Patents by Inventor Timothy Fred Lauder
Timothy Fred Lauder 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: 11186363Abstract: A rotary wing aircraft includes an airframe, a stationary mast fixedly engaged to the airframe and extending along a first axis, and an electric motor. The electric motor includes a stator assembly engaged to the mast and a rotor assembly disposed radially outward from the stator assembly and configured to rotate with respect to the stator assembly. A plurality of rotor blades project radially outward from the rotor assembly.Type: GrantFiled: October 17, 2016Date of Patent: November 30, 2021Assignee: Sikorsky Aircraft CorporationInventors: Timothy Fred Lauder, Jonathan Hartman, Peter James Waltner
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Patent number: 10752343Abstract: An electric propulsion system includes a mast defining an axis of rotation. At least one yoke is rotatably mounted to the mast. A fairing assembly surrounds the at least one yoke. An electric motor includes a stator assembly associated with the fairing assembly and a rotor assembly associated with the yoke.Type: GrantFiled: October 18, 2016Date of Patent: August 25, 2020Assignee: Sikorsky Aircraft CorporationInventor: Timothy Fred Lauder
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Patent number: 10577090Abstract: An electric propulsion system for use with a mast defining an axis of rotation and one or more rotor blades which rotate about the axis of rotation, includes a yoke assembly, electric motor, motor support housing, and overrunning clutch. The yoke assembly is rotatable with respect to the mast, and configured to support one or more of the rotor blades. The motor includes a motor-stator and a motor-rotor, and is arranged circumferentially around the mast. The housing circumferentially surrounds the mast and includes a rotatable portion attached to and rotatable with the yoke assembly. The overrunning clutch includes an inner hub rotatable with the motor-rotor, and an outer hub rotatable with the rotatable portion of the housing. The overrunning clutch is configured to transfer torque from the motor to the yoke assembly in a drive mode, and configured to disengage the yoke assembly from the motor in an overrunning mode.Type: GrantFiled: February 16, 2017Date of Patent: March 3, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventor: Timothy Fred Lauder
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Patent number: 10389078Abstract: A cooling system for a rotorcraft laser system is provided. The cooling system includes at least one laser carrying component operatively coupling a laser turret and a laser generating assembly. The cooling system also includes at least one fuel line fluidly coupled to a fuel tank containing a fuel. The cooling system further includes a heat exchanger containing a portion of the laser carrying component and the fuel line to transfer heat therebetween to cool the laser carrying component.Type: GrantFiled: December 10, 2015Date of Patent: August 20, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Alfred Russell Smiley, Panagiotis Koliais, Timothy Fred Lauder, Mark R. Alber
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Patent number: 10150567Abstract: A rotor system for a rotorcraft includes a first rotor assembly defining a rotation axis, a second rotor assembly offset from the first rotor assembly along the rotation axis, and a drive system connected to the first and second rotor assemblies. The drive system includes a first electric motor disposed along the rotation axis and operably connected to the first rotor assembly, and a second electric motor disposed along the rotation axis and operably connected to the second rotor assembly to rotate the second rotor assembly about the rotation axis independent of rotation of the first rotor assembly about the rotation axis.Type: GrantFiled: January 27, 2016Date of Patent: December 11, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Timothy Fred Lauder, Patrick Boyle
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Patent number: 10077108Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage with first and second wings extending outwardly from opposite sides of the fuselage, nacelles with proprotors respectively disposed on the first and second wings, the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and exhaust deflectors disposed proximate to trailing ends of the nacelles. The exhaust deflectors are disposed to assume at least first, second and third configurations respectively associated with first, second and third flight conditions.Type: GrantFiled: January 4, 2016Date of Patent: September 18, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventor: Timothy Fred Lauder
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Publication number: 20180261966Abstract: A cooling system for a rotorcraft laser system is provided. The cooling system includes at least one laser carrying component operatively coupling a laser turret and a laser generating assembly. The cooling system also includes at least one fuel line fluidly coupled to a fuel tank containing a fuel. The cooling system further includes a heat exchanger containing a portion of the laser carrying component and the fuel line to transfer heat therebetween to cool the laser carrying component.Type: ApplicationFiled: December 10, 2015Publication date: September 13, 2018Applicant: Sikorsky Aircraft CorporationInventors: Alfred Russell Smiley, Panagiotis Koliais, Timothy Fred Lauder, Mark R. Alber
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Publication number: 20180229835Abstract: An electric propulsion system for use with a mast defining an axis of rotation and one or more rotor blades which rotate about the axis of rotation, includes a yoke assembly, electric motor, motor support housing, and overrunning clutch. The yoke assembly is rotatable with respect to the mast, and configured to support one or more of the rotor blades. The motor includes a motor-stator and a motor-rotor, and is arranged circumferentially around the mast. The housing circumferentially surrounds the mast and includes a rotatable portion attached to and rotatable with the yoke assembly. The overrunning clutch includes an inner hub rotatable with the motor-rotor, and an outer hub rotatable with the rotatable portion of the housing. The overrunning clutch is configured to transfer torque from the motor to the yoke assembly in a drive mode, and configured to disengage the yoke assembly from the motor in an overrunning mode.Type: ApplicationFiled: February 16, 2017Publication date: August 16, 2018Inventor: Timothy Fred Lauder
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Publication number: 20180105263Abstract: An electric propulsion system includes a mast defining an axis of rotation. At least one yoke is rotatably mounted to the mast. A fairing assembly surrounds the at least one yoke. An electric motor includes a stator assembly associated with the fairing assembly and a rotor assembly associated with the yoke.Type: ApplicationFiled: October 18, 2016Publication date: April 19, 2018Inventor: Timothy Fred Lauder
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Publication number: 20170341733Abstract: A rotor head is provided and includes a non-rotating frame, a rotating frame rotatable relative to the non-rotating frame and configured to impart motion to the rotating frame, a rotor hub assembly rotatable about a rotation axis and including a hub and blades extending outwardly from the hub and being pivotable about respective pitch axes thereof and rocker assemblies respectively associated with corresponding ones of the blades. Each rocker assembly is interconnected between the rotating frame and the corresponding one of the blades and configured to convert the motion imparted to the rotating frame into a pitching of one of the blades about the respective pitch axes and amplify the motion such that an angle of the pitching exceeds an angle that would be achieved if the corresponding one of the blades were connected directly to the rotating frame.Type: ApplicationFiled: March 23, 2017Publication date: November 30, 2017Inventors: Frank P. D'Anna, Timothy Fred Lauder, Mark R. Alber, Irving Lawrence Cullen, Bryan Kenneth Baskin
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Publication number: 20170297689Abstract: A rotary wing aircraft includes an airframe, a stationary mast fixedly engaged to the airframe and extending along a first axis, and an electric motor. The electric motor includes a stator assembly engaged to the mast and a rotor assembly disposed radially outward from the stator assembly and configured to rotate with respect to the stator assembly. A plurality of rotor blades project radially outward from the rotor assembly.Type: ApplicationFiled: October 17, 2016Publication date: October 19, 2017Inventors: Timothy Fred Lauder, Jonathan Hartman, Peter James Waltner
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Patent number: 9731832Abstract: A torque converter for converting torque between an input shaft and an output shaft includes an impeller operably connected to the input shaft and rotatable therewith. The torque converter further includes a turbine operably connected to the output shaft and rotatable therewith. A fluid flow system directs a flow of motive fluid through the impeller and through the turbine to drive rotation of the output shaft relative to the input shaft. A lockup mechanism is engageable to urge rotation of the output shaft at an output shaft rotational speed identical to an input shaft rotational speed. A switching module controls an actuation system to urge engagement of the lockup mechanism.Type: GrantFiled: June 20, 2013Date of Patent: August 15, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Michael Joseph DeVita, Mark Denton Bystry, Jr., Timothy Fred Lauder
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Publication number: 20170217576Abstract: A rotor drive system includes a mast defining a rotation axis, an electric motor with a stator portion fixed to the stationary mast, a rotor portion rotatably relative to the stator portion, and a clutch disposed along the rotation axis and connected to the rotor portion of the electric motor. A rotor assembly is rotatable about the rotation axis and operably connected to clutch such that, when rotational speed of the rotor assembly exceeds rotational speed of the rotor portion of the electric motor, the clutch disengages the rotor assembly from the electric motor rotor portion.Type: ApplicationFiled: January 29, 2016Publication date: August 3, 2017Inventors: Timothy Fred Lauder, Jonathan Hartman
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Publication number: 20170210480Abstract: A rotor system for a rotorcraft includes a first rotor assembly defining a rotation axis, a second rotor assembly offset from the first rotor assembly along the rotation axis, and a drive system connected to the first and second rotor assemblies. The drive system includes a first electric motor disposed along the rotation axis and operably connected to the first rotor assembly, and a second electric motor disposed along the rotation axis and operably connected to the second rotor assembly to rotate the second rotor assembly about the rotation axis independent of rotation of the first rotor assembly about the rotation axis.Type: ApplicationFiled: January 27, 2016Publication date: July 27, 2017Inventors: Timothy Fred Lauder, Patrick Boyle
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Publication number: 20170183091Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage with first and second wings extending outwardly from opposite sides of the fuselage, nacelles with proprotors respectively disposed on the first and second wings, the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and exhaust deflectors disposed proximate to trailing ends of the nacelles. The exhaust deflectors are disposed to assume at least first, second and third configurations respectively associated with first, second and third flight conditions.Type: ApplicationFiled: January 4, 2016Publication date: June 29, 2017Inventor: Timothy Fred Lauder
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Publication number: 20170129597Abstract: An aircraft comprising an airframe; a rotor system mounted to the airframe, the rotor system including a plurality of rotor blades, each of the plurality of rotor blades including a root portion extending to a tip portion through an airfoil portion, the airfoil portion having a leading edge and a trailing edge; at least one control surface mounted within the airfoil portion of at least one of the plurality of rotor blades; at least one actuator configured to actuate the at least one control surface; and at least one actuator configured to pitch at least one of the plurality of rotor blades about a blade pitch axis.Type: ApplicationFiled: November 10, 2016Publication date: May 11, 2017Inventors: Timothy Fred Lauder, Jonathan Hartman, Nicholas D. Lappos
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Publication number: 20170021924Abstract: A tail sitter aircraft is capable of forward flight and hover operations. The tail sitter aircraft includes a wing and first and second prop-nacelles supportively disposed on the wing. Each of the first and second prop-nacelles includes an articulable rotor, which is rotatable about variable rotational axes and which includes blades that are collectively and cyclically controllable in both forward flight and hover regimes.Type: ApplicationFiled: May 18, 2016Publication date: January 26, 2017Inventors: Stephen Kubik, Joseph T. Driscoll, Frank P. D'Anna, Mark R. Alber, Timothy Fred Lauder, Cody Fegely
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Publication number: 20160304195Abstract: An aircraft is provided and includes a propeller to generate aircraft thrust, a prop-nacelle housing and supporting the propeller, a wing supporting the prop nacelle and including first coupling elements. The first coupling elements are each configured to selectively couple with a second set of coupling elements associated with a group of interchangeable fuselages.Type: ApplicationFiled: February 12, 2016Publication date: October 20, 2016Inventors: Mark R. Alber, Charles Gayagoy, Jeffrey Parkhurst, Timothy Fred Lauder, Michael Joseph DeVita
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Patent number: 9452831Abstract: An individual blade control system (IBCS) for a rotor system having a rotor hub is provided including a plurality of blade cuffs mounted to the rotor hub. Each blade cuff is configured to receive a rotor blade and rotate about a blade axis. A plurality of electrical actuators is mounted to the rotor hub adjacent at least one of the plurality of blade cuffs. Each electrical actuator is configured to rotate about an actuator axis. The plurality of blade axes and the plurality of actuator axes are arranged in a plane. Each electrical actuator is coupled to an adjacent blade cuff such that rotation of one of the plurality of electrical actuators causes a proportional rotation of one of the blade cuffs.Type: GrantFiled: April 22, 2013Date of Patent: September 27, 2016Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Bryan D. Mayrides, William A. Welsh, Michael Joseph DeVita, Timothy Fred Lauder
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Patent number: 9435261Abstract: A fluid cooled system includes a first heat generating component. A first airflow pathway directs a first flow of air across a first heat exchanger. A second airflow pathway directs a second flow of air across a second heat exchanger. A first working fluid is flowed from the first heat generating component, through the first heat exchanger and through the second heat exchanger and returned to the first heat generating component.Type: GrantFiled: October 5, 2012Date of Patent: September 6, 2016Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Michael Joseph DeVita, Timothy Fred Lauder, Mark Denton Bystry