.Type: ApplicationFiled: February 27, 2015Publication date: July 9, 2015Applicant: THE BOEING COMPANYInventors: Robert Douglas Maclean, Jan A. Kordel, Warren H. Steyaert, David Douglas Boes
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Patent number: 9045217Abstract: Latching apparatus and methods are disclosed herein. An example apparatus includes a first latch portion including a first tooth and a first pin disposed in a first aperture defined by the first tooth and a second latch portion including a second tooth and a second pin disposed in an second aperture defined by the second tooth. The second tooth of the second latch portion is to mesh with the first tooth of the first latch portion to substantially orient the first pin and the second pin along an axis. The example apparatus further includes an actuator adjacent a first end of one of the first latch portion or the second latch portion to move the first pin and the second pin along the axis to lock the first latch portion to the second latch portion.Type: GrantFiled: April 29, 2014Date of Patent: June 2, 2015Assignee: The Boeing CompanyInventors: Jan A. Kordel, Mark S. Good
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Patent number: 9016623Abstract: A flaperon mechanism that provides jam protection while preventing the component departing from the airplane or causing unacceptable collateral damage. The jam protection feature comprises a controlled failure (fused) mechanism that is associated with the flaperon and flaperon hinge panel and maintains functional movement of the devices. Additional features can be added to the mechanism to block, shield, allow runout and shed other obstruction avenues.Type: GrantFiled: November 30, 2011Date of Patent: April 28, 2015Assignee: The Boeing CompanyInventors: Robert D. Maclean, Jan A. Kordel, Warren H. Steyaert, David D. Boes
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Publication number: 20140231581Abstract: Latching apparatus and methods are disclosed herein. An example apparatus includes a first latch portion including a first tooth and a first pin disposed in a first aperture defined by the first tooth and a second latch portion including a second tooth and a second pin disposed in an second aperture defined by the second tooth. The second tooth of the second latch portion is to mesh with the first tooth of the first latch portion to substantially orient the first pin and the second pin along an axis. The example apparatus further includes an actuator adjacent a first end of one of the first latch portion or the second latch portion to move the first pin and the second pin along the axis to lock the first latch portion to the second latch portion.Type: ApplicationFiled: April 29, 2014Publication date: August 21, 2014Applicant: The Boeing CompanyInventors: Jan A. Kordel, Mark S. Good
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Patent number: 8733692Abstract: Latching apparatus and methods are disclosed herein. An example apparatus includes a first latch portion including a first tooth and a first pin disposed in a first aperture defined by the first tooth and a second latch portion including a second tooth and a second pin disposed in an second aperture defined by the second tooth. The second tooth of the second latch portion is to mesh with the first tooth of the first latch portion to substantially orient the first pin and the second pin along an axis. The example apparatus further includes an actuator adjacent a first end of one of the first latch portion or the second latch portion to move the first pin and the second pin along the axis to lock the first latch portion to the second latch portion.Type: GrantFiled: June 11, 2012Date of Patent: May 27, 2014Assignee: The Boeing CompanyInventors: Jan A. Kordel, Mark S. Good
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Publication number: 20140061371Abstract: A wing fold system of a wing of an aircraft. The system may include a first lock of a latch to prevent movement of a latch pin of the latch to prevent movement of an unfixed portion of the wing with respect to a fixed portion of the wing, the first lock may include a first cam configured to prevent the second lock from transitioning to a second engaged position until the first lock may be in a first engaged position via contact with a second cam of the second lock. A second lock of the latch, the second lock may include the second cam configured to prevent the first lock from transitioning away from the first engaged position until the second lock transitions away from the second engaged position.Type: ApplicationFiled: October 9, 2013Publication date: March 6, 2014Applicant: The Boeing CompanyInventors: Mark Steven Good, Jan A. Kordel, Quentin Theodor Pietersen, Steven Paul Walker, Kelly Thomas Jones, Matthew August Lassen, Rickie Hansken
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Publication number: 20130327883Abstract: Latching apparatus and methods are disclosed herein. An example apparatus includes a first latch portion including a first tooth and a first pin disposed in a first aperture defined by the first tooth and a second latch portion including a second tooth and a second pin disposed in an second aperture defined by the second tooth. The second tooth of the second latch portion is to mesh with the first tooth of the first latch portion to substantially orient the first pin and the second pin along an axis. The example apparatus further includes an actuator adjacent a first end of one of the first latch portion or the second latch portion to move the first pin and the second pin along the axis to lock the first latch portion to the second latch portion.Type: ApplicationFiled: June 11, 2012Publication date: December 12, 2013Inventors: Jan A. Kordel, Mark S. Good
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Publication number: 20130320151Abstract: A rotary actuated high lift gapped aileron system and method are presented. A high lift gapped aileron couples to an airfoil at a hinge line and changes a camber of the airfoil. A rotary actuator coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door positioned under the hinge line provides an airflow over the high lift gapped aileron. A deployment linkage mechanism coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.Type: ApplicationFiled: May 29, 2012Publication date: December 5, 2013Inventors: Jan A. Kordel, Seiya Sakurai
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Patent number: 8567726Abstract: Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.Type: GrantFiled: October 3, 2011Date of Patent: October 29, 2013Assignee: The Boeing CompanyInventors: Douglas S. Lacy, Jan A. Kordel, John V. Dovey, Michael A. Balzer, Seiya Sakurai, Neal V. Huynh
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Publication number: 20130134262Abstract: A flaperon mechanism that provides jam protection while preventing the component departing from the airplane or causing unacceptable collateral damage. The jam protection feature comprises a controlled failure (fused) mechanism that is associated with the flaperon and flaperon hinge panel and maintains functional movement of the devices. Additional features can be added to the mechanism to block, shield, allow runout and shed other obstruction avenues.Type: ApplicationFiled: November 30, 2011Publication date: May 30, 2013Applicant: THE BOEING COMPANYInventors: Robert Douglas Maclean, Jan A. Kordel, Warren H. Steyaert, David Douglas Boes
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Publication number: 20120018588Abstract: Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.Type: ApplicationFiled: October 3, 2011Publication date: January 26, 2012Applicant: THE BOEING COMPANYInventors: Douglas S. Lacy, Jan A. Kordel, John V. Dovey, Michael A. Balzer, Seiya Sakurai, Neal V. Huynh
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Patent number: 8038103Abstract: Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.Type: GrantFiled: July 2, 2009Date of Patent: October 18, 2011Assignee: The Boeing CompanyInventors: Douglas S. Lacy, Jan A. Kordel, John V. Dovey, Michael A. Balzer, Seiya Sakurai, Neal V. Huynh
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Patent number: 7766282Abstract: Trailing edge device catchers and associated systems and methods are disclosed. A system in accordance with one embodiment includes a wing having a wing support, a trailing edge device carried by and movable relative to the wing and having a device support, and a coupling connected between the wing and the trailing edge device. The coupling can include a pivot joint that includes a pivot element aligned along a pivot axis and connected between the wing support and the device support. The coupling can further include an actuator coupled between the wing and the trailing edge device, with the actuator having a first position in which the trailing edge device is stowed, and a second position in which the trailing edge device is deployed, with an air flow gap located between the wing and the trailing edge device when the trailing edge device is in the second position. A cam track is carried by one of the wing and the trailing edge device and has opposing cam track surfaces fixed relative to each other.Type: GrantFiled: December 11, 2007Date of Patent: August 3, 2010Assignee: The Boeing CompanyInventors: Jan A. Kordel, Seiya Sakurai, Michael A. Balzer, John V. Dovey
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Publication number: 20100170998Abstract: Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.Type: ApplicationFiled: July 2, 2009Publication date: July 8, 2010Applicant: The Boeing CompanyInventors: Douglas S. Lacy, Jan A. Kordel, John V. Dovey, Michael A. Balzer, Seiya Sakurai, Neal V. Huynh
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Patent number: 7744040Abstract: Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path. An outboard trailing edge device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path that is non-parallel to the first motion path. An intermediate trailing edge device can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.Type: GrantFiled: November 4, 2008Date of Patent: June 29, 2010Assignee: The Boeing CompanyInventors: Douglas S. Lacy, Kevin W. Beyer, Stephen T. Brown, Paul W. Dees, Neal V. Huynh, Jan A. Kordel, Clayton A. Prow, Seiya Sakurai
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Patent number: 7708231Abstract: Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.Type: GrantFiled: November 21, 2005Date of Patent: May 4, 2010Assignee: The Boeing CompanyInventors: Douglas S. Lacy, Jan A. Kordel, John V. Dovey, Michael A. Balzer, Seiya Sakurai, Neal V. Huynh
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Patent number: 7611099Abstract: Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.Type: GrantFiled: September 7, 2005Date of Patent: November 3, 2009Assignee: The Boeing CompanyInventors: Jan A. Kordel, Seiya Sakurai, Bret A. Bowers, Christopher G. Glassmoyer, Darren B. Williams