Patents by Inventor David Lednicer
David Lednicer 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: 10723444Abstract: A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.Type: GrantFiled: February 9, 2018Date of Patent: July 28, 2020Assignee: ICON AIRCRAFT, INC.Inventors: Matthew Gionta, Jon Karkow, John Roncz, Dieter Koehler, David Lednicer
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Publication number: 20180178903Abstract: A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.Type: ApplicationFiled: February 9, 2018Publication date: June 28, 2018Applicant: ICON AIRCRAFT, Inc.Inventors: Matthew Gionta, Jon Karkow, John Roncz, Dieter Koehler, David Lednicer
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Patent number: 9926071Abstract: A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.Type: GrantFiled: April 5, 2016Date of Patent: March 27, 2018Assignee: ICON AIRCRAFT, INC.Inventors: Matthew Gionta, Jon Karkow, John Roncz, Dieter Koehler, David Lednicer
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Publication number: 20170021916Abstract: A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.Type: ApplicationFiled: April 5, 2016Publication date: January 26, 2017Applicant: Icon Aircraft, Inc.Inventors: Matthew Gionta, Jon Karkow, John Roncz, Dieter Koehler, David Lednicer
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Patent number: 9327828Abstract: A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.Type: GrantFiled: July 19, 2013Date of Patent: May 3, 2016Assignee: Icon Aircraft, Inc.Inventors: Matthew Gionta, Jon Karkow, John Roncz, Dieter Koehler, David Lednicer
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Publication number: 20140021302Abstract: A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.Type: ApplicationFiled: July 19, 2013Publication date: January 23, 2014Inventors: Matthew Gionta, Jon Karkow, John Roncz, Dieter Koehler, Len Fox, David Lednicer
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Patent number: 4744728Abstract: A family of airfoil cross sections, termed SC21xx, for use in a helicopter blade is disclosed. The airfoil (36) achieves maximum lift performance equivalent to prior art airfoil configurations without incurring increased aerodynamic drag at high velocities. The airfoil (36) was developed by thickening and drooping the leading edge region (38) of the prior art airfoil (30) improving lift in the leading edge region (38) and delaying the formation of sonic shock waves at high velocities.Type: GrantFiled: September 3, 1986Date of Patent: May 17, 1988Assignee: United Technologies CorporationInventors: David A. Lednicer, Stephen J. Owen
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Patent number: RE33589Abstract: A family of airfoil cross sections, termed SC21xx, for use in a helicopter blade is disclosed. The airfoil (36) achieves maximum lift performance equivalent to prior art airfoil configurations without incurring increased aerodynamic drag at high velocities. The airfoil (36) was developed by thickening and drooping the leading edge region (38) of the prior art airfoil (30) improving lift in the leading edge region (38) and delaying the formation of sonic shock waves at high velocities.Type: GrantFiled: May 17, 1990Date of Patent: May 14, 1991Assignee: United Technologies CorporationInventors: David A. Lednicer, Stephen J. Owen