Patents by Inventor Carlos J. Stevens
Carlos J. Stevens 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: 10479531Abstract: A shell rotor assembly for use in a control moment gyroscope herein. The shell rotor assembly includes, but is not limited to, a first shell member having a first wall portion and a first rim portion formed integrally with one another and a second shell member having a second wall portion and a second rim portion formed integrally with one another. The first rim portion and the second rim portion are attached to one another.Type: GrantFiled: August 24, 2010Date of Patent: November 19, 2019Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Carlos J. Stevens, Mark Heller, Stephen Edward Fiske
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Patent number: 9354079Abstract: Embodiments of control moment gyroscopes (CMGs) are provided, as are embodiments of a method for fabricating CMGs. In one embodiment, a CMG includes a stator housing, an inner gimbal assembly (IGA), and a torque motor coupled to the stator housing and configured to rotate the IGA about a gimbal axis to selectively generate a desired output torque during operation of the CMG. The IGA includes, in turn, an IGA support structure rotatably coupled to the stator housing, a monolithic CMG rotor rotatably mounted to the IGA support structure, and a spin motor coupled to the IGA support structure and configured to rotate the monolithic CMG rotor about a spin axis.Type: GrantFiled: May 21, 2012Date of Patent: May 31, 2016Assignee: Honeywell International Inc.Inventors: Porter Davis, Theodis Johnson, Carlos J. Stevens
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Patent number: 8919213Abstract: A control moment gyroscope (CMG) includes a stator housing, an inner gimbal assembly (IGA), and a torque motor coupled to the stator housing and configured to rotate the IGA housing about a gimbal axis to selectively generate a desired output torque during operation of the CMG. The IGA includes, in turn, an IGA housing rotatably coupled to the stator housing, a CMG rotor rotatably mounted within the IGA housing, and a spin motor coupled to the IGA housing and configured to rotate the CMG rotor about a spin axis. The CMG rotor includes a rotor shaft, a rotor rim circumscribing the rotor shaft, and a plurality of radially-compliant spokes extending between the rotor shaft and the rotor rim.Type: GrantFiled: May 21, 2012Date of Patent: December 30, 2014Assignee: Honeywell International Inc.Inventors: Porter Davis, Carlos J. Stevens
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Publication number: 20140026688Abstract: Embodiments of control moment gyroscopes (CMGs) are provided, as are embodiments of a method for fabricating CMGs. In one embodiment, a CMG includes a stator housing, an inner gimbal assembly (IGA), and a torque motor coupled to the stator housing and configured to rotate the IGA housing about a gimbal axis to selectively generate a desired output torque during operation of the CMG. The IGA includes, in turn, an IGA support structure housing rotatably coupled to the stator housing, a monolithic CMG rotor rotatably mounted to the IGA support structure housing, and a spin motor coupled to the IGA support structure housing and configured to rotate the monolithic CMG rotor about a spin axis.Type: ApplicationFiled: May 21, 2012Publication date: January 30, 2014Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Porter Davis, Theodis Johnson, Carlos J. Stevens
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Publication number: 20130305850Abstract: Embodiments of control moment gyroscopes (CMGs) are provided, as are embodiments of a method for fabricating CMGs. In one embodiment, a CMG includes a stator housing, an inner gimbal assembly (IGA), and a torque motor coupled to the stator housing and configured to rotate the IGA housing about a gimbal axis to selectively generate a desired output torque during operation of the CMG. The IGA includes, in turn, an IGA housing rotatably coupled to the stator housing, a CMG rotor rotatably mounted within the IGA housing, and a spin motor coupled to the IGA housing and configured to rotate the CMG rotor about a spin axis. The CMG rotor includes a rotor shaft, a rotor rim circumscribing the rotor shaft, and a plurality of radially-compliant spokes extending between the rotor shaft and the rotor rim.Type: ApplicationFiled: May 21, 2012Publication date: November 21, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Porter Davis, Carlos J. Stevens
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Patent number: 8205514Abstract: A control moment gyroscope (CMG) is provided for deployment on a spacecraft. The CMG includes a stator housing, an inner gimbal assembly disposed in the stator housing, and a torque motor coupled to the stator housing and at least partially disposed around an intermediate portion of the inner gimbal assembly. The torque motor is configured to rotate the inner gimbal assembly about a gimbal axis.Type: GrantFiled: January 18, 2008Date of Patent: June 26, 2012Assignee: Honeywell International Inc.Inventors: Carlos J. Stevens, Stephen E. Fiske
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Patent number: 8171805Abstract: Methods and apparatus are provided for determining torque in an environmentally isolated system. A drive system is coupled to the environmentally isolated system via a non-contact, magnetic coupling that has a known angular stiffness and at least two coupling sections. A relative deflection of each coupling section is optically measured, and the torque is determined based on the relative deflection and the known angular stiffness.Type: GrantFiled: February 18, 2010Date of Patent: May 8, 2012Assignee: Honeywell International Inc.Inventor: Carlos J. Stevens
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Publication number: 20120048040Abstract: A shell rotor assembly for use in a control moment gyroscope is disclosed herein. The shell rotor assembly includes, but is not limited to, a first shell member having a first wall portion and a first rim portion formed integrally with one another and a second shell member having a second wall portion and a second rim portion formed integrally with one another. The first rim portion and the second rim portion are attached to one another.Type: ApplicationFiled: August 24, 2010Publication date: March 1, 2012Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Carlos J. Stevens, Mark Heller, Stephen Edward Fiske
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Publication number: 20110197683Abstract: Methods and apparatus are provided for determining torque in an environmentally isolated system. A drive system is coupled to the environmentally isolated system via a non-contact, magnetic coupling that has a known angular stiffness and at least two coupling sections. A relative deflection of each coupling section is optically measured, and the torque is determined based on the relative deflection and the known angular stiffness.Type: ApplicationFiled: February 18, 2010Publication date: August 18, 2011Applicant: HONEYWELL INTERNATIONAL INC.Inventor: Carlos J. Stevens
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Patent number: 7997157Abstract: A control moment gyroscope (CMG) is provided for deployment on a spacecraft. The CMG includes an inner gimbal assembly (IGA), which, in turn, includes an IGA housing, a rotor rotatably coupled to the IGA housing, and a spin motor coupled to the IGA housing and configured to rotate the rotor about a spin axis. The CMG further comprises a stator assembly, which includes: (i) a stator assembly housing rotatably coupled to the IGA housing, and (ii) a torque module assembly coupled to the stator assembly housing and configured to rotate the IGA about a gimbal axis. A gimbal bearing is disposed between the IGA housing and the stator assembly housing. The gimbal bearing resides between the spin axis and the torque module assembly such that the distance between the gimbal bearing and the spin axis is less than the distance between the gimbal bearing and the torque module assembly.Type: GrantFiled: February 11, 2008Date of Patent: August 16, 2011Assignee: Honeywell International Inc.Inventors: Dennis Wayne Smith, Paul Buchele, Carlos J. Stevens, Stephen Edward Fiske
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Publication number: 20100000349Abstract: A control moment gyroscope (CMG) is provided for deployment on a spacecraft. The CMG includes a stator housing, an inner gimbal assembly disposed in the stator housing, and a torque motor coupled to the stator housing and at least partially disposed around an intermediate portion of the inner gimbal assembly. The torque motor is configured to rotate the inner gimbal assembly about a gimbal axis.Type: ApplicationFiled: January 18, 2008Publication date: January 7, 2010Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Carlos J. Stevens, Stephen E. Fiske
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Publication number: 20090200428Abstract: A control moment gyroscope (CMG) is provided for deployment on a spacecraft. The CMG includes an inner gimbal assembly (IGA), which, in turn, includes an IGA housing, a rotor rotatably coupled to the IGA housing, and a spin motor coupled to the IGA housing and configured to rotate the rotor about a spin axis. The CMG further comprises a stator assembly, which includes: (i) a stator assembly housing rotatably coupled to the IGA housing, and (ii) a torque module assembly coupled to the stator assembly housing and configured to rotate the IGA about a gimbal axis. A gimbal bearing is disposed between the IGA housing and the stator assembly housing. The gimbal bearing resides between the spin axis and the torque module assembly such that the distance between the gimbal bearing and the spin axis is less than the distance between the gimbal bearing and the torque module assembly.Type: ApplicationFiled: February 11, 2008Publication date: August 13, 2009Applicant: Honeywell International Inc.Inventors: Dennis Wayne Smith, Paul Buchele, Carlos J. Stevens, Stephen Edward Fiske
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Patent number: 7299817Abstract: A valve is provided for use on a control moment gyroscope (CMG) having a housing separating an internal environment from an external environment. The valve includes a valve housing, a valve element, and bellows. The valve housing is configured to couple to the CMG housing and includes an inner surface defining a cavity, an outer surface, and an opening extending therebetween. The valve element is disposed within the valve housing cavity and is movable between a closed position, in which fluid is prevented from flowing through the valve housing opening, and an open position, in which fluid may flow through the valve housing opening. The bellows is disposed within the valve housing and coupled to the valve element and has an internal chamber. The bellows selectively moves the valve element closed and open in response to a differential pressure between the bellows internal chamber and the valve housing cavity.Type: GrantFiled: September 1, 2004Date of Patent: November 27, 2007Assignee: Honeywell International, Inc.Inventors: Gary L. Gisler, James T. Hanks, Carlos J. Stevens, Robert E. Winkel
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Publication number: 20040089089Abstract: In a gear train having a first gear, a second gear in mesh with the first gear, and a third gear in mesh with the second gear, an anti-backlash mechanism having a first anti-backlash gear positioned in operative relationship with the first gear and the second gear, a second anti-backlash gear positioned in operative relationship with the second gear and the third gear, whereby the first anti-backlash gear controls backlash between the first gear and the second gear, and the second anti-backlash gear controls backlash between the second gear and the third gear.Type: ApplicationFiled: November 8, 2002Publication date: May 13, 2004Inventors: Carlos J. Stevens, Robert E. Winkel