Patents by Inventor Eric Lucien Nussenblatt
Eric Lucien Nussenblatt 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: 11235869Abstract: An aircraft includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail. The translational thrust system provides translational thrust to the airframe. An upper hub fairing is positioned at the upper rotor assembly. A lower hub fairing is positioned at the lower rotor assembly. A shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The upper hub fairing is substantially sealed to the shaft fairing and the lower hub fairing is substantially sealed to the shaft fairing.Type: GrantFiled: March 27, 2020Date of Patent: February 1, 2022Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Thomas Alan Egolf, Robert D. Beatty, Gary Law, Chris P. Butler, Eric Lucien Nussenblatt, Edward Reed
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Patent number: 10793264Abstract: A rotor assembly for a rotary wing aircraft includes a rotor hub having a central axis, the rotor hub rotatable about the central axis. A plurality of flexible structural members extend radially outwardly from the rotor hub, each flexible structural member substantially U-shaped and having a first arm extending from the hub, a second arm extending from the hub, and an end portion connecting the first arm to the second arm at a radially outboard end of the flexible structural member. A clamp member is positioned between the first arm and the second arm of each structural member and secured thereto to tie deflection of the first arm to deflection of the second arm. A rotor blade is secured to each flexible structural member of the plurality of flexible structural members via the clamp member.Type: GrantFiled: June 26, 2015Date of Patent: October 6, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Eric Lucien Nussenblatt, David H. Hunter, Justin Thomas
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Publication number: 20200223536Abstract: An aircraft includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail. The translational thrust system provides translational thrust to the airframe. An upper hub fairing is positioned at the upper rotor assembly. A lower hub fairing is positioned at the lower rotor assembly. A shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The upper hub fairing is substantially sealed to the shaft fairing and the lower hub fairing is substantially sealed to the shaft fairing.Type: ApplicationFiled: March 27, 2020Publication date: July 16, 2020Inventors: Thomas Alan Egolf, Robert D. Beatty, Gary Law, Chris P. Butler, Eric Lucien Nussenblatt, Edward Reed
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Patent number: 10669022Abstract: A bearing arrangement for use with a structure defining an outer surface which expands and contracts inward and outward relative to the structure includes, a member having at least one inner surface to face the outer surface, and at least one protrusion extending from the inner surface, the at least one protrusion being biased toward and in contact with the outer surface and maintains contact as the structure expands and contracts.Type: GrantFiled: August 25, 2016Date of Patent: June 2, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: David H. Hunter, Eric Lucien Nussenblatt
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Patent number: 10654566Abstract: A main rotor system for a rotary wing aircraft is provided including a lower rotor hub to which lower rotor blades are attachable. The lower rotor hub rotates about an axis in a first direction. A hollow rotor shaft extends through the lower rotor hub. The first end of the rotor shaft couples to a component of the rotary wing aircraft for rotation about an axis. An upper rotor hub arranged at the second end of the rotor shaft includes a plurality of similar upper rotor members equidistantly spaced about a circumference of the rotor shaft to form an open center aligned with a hollow interior of the rotor shaft. An opening configured to receive an upper rotor blade is formed between adjacent upper rotor members and the upper rotor hub is configured to rotate in a second direction, opposite the first direction.Type: GrantFiled: September 28, 2015Date of Patent: May 19, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Ron William Waldo, Eric Lucien Nussenblatt, David H. Hunter, Bryan Kenneth Baskin
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Patent number: 10618630Abstract: A rotor assembly for a rotary wing aircraft includes a rotor hub having a central axis. The rotor hub is rotatable about the central axis. A plurality of flexible structural members extend radially outwardly from the rotor hub. Each flexible structural member is substantially U-shaped having a first arm extending from the hub, a second arm extending from the hub, and an end portion connecting the first arm to the second arm at a radially outboard end of the flexible structural member. The first arm, the second arm and/or the end portion have a cross section with a height along the central axis greater than a thickness of the cross section to increase stiffness of the rotor assembly along the central axis. The rotor assembly further includes a plurality of rotor blades, each rotor blade being secured to each flexible structural member of the plurality of flexible structural members.Type: GrantFiled: August 5, 2015Date of Patent: April 14, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Eric Lucien Nussenblatt, David H. Hunter
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Patent number: 10618643Abstract: A rotor hub assembly is provided including an open rotor hub having a base plate and a plurality of rotor members mounted about a circumference of the base plate. The rotor members are configured to form a plurality of rotor blade openings between adjacent rotor members, and a central opening between all of the rotor members. A plate includes a central body portion and a plurality of arms. Each of the plurality of arms is configured to mount to one of the plurality of rotor members such that the central body portion is generally positioned within the central opening of the open rotor hub.Type: GrantFiled: December 4, 2013Date of Patent: April 14, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Ron William Waldo, Eric Lucien Nussenblatt, Bryan Kenneth Baskin, David H. Hunter
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Patent number: 10611471Abstract: A rotor blade rotated about a rotor hub is provided including a first section configured to mount to the rotor hub. The first section includes a spindle and an inboard torque tube surrounding a portion of the spindle. A second section of the rotor blade includes a flexbeam and an outboard torque tube attached to and surrounding the flexbeam. An inboard end of the flexbeam is rotatable coupled to a first end of the spindle. The second section is configured to rotate about a blade axis between an aligned position and a rotated position. A transitional brace configured to surround a portion of the rotor blade adjacent the coupled flexbeam and spindle is movable between a first position and a second position. When in the first position, the transitional brace limits movement of the second section about the blade axis.Type: GrantFiled: May 1, 2015Date of Patent: April 7, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: David H. Hunter, Eric Lucien Nussenblatt
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Patent number: 10549841Abstract: A pin wrap having a unitary construction that includes a first elongated arm extending from an inboard end to an outboard end; a second elongated arm extending from the inboard end to the outboard end; and a curved end having an internal surface and a directly opposing external surface. The curved end integrally connects the first elongated arm to the second elongated arm at the outboard end. Also, the curved end is arcuate having a plurality of radii of curvatures. A blade and a helicopter with a blade can include the pin wrap.Type: GrantFiled: May 20, 2015Date of Patent: February 4, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Eric Lucien Nussenblatt, David H. Hunter
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Patent number: 10400851Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly with an upper blade and a lower rotor assembly with a lower blade. A first antenna in one of upper blade and the lower blade, and a second antenna in the other of the upper blade and the lower blade. An oscillator to apply an excitation signal to the first antenna. A blade proximity monitor to monitor a magnitude of the excitation signal and an output signal from the second antenna to determine a distance between the upper blade and the lower blade.Type: GrantFiled: September 30, 2015Date of Patent: September 3, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Maximilian August Koessick, Michael J. Kostoss, Eric Lucien Nussenblatt, Justin Thomas, Christopher Paul Butler, Brandon Michael Cerge
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Patent number: 10214284Abstract: A pitch bearing for connecting first and second articles is provided. The first article includes a first curved outer surface and the second article includes a second curved outer surface opposite the first curved outer surface. The pitch bearing includes an axisymmetric structure interposed between the first and second curved outer surfaces. The axisymmetric structure includes compliant layers and stabilizing layers interleaved between the compliant layers. The compliant layers and the stabilizing layers proximate to the first article haves a curvature matching that of the first curved outer surface. The compliant layers and the stabilizing layers proximate to the second article have a curvature matching that of the second curved outer surface. A shear stiffness of each of the stabilizing layers is greater than a shear stiffness of each of the compliant layers.Type: GrantFiled: September 30, 2013Date of Patent: February 26, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: David H. Hunter, Eric S. Parsons, Eric Lucien Nussenblatt, Ryan Thomas Casey
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Patent number: 10173770Abstract: A cylindrical elastomeric bearing including a plurality of elastomeric layers arranged about a central bore. The elastomeric layers are characterized by a middle portion having a first thickness and two outer portions having a second thickness, the second thickness being greater than the first thickness, the one or more elastomeric layers being tapered between the middle portion and the outer portions. One or more shim layers, each of the plurality of shim layers being arranged between two of the plurality of elastomeric layers. The shim layers are shaped to fit with the elastomer layers.Type: GrantFiled: September 17, 2015Date of Patent: January 8, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Eric Lucien Nussenblatt, David H. Hunter
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Publication number: 20180237134Abstract: A bearing arrangement for use with a structure defining an outer surface which expands and contracts inward and outward relative to the structure includes, a member having at least one inner surface to face the outer surface, and at least one protrusion extending from the inner surface, the at least one protrusion being biased toward and in contact with the outer surface and maintains contact as the structure expands and contracts.Type: ApplicationFiled: August 25, 2016Publication date: August 23, 2018Inventors: David H. Hunter, Eric Lucien Nussenblatt
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Publication number: 20170305543Abstract: An aircraft includes an airframe; an extending tail; a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly; a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe; an upper hub fairing positioned at the upper rotor assembly; a lower hub fairing positioned at the lower rotor assembly; and a shaft fairing disposed between the upper hub fairing and the lower hub fairing; wherein the upper hub fairing is substantially sealed to the shaft fairing and the lower hub fairing is substantially sealed to the shaft fairing.Type: ApplicationFiled: October 1, 2015Publication date: October 26, 2017Applicant: SIKORSKY AIRCRAFT CORPORATIONInventors: Robert C. Moffitt, William J. Eadie, David H. Hunter, Bryan Kenneth Baskin, Chris Paul Butler, Lance Halcom, Eric Lucien Nussenblatt
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Publication number: 20170297688Abstract: A main rotor system for a rotary wing aircraft is provided including a lower rotor hub to which lower rotor blades are attachable. The lower rotor hub rotates about an axis in a first direction. A hollow rotor shaft extends through the lower rotor hub. The first end of the rotor shaft couples to a component of the rotary wing aircraft for rotation about an axis. An upper rotor hub arranged at the second end of the rotor shaft includes a plurality of similar upper rotor members equidistantly spaced about a circumference of the rotor shaft to form an open center aligned with a hollow interior of the rotor shaft. An opening configured to receive an upper rotor blade is formed between adjacent upper rotor members and the upper rotor hub is configured to rotate in a second direction, opposite the first direction.Type: ApplicationFiled: September 28, 2015Publication date: October 19, 2017Inventors: Ron William Waldo, Eric Lucien Nussenblatt, David H. Hunter, Bryan Kenneth Baskin
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Publication number: 20170297691Abstract: A cylindrical elastomeric bearing including a plurality of elastomeric layers arranged about a central bore. The elastomeric layers are characterized by a middle portion having a first thickness and two outer portions having a second thickness, the second thickness being greater than the first thickness, the one or more elastomeric layers being tapered between the middle portion and the outer portions. One or more shim layers, each of the plurality of shim layers being arranged between two of the plurality of elastomeric layers. The shim layers are shaped to fit with the elastomer layers.Type: ApplicationFiled: September 17, 2015Publication date: October 19, 2017Inventors: Eric Lucien Nussenblatt, David H. Hunter
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Publication number: 20170283046Abstract: An aircraft includes an airframe; an extending tail; a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly; a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe; an upper hub fairing positioned at the upper rotor assembly; a lower hub fairing positioned at the lower rotor assembly; and a shaft fairing disposed between the upper hub fairing and the lower hub fairing; wherein a geometry of at least one of the upper hub fairing and the lower hub fairing progressively blends from a circle to a series of curved elliptical surfaces in an inboard direction.Type: ApplicationFiled: October 1, 2015Publication date: October 5, 2017Inventors: Thomas Alan Egolf, Robert D. Beatty, Gary Law, Chris P. Butler, Eric Lucien Nussenblatt, Edward Reed
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Patent number: 9771152Abstract: A spar for a rotor blade assembly is provided including a generally hollow tubular body. A spacer protrudes from at least one surface of the body along a length of the body. A hole extends through the body and the spacer. The hole is configured to align with a through hole in an adjacent flexbeam assembly. The spacer is configured to contact a surface of the adjacent flexbeam assembly to create a match fit between the body and the flexbeam assembly.Type: GrantFiled: March 20, 2013Date of Patent: September 26, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Justin Thomas, Eric Lucien Nussenblatt, Eric S. Parsons, Ryan Thomas Casey, David H. Hunter
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Publication number: 20170217564Abstract: A rotor assembly for a rotary wing aircraft includes a rotor hub having a central axis. The rotor hub is rotatable about the central axis. A plurality of flexible structural members extend radially outwardly from the rotor hub. Each flexible structural member is substantially U-shaped having a first arm extending from the hub, a second arm extending from the hub, and an end portion connecting the first arm to the second arm at a radially outboard end of the flexible structural member. The first arm, the second arm and/or the end portion have a cross section with a height along the central axis greater than a thickness of the cross section to increase stiffness of the rotor assembly along the central axis. The rotor assembly further includes a plurality of rotor blades, each rotor blade being secured to each flexible structural member of the plurality of flexible structural members.Type: ApplicationFiled: August 5, 2015Publication date: August 3, 2017Inventors: Eric Lucien Nussenblatt, David H. Hunter
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Publication number: 20170217581Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly with a plurality of blades rotating in a first plane and a lower rotor assembly with a plurality of blades rotating in a second plane, each of the blades having a root end, a midpoint, and a tip end. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. The blades of the upper rotor assembly and the blades of the lower rotor assembly are indexed to improve tip end clearance between pairs of tip ends in the crossing plane as the tip ends move in respective first and second sinusoidal paths.Type: ApplicationFiled: September 29, 2015Publication date: August 3, 2017Inventors: David H. Hunter, Scott A. Chasen, Brandon Michael Cerge, Maximilian August Koessick, Michael J. Kostoss, Eric Lucien Nussenblatt, Justin Thomas, Chris P. Butler