Patents by Inventor David D. North
David D. North 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: 20240375799Abstract: An aircraft includes an onboard power supply, an empennage assembly, and a horizontal main wing each connected to a fuselage, and a vertical cross-wing arranged orthogonally with respect to the main wing. Flight control surfaces are arranged on the empennage assembly, vertical cross-wing, and horizontal main wing. A distributed propulsion system includes a first pair of propellers connected to the horizontal main wing and a second pair of propellers connected to the vertical cross-wing. Each of the propellers is connected to and powered by the power supply. Each propeller forms an acute canting angle with respect to an axis of the particular horizontal main wing or the vertical cross-wing to which the propeller is connected. The flight modes may include vertical takeoff and landing (VTOL), hover mode, rapid descent, and forward and backward flight modes. The propellers are unpowered during the rapid descent mode.Type: ApplicationFiled: April 30, 2024Publication date: November 14, 2024Inventors: STEVEN C. GEUTHER, DAVID D. NORTH, BRIAN E. DUVALL, JACOB R. SCHAEFER
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Patent number: 12006030Abstract: An aircraft wing configuration for a vertical or a short take-off and landing aircraft having a plurality of propeller-blown wings mounted at different longitudinal locations along a fuselage of the vertical take-off and landing aircraft, producing two or more lifting surfaces, fixed at a predetermined acute wing angle greater than 0° and substantially less than 90° relative to a horizontal plane, and having a plurality of flaps disposed behind the wings. The configuration has a plurality of propellers distributed in front of the plurality of wings producing two or more lifting surfaces and mounted such that the wings are externally blown by forced airstreams from the propellers. The propellers produce distributed thrust components, and the plurality of flaps are in the forced airstreams of the propellers when one or more of the flaps is in an extended position.Type: GrantFiled: April 24, 2020Date of Patent: June 11, 2024Assignee: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASAInventors: Steven C. Geuther, David D. North, Robert G. McSwain, Michael D. Patterson, Gregory Howland, Jared S. Fell, Christopher M. Cagle, Xiaofan Fei, Siena K. S. Whiteside, David A. Hare
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Patent number: 11613349Abstract: The presently disclosed embodiments relate to vertical takeoff and landing (VTOL) aircraft that have the capability of hovering in both a “nose forward” and a “nose up” orientation, and any orientation between those two. The disclosed aircraft can also transition into wing born (non-hovering) flight from any of the hovering orientations. In addition, certain of the disclosed embodiments can, if desired, use only vectored thrust control to maintain stable flight in both hover and forward flight. No control surfaces (e.g. ailerons, elevators, rudders, flaps) are required to maintain a stable vehicle attitude. However, the disclosure contemplates aircraft both with and without such control surfaces.Type: GrantFiled: May 25, 2021Date of Patent: March 28, 2023Assignee: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASAInventors: David D. North, Michael P. Hendrickson, Joshua C. Glaab
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Publication number: 20210331791Abstract: An aircraft wing configuration for a vertical or a short take-off and landing aircraft having a plurality of propeller-blown wings mounted at different longitudinal locations along a fuselage of the vertical take-off and landing aircraft, producing two or more lifting surfaces, fixed at a predetermined acute wing angle greater than 0° and substantially less than 90° relative to a horizontal plane, and having a plurality of flaps disposed behind the wings. The configuration has a plurality of propellers distributed in front of the plurality of wings producing two or more lifting surfaces and mounted such that the wings are externally blown by forced airstreams from the propellers. The propellers produce distributed thrust components, and the plurality of flaps are in the forced airstreams of the propellers when one or more of the flaps is in an extended position.Type: ApplicationFiled: April 24, 2020Publication date: October 28, 2021Inventors: Steven C. Geuther, David D. North, Robert G. McSwain, Michael D. Patterson, Gregory Howland, Jared S. Fell, Christopher M. Cagle, Xiaofan Fei, Siena K.S. Whiteside, David A. Hare
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Publication number: 20210276709Abstract: The presently disclosed embodiments relate to vertical takeoff and landing (VTOL) aircraft that have the capability of hovering in both a “nose forward” and a “nose up” orientation, and any orientation between those two. The disclosed aircraft can also transition into wing born (non-hovering) flight from any of the hovering orientations. In addition, certain of the disclosed embodiments can, if desired, use only vectored thrust control to maintain stable flight in both hover and forward flight. No control surfaces (e.g. ailerons, elevators, rudders, flaps) are required to maintain a stable vehicle attitude. However, the disclosure contemplates aircraft both with and without such control surfaces.Type: ApplicationFiled: May 25, 2021Publication date: September 9, 2021Inventors: DAVID D. NORTH, MICHAEL P. HENDRICKSON, JOSHUA . GLAAB
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Patent number: 11014664Abstract: The presently disclosed embodiments relate to vertical takeoff and landing (VTOL) aircraft that have the capability of hovering in both a “nose forward” and a “nose up” orientation, and any orientation between those two. The disclosed aircraft can also transition into wing born (non-hovering) flight from any of the hovering orientations. In addition, certain of the disclosed embodiments can, if desired, use only vectored thrust control to maintain stable flight in both hover and forward flight. No control surfaces (e.g. ailerons, elevators, rudders, flaps) are required to maintain a stable vehicle attitude. However, the disclosure contemplates aircraft both with and without such control surfaces.Type: GrantFiled: August 21, 2018Date of Patent: May 25, 2021Assignee: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASAInventors: David D. North, Michael P. Hendrickson, Joshua C. Glaab
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Patent number: 10538321Abstract: Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.Type: GrantFiled: September 11, 2018Date of Patent: January 21, 2020Assignee: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASAInventors: David D. North, Mark J. Aull, William J. Fredericks, Mark D. Moore, Paul M. Rothhaar, William T. Hodges, Zachary R. Johns
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Patent number: 10370100Abstract: A vehicle includes a wing and a control surface pivotably coupled to the wing and configured to pivot about a range of motion. A propulsor is coupled to the control surface and configured to rotate between a first position associated with a hover flight mode and a second position associated with a forward flight mode. The propulsor is aerodynamically actuated between the first position and the second position due to aerodynamics about the wing. The propulsor may rotate from an initial flight mode, such as a takeoff mode, to a second flight mode, such as a forward flight mode.Type: GrantFiled: March 22, 2016Date of Patent: August 6, 2019Assignee: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASAInventors: Paul M. Rothhaar, William J. Fredericks, David D. North
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Publication number: 20190061936Abstract: The presently disclosed embodiments relate to vertical takeoff and landing (VTOL) aircraft that have the capability of hovering in both a “nose forward” and a “nose up” orientation, and any orientation between those two. The disclosed aircraft can also transition into wing born (non-hovering) flight from any of the hovering orientations. In addition, certain of the disclosed embodiments can, if desired, use only vectored thrust control to maintain stable flight in both hover and forward flight. No control surfaces (e.g. ailerons, elevators, rudders, flaps) are required to maintain a stable vehicle attitude. However, the disclosure contemplates aircraft both with and without such control surfaces.Type: ApplicationFiled: August 21, 2018Publication date: February 28, 2019Inventors: David D. North, Michael P. Hendrickson, Joshua C. Glaab
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Publication number: 20190016459Abstract: Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.Type: ApplicationFiled: September 11, 2018Publication date: January 17, 2019Inventors: DAVID D. NORTH, MARK J. AULL, WILLIAM J. FREDERICKS, MARK D. MOORE, PAUL M. ROTHHAAR, WILLIAM T. HODGES, ZACHARY R. JOHNS
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Patent number: 10071801Abstract: Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.Type: GrantFiled: March 24, 2016Date of Patent: September 11, 2018Assignee: THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASAInventors: David D. North, Mark J. Aull, William J. Fredericks, Mark D. Moore, Paul M. Rothhaar, William T. Hodges, Zachary R. Johns
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Patent number: 9896200Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.Type: GrantFiled: October 24, 2016Date of Patent: February 20, 2018Assignee: THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASAInventors: William J. Fredericks, Mark D. Moore, Ronald C. Busan, Paul M. Rothhaar, David D. North, William M. Langford, Christopher T. Laws, William T. Hodges, Zachary R. Johns, Sandy R. Webb
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Patent number: 9599995Abstract: A kite system includes a kite and a ground station. The ground station includes a sensor that can be utilized to determine an angular position and velocity of the kite relative to the ground station. A controller utilizes a fuzzy logic control system to autonomously fly the kite. The system may include a ground station having powered winding units that generate power as the lines to the kite are unreeled. The control system may be configured to fly the kite in a crosswind trajectory to increase line tension for power generation. The sensors for determining the position of the kite are preferably ground-based.Type: GrantFiled: December 4, 2014Date of Patent: March 21, 2017Assignee: THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONInventors: David D. North, Mark J. Aull
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Publication number: 20170057631Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.Type: ApplicationFiled: October 24, 2016Publication date: March 2, 2017Inventors: William J. FREDERICKS, Mark D. MOORE, Ronald C. BUSAN, Paul M. ROTHHAAR, David D. NORTH, William M. LANGFORD, Christopher T. LAWS, William T HODGES, Zachary R. JOHNS, Sandy R. WEBB
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Patent number: 9475579Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.Type: GrantFiled: August 13, 2014Date of Patent: October 25, 2016Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: William J. Fredericks, Mark D. Moore, Ronald C. Busan, Paul M. Rothhaar, David D. North, William M. Langford, Christopher T. Laws, William T. Hodges, Zachary R. Johns, Sandy R. Webb
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Publication number: 20160288903Abstract: A vehicle includes a wing and a control surface pivotably coupled to the wing and configured to pivot about a range of motion. A propulsor is coupled to the control surface and configured to rotate between a first position associated with a hover flight mode and a second position associated with a forward flight mode. The propulsor is aerodynamically actuated between the first position and the second position due to aerodynamics about the wing. The propulsor may rotate from an initial flight mode, such as a takeoff mode, to a second flight mode, such as a forward flight mode.Type: ApplicationFiled: March 22, 2016Publication date: October 6, 2016Inventors: PAUL M. ROTHHAAR, WILLIAM J. FREDERICKS, DAVID D. NORTH
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Publication number: 20160244158Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.Type: ApplicationFiled: August 13, 2014Publication date: August 25, 2016Inventors: WILLIAM J. FREDERICKS, Mark D. Moore, Ronald C. Busan, Paul M. Rothhaar, David D. North, William M. Langford, Christopher T. Laws, William T. Hodges, Zachary R. Johns, Sandy R. Webb
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Publication number: 20160200436Abstract: Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.Type: ApplicationFiled: March 24, 2016Publication date: July 14, 2016Inventors: David D. North, Mark J. Aull, William J. Fredericks, Mark D. Moore, Paul M. Rothhaar, WILLIAM T. Hodges, Zachary R. Johns
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Publication number: 20150153741Abstract: A kite system includes a kite and a ground station. The ground station includes a sensor that can be utilized to determine an angular position and velocity of the kite relative to the ground station. A controller utilizes a fuzzy logic control system to autonomously fly the kite. The system may include a ground station having powered winding units that generate power as the lines to the kite are unreeled. The control system may be configured to fly the kite in a crosswind trajectory to increase line tension for power generation. The sensors for determining the position of the kite are preferably ground-based.Type: ApplicationFiled: December 4, 2014Publication date: June 4, 2015Inventors: DAVID D. NORTH, MARK J. AULL
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Patent number: 8922041Abstract: A kite system includes a kite and a ground station. The ground station includes a sensor that can be utilized to determine an angular position and velocity of the kite relative to the ground station. A controller utilizes a fuzzy logic control system to autonomously fly the kite. The system may include a ground station having powered winding units that generate power as the lines to the kite are unreeled. The control system may be configured to fly the kite in a crosswind trajectory to increase line tension for power generation. The sensors for determining the position of the kite are preferably ground-based.Type: GrantFiled: February 13, 2013Date of Patent: December 30, 2014Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: David D. North, Mark J. Aull