Patents by Inventor Thomas A. Zientek
Thomas A. Zientek 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: 9487291Abstract: A method and apparatus for moving a blade of a rotorcraft. The method comprises operating the rotorcraft and applying a torque to an elongate member connected to a tip portion of the blade during operation of the rotorcraft using a tip actuation mechanism that is external to the blade and associated with the elongate member such that the tip portion of the blade rotates about an axis through the blade.Type: GrantFiled: December 5, 2012Date of Patent: November 8, 2016Assignee: THE BOEING COMPANYInventors: Thomas A. Zientek, Terrence S. Birchette, Friedrich K. Straub
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Patent number: 9284727Abstract: An acoustic barrier structure can include a support structure that defines a plurality of cells, a weight attached to the support structure, and at least one resonant membrane covering one of the plurality of cells. The at least one resonant membrane can comprise at least one weight. The at least one resonant membrane can have an anti-resonant frequency and the support structure with the weight can provide wide frequency band gaps between odd resonance modes while suppressing structure-membrane coupled modes to enable the anti-resonance of the at least one resonant membrane.Type: GrantFiled: September 25, 2014Date of Patent: March 15, 2016Assignee: The Boeing CompanyInventors: Geoffrey P. McKnight, Chia-Ming Chang, Tiffany A. Stewart, Joshua M. Montgomery, Janet M. Hogan, Thomas A. Zientek, Douglas R. Ludin
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Publication number: 20150027807Abstract: An acoustic barrier structure can include a support structure that defines a plurality of cells, a weight attached to the support structure, and at least one resonant membrane covering one of the plurality of cells. The at least one resonant membrane can comprise at least one weight. The at least one resonant membrane can have an anti-resonant frequency and the support structure with the weight can provide wide frequency band gaps between odd resonance modes while suppressing structure-membrane coupled modes to enable the anti-resonance of the at least one resonant membrane.Type: ApplicationFiled: September 25, 2014Publication date: January 29, 2015Inventors: Geoffrey P. McKnight, Chia-Ming Chang, Tiffany A. Stewart, Joshua M. Montgomery, Janet M. Hogan, Thomas A. Zientek, Douglas R. Ludin
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Patent number: 8869933Abstract: An acoustic barrier structure can include a support structure that defines a plurality of cells, a weight attached to the support structure, and at least one resonant membrane covering one of the plurality of cells. The at least one resonant membrane can comprise at least one weight. The at least one resonant membrane can have an anti-resonant frequency and the support structure with the weight can provide wide frequency band gaps between odd resonance modes while suppressing structure-membrane coupled modes to enable the anti-resonance of the at least one resonant membrane.Type: GrantFiled: July 29, 2013Date of Patent: October 28, 2014Assignee: The Boeing CompanyInventors: Geoffrey P. McKnight, Chia-Ming Chang, Tiffany A. Stewart, Joshua M. Montgomery, Janet M. Hogan, Thomas A. Zientek, Douglas R. Ludin
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Patent number: 8360721Abstract: A stiff in-plane gimbaled rotor head for a rotorcraft, such as a helicopter, includes a vertically extending rotor shaft, a center hub disposed on the rotor shaft for conjoint rotation therewith, and an outer hub surrounding the center hub and coupled thereto through a spherical gimbal bearing for conjoint rotation therewith, and such that the outer hub is also capable of an angular range of gimbaling movement relative to the center hub. A plurality of rotor blades, which may include three or more blades, is coupled to the rotor shaft through the inner and outer hubs by a constant velocity joint that enables the blades to be rotated in a common plane about the axis of the rotor shaft while controlling the respective pitches of the blades and such that any other relative in-plane and out-of-plane movements of the blades during rotation is prevented.Type: GrantFiled: January 8, 2008Date of Patent: January 29, 2013Assignee: The Boeing CompanyInventors: Daniel M. Podgurski, Thomas A. Zientek, Evhen M. Mychalowycz
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Patent number: 7757992Abstract: Embodiments of systems and methods for enhancing the performance of rotary wing aircraft through reduced torque, noise and vibration are disclosed. In one embodiment, a method includes configuring the rotorcraft in a selected flight condition, communicating input signals to a control system operable to position sails coupled to tips of blades of a rotor assembly, processing the input signals according to a constraint condition to generate sail positional information, and transferring the sail positional information to the sail. Alternately, input signals may be communicated to a control system operable to position a plurality of sails, each sail having an aerodynamic shape and positioned proximate to a tip portion of the rotor blade. The input signals may be configured to rotate each sail about a longitudinal axis into a corresponding pitch angle independently of the other sails.Type: GrantFiled: May 23, 2007Date of Patent: July 20, 2010Assignee: The Boeing CompanyInventors: Richard Bussom, Michael A. McVeigh, Robert P. Narducci, Thomas A. Zientek
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Publication number: 20100012770Abstract: Embodiments of systems and methods for enhancing the performance of rotary wing aircraft through reduced torque, noise and vibration are disclosed. In one embodiment, a method includes configuring the rotorcraft in a selected flight condition, communicating input signals to a control system operable to position sails coupled to tips of blades of a rotor assembly, processing the input signals according to a constraint condition to generate sail positional information, and transferring the sail positional information to the sail. Alternately, input signals may be communicated to a control system operable to position a plurality of sails, each sail having an aerodynamic shape and positioned proximate to a tip portion of the rotor blade. The input signals may be configured to rotate each sail about a longitudinal axis into a corresponding pitch angle independently of the other sails.Type: ApplicationFiled: May 23, 2007Publication date: January 21, 2010Applicant: THE BOEING COMPANYInventors: Richard Bussom, Michael A. McVeigh, Robert P. Narducci, Thomas A. Zientek
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Publication number: 20090175725Abstract: A stiff in-plane gimbaled rotor head for a rotorcraft, such as a helicopter, includes a vertically extending rotor shaft, a center hub disposed on the rotor shaft for conjoint rotation therewith, and an outer hub surrounding the center hub and coupled thereto through a spherical gimbal bearing for conjoint rotation therewith, and such that the outer hub is also capable of an angular range of gimbaling movement relative to the center hub. A plurality of rotor blades, which may include three or more blades, is coupled to the rotor shaft through the inner and outer hubs by a constant velocity joint that enables the blades to be rotated in a common plane about the axis of the rotor shaft while controlling the respective pitches of the blades and such that any other relative in-plane and out-of-plane movements of the blades during rotation is prevented.Type: ApplicationFiled: January 8, 2008Publication date: July 9, 2009Inventors: Daniel M. Podgurski, Thomas A. Zientek, Evhen M. Mychalowycz
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Patent number: 7281900Abstract: Low-noise airfoils and methods of reducing noise. One embodiment provides an aerodynamic member that includes two body portions coupled to each other. The second body portion includes a plurality of airfoil members in a fixed relationship with each other. Optionally, the airfoil members may define an open end of the second body portion. In the alternative, the member can include a third body portion that has an airfoil shape and that is coupled to the second body portion opposite the first body portion. Preferably, the first portion, the airfoil members, and third portion are 12%, 8%, and 2% thickness/chord airfoils respectively. Further, the aerodynamic member may be a rotor blade on a tandem helicopter. Another embodiment provides a cambered airfoil with two coupled body portions one of which has air foil members. One of the body portions includes a slot there through with airfoil members on opposite sides of the slot.Type: GrantFiled: May 13, 2005Date of Patent: October 16, 2007Assignee: The Boeing CompanyInventor: Thomas A. Zientek
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Patent number: 7264200Abstract: The present invention discloses systems and methods for the performance enhancement of rotary wing aircraft through reduced torque, noise and vibration. In one embodiment, a system includes a sail having an aerodynamic shape positioned proximate to a tip of the rotor blade. An actuator may be configured to rotate the sail relative to the blade tip. a A control system receives information from a rotorcraft system and commands the actuator to rotate the sail to a predetermined favorable rotor blade operating condition. In another embodiment, a method includes configuring the rotorcraft in a selected flight condition, communicating input signals to a control system operable to position sails coupled to tips of blades of a rotor assembly, processing the input signals according to a constraint condition to generate sail positional information, and transferring the sail positional information to the sail.Type: GrantFiled: July 23, 2004Date of Patent: September 4, 2007Assignee: The Boeing CompanyInventors: Richard Bussom, Michael A. McVeigh, Robert P. Narducci, Thomas A. Zientek
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Patent number: 7264199Abstract: A rotor system (12) for a helicopter (10) includes a rotating shaft (82). A gimbaled hub assembly (56) is coupled to the rotating shaft (82). Rotating blades (24) and non-rotating blades (33) are coupled to the gimbaled hub assembly (56). The non-rotating blades (33) provide lift for the helicopter (10) in forward flight unloading the rotating blades. The rotating and non-rotating blades (24, 33) provide equal and opposite rolling moments for lift offset operation.Type: GrantFiled: October 18, 2005Date of Patent: September 4, 2007Assignee: The Boeing CompanyInventor: Thomas A. Zientek
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Publication number: 20070084962Abstract: A rotor system (12) for a helicopter (10) includes a rotating shaft (82). A gimbaled hub assembly (56) is coupled to the rotating shaft (82). Rotating blades (24) and non-rotating blades (33) are coupled to the gimbaled hub assembly (56). The non-rotating blades (33) provide lift for the helicopter (10) in forward flight unloading the rotating blades. The rotating and non-rotating blades (24, 33) provide equal and opposite rolling moments for lift offset operation.Type: ApplicationFiled: October 18, 2005Publication date: April 19, 2007Applicant: THE BOEING COMPANYInventor: Thomas Zientek
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Publication number: 20060257261Abstract: Low-noise airfoils and methods of reducing noise. One embodiment provides an aerodynamic member that includes two body portions coupled to each other. The second body portion includes a plurality of airfoil members in a fixed relationship with each other. Optionally, the airfoil members may define an open end of the second body portion. In the alternative, the member can include a third body portion that has an airfoil shape and that is coupled to the second body portion opposite the first body portion. Preferably, the first portion, the airfoil members, and third portion are 12%, 8%, and 2% thickness/chord airfoils respectively. Further, the aerodynamic member may be a rotor blade on a tandem helicopter. Another embodiment provides a cambered airfoil with two coupled body portions one of which has air foil members. One of the body portions includes a slot there through with airfoil members on opposite sides of the slot.Type: ApplicationFiled: May 13, 2005Publication date: November 16, 2006Inventor: Thomas Zientek
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Publication number: 20060027703Abstract: The present invention discloses systems and methods for the performance enhancement of rotary wing aircraft through reduced torque, noise and vibration. In one embodiment, a system includes a sail having an aerodynamic shape positioned proximate to a tip of the rotor blade. An actuator may be configured to rotate the sail relative to the blade tip. a A control system receives information from a rotorcraft system and commands the actuator to rotate the sail to a predetermined favorable rotor blade operating condition. In another embodiment, a method includes configuring the rotorcraft in a selected flight condition, communicating input signals to a control system operable to position sails coupled to tips of blades of a rotor assembly, processing the input signals according to a constraint condition to generate sail positional information, and transferring the sail positional information to the sail.Type: ApplicationFiled: July 23, 2004Publication date: February 9, 2006Inventors: Richard Bussom, Michael McVeigh, Robert Narducci, Thomas Zientek