Patents by Inventor Gary E. Lemke
Gary E. Lemke 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: 20230116317Abstract: Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to, based on the satellite exiting the launch vehicle, enable release of magnets or locks of an array, a release controller to control the release of the magnets or the locks of the array based on a release sequence to autonomously deploy the solar array, and a sequence analyzer to adapt the release sequence during execution of the release sequence, wherein adapting the release sequence includes changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.Type: ApplicationFiled: December 13, 2022Publication date: April 13, 2023Inventors: Gary E. Lemke, Chris J. Wasson, John P. Mills, Cecilia G. Cantu
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Patent number: 11535406Abstract: Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to enable ignition of squibs of a squib array based on the satellite exiting the launch vehicle, and a squib controller to control the ignition of the squibs based on a firing sequence of the squibs, where the squib controller is to vary the firing sequence to autonomously deploy the solar array.Type: GrantFiled: December 18, 2018Date of Patent: December 27, 2022Assignee: The Boeing CompanyInventors: Gary E. Lemke, Chris J. Wasson, John P. Mills, Cecilia G. Cantu
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Patent number: 11505338Abstract: Systems and methods for launching a plurality of spacecraft, provided in a stack of spacecraft, from a launch vehicle traveling along an in-track path include releasing, in a first separation event occurring at a first time, a first spacecraft from the stack of spacecraft using a first separation force having a first separation force in-track component along the in-track path. Subsequently, in a second separation event occurring at a second time, a second spacecraft is released from the stack of spacecraft using a second separation force having a second separation force in-track component along the in-track path, wherein the second time occurs a first time delay after the first time. The first and second separation in-track components may be different, such as by varying a magnitude of the separation force or an angle at which the spacecraft is launched.Type: GrantFiled: February 22, 2019Date of Patent: November 22, 2022Assignee: The Boeing CompanyInventors: Sadek W. Mansour, Gary E. Lemke, Jason D. Flathom, Jeffrey S. Noel
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Patent number: 11338944Abstract: A control system configured to execute a safing mode sequence for a spacecraft is disclosed. The control system includes one or more star trackers that each include a field of view to capture light from a plurality of space objects surrounding the celestial body. The control system also includes one or more actuators, one or more processors in electronic communication with the one or more actuators, and a memory coupled to the one or more processors. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to determine a current attitude of the spacecraft, and re-orient the spacecraft from a current attitude into a momentum neutral attitude.Type: GrantFiled: May 29, 2019Date of Patent: May 24, 2022Assignee: GM Global Technology Operations LLCInventors: Cecilia G. Cantu, Gary E. Lemke, John Preston Charles Mills, Christopher James Wasson
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Patent number: 11273933Abstract: A control system for reducing disturbance torque of a spacecraft is disclosed. The spacecraft revolves around a celestial body surrounded by an atmosphere. The control system includes processors in electronic communication with one or more actuators and a memory. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to instruct the spacecraft to enter a safing mode. In response to entering the safing mode, the control system instructs the one or more actuators to align a principal axis of the spacecraft with a vector that is normal to the orbit around the celestial body. The control system also instructs the actuators to rotate the spacecraft about the principal axis, where a rotational orientation of the spacecraft relative to the celestial body is shifted by about one-half a rotation about the principal axis.Type: GrantFiled: May 29, 2019Date of Patent: March 15, 2022Assignee: The Boeing CompanyInventors: Christopher James Wasson, Gary E. Lemke, John Preston Charles Mills, Cecilia G. Cantu, Timothy S. Lui
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Patent number: 11174047Abstract: A control system for a spacecraft for determining a resultant torque that is exerted upon a spacecraft by one or more magnetic torque rods is disclosed. The spacecraft is configured to revolve around a celestial body in an orbit. A magnetic field of the celestial body is predictable, and a direction of the magnetic field located around the orbit is fixed. The control system includes the one or more magnetic torque rods, one or more processors in electronic communication with the one or more magnetic torque rods, and a memory coupled to the one or more processors. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to instruct the one or more magnetic torque rods to exert the resultant torque upon the spacecraft.Type: GrantFiled: May 29, 2019Date of Patent: November 16, 2021Assignee: The Boeing CompanyInventors: Gary E. Lemke, John Preston Charles Mills, Christopher James Wasson, Cecilia G. Cantu
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Publication number: 20200377236Abstract: A control system for a spacecraft for determining a resultant torque that is exerted upon a spacecraft by one or more magnetic torque rods is disclosed. The spacecraft is configured to revolve around a celestial body in an orbit. A magnetic field of the celestial body is predictable, and a direction of the magnetic field located around the orbit is fixed. The control system includes the one or more magnetic torque rods, one or more processors in electronic communication with the one or more magnetic torque rods, and a memory coupled to the one or more processors. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to instruct the one or more magnetic torque rods to exert the resultant torque upon the spacecraft.Type: ApplicationFiled: May 29, 2019Publication date: December 3, 2020Applicant: The Boeing CompanyInventors: Gary E. Lemke, John Preston Charles Mills, Christopher James Wasson, Cecilia G. Cantu
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Publication number: 20200377240Abstract: A control system configured to execute a safing mode sequence for a spacecraft is disclosed. The control system includes one or more star trackers that each include a field of view to capture light from a plurality of space objects surrounding the celestial body. The control system also includes one or more actuators, one or more processors in electronic communication with the one or more actuators, and a memory coupled to the one or more processors. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to determine a current attitude of the spacecraft, and re-orient the spacecraft from a current attitude into a momentum neutral attitude.Type: ApplicationFiled: May 29, 2019Publication date: December 3, 2020Inventors: Cecilia G. Cantu, Gary E. Lemke, John Preston Charles Mills, Christopher James Wasson
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Publication number: 20200377235Abstract: A control system for reducing disturbance torque of a spacecraft is disclosed. The spacecraft revolves around a celestial body surrounded by an atmosphere. The control system includes processors in electronic communication with one or more actuators and a memory. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to instruct the spacecraft to enter a safing mode. In response to entering the safing mode, the control system instructs the one or more actuators to align a principal axis of the spacecraft with a vector that is normal to the orbit around the celestial body. The control system also instructs the actuators to rotate the spacecraft about the principal axis, where a rotational orientation of the spacecraft relative to the celestial body is shifted by about one-half a rotation about the principal axis.Type: ApplicationFiled: May 29, 2019Publication date: December 3, 2020Inventors: Christopher James Wasson, Gary E. Lemke, John Preston Charles Mills, Cecilia G. Cantu, Timothy S. Lui
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Publication number: 20200270001Abstract: Systems and methods for launching a plurality of spacecraft, provided in a stack of spacecraft, from a launch vehicle traveling along an in-track path include releasing, in a first separation event occurring at a first time, a first spacecraft from the stack of spacecraft using a first separation force having a first separation force in-track component along the in-track path. Subsequently, in a second separation event occurring at a second time, a second spacecraft is released from the stack of spacecraft using a second separation force having a second separation force in-track component along the in-track path, wherein the second time occurs a first time delay after the first time. The first and second separation in-track components may be different, such as by varying a magnitude of the separation force or an angle at which the spacecraft is launched.Type: ApplicationFiled: February 22, 2019Publication date: August 27, 2020Applicant: The Boeing CompanyInventors: Sadek W. Mansour, Gary E. Lemke, Jason D. Flathom, Jeffrey S. Noel
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Patent number: 10717551Abstract: A spacecraft system includes a plurality of spacecraft in a stack. The stack has one or more layers, each layer includes at least two spacecraft, and each spacecraft is releasably coupled to one or more adjacent spacecraft in the stack. The spacecraft system also includes a controller configured to, for each layer, (i) cause the layer to release from the stack, and (ii) after the layer releases from the stack, cause the at least two spacecraft in the layer to release from each other.Type: GrantFiled: June 3, 2019Date of Patent: July 21, 2020Assignee: The Boeing CompanyInventors: Miguel A. Estevez, Jason D. Flathom, Gary E. Lemke, Dennis Yoichi Nakasone, Christopher P. Volk, Elvis D. Silva
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Publication number: 20200189770Abstract: Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to enable ignition of squibs of a squib array based on the satellite exiting the launch vehicle, and a squib controller to control the ignition of the squibs based on a firing sequence of the squibs, where the squib controller is to vary the firing sequence to autonomously deploy the solar array.Type: ApplicationFiled: December 18, 2018Publication date: June 18, 2020Inventors: Gary E. Lemke, Chris J. Wasson, John P. Mills, Cecilia G. Cantu
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Publication number: 20200024010Abstract: In an example, a spacecraft system includes a plurality of spacecraft in a stack. The stack has one or more layers, each layer includes at least two spacecraft, and each spacecraft is releasably coupled to one or more adjacent spacecraft in the stack. The spacecraft system also includes a controller configured to, for each layer, (i) cause the layer to release from the stack, and (ii) after the layer releases from the stack, cause the at least two spacecraft in the layer to release from each other.Type: ApplicationFiled: June 3, 2019Publication date: January 23, 2020Inventors: Miguel A. Estevez, Jason D. Flathom, Gary E. Lemke, Dennis Yoichi Nakasone, Christopher P. Volk, Elvis D. Silva
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Patent number: 10351268Abstract: A spacecraft system includes a plurality of spacecraft in a stack. The stack has one or more layers, each layer includes at least two spacecraft, and each spacecraft is releasably coupled to one or more adjacent spacecraft in the stack. The spacecraft system also includes a controller configured to, for each layer, (i) cause the layer to release from the stack, and (ii) after the layer releases from the stack, cause the at least two spacecraft in the layer to release from each other.Type: GrantFiled: December 8, 2016Date of Patent: July 16, 2019Assignee: The Boeing CompanyInventors: Miguel A. Estevez, Jason D. Flathom, Gary E. Lemke, Dennis Yoichi Nakasone, Christopher P. Volk, Elvis D. Silva
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Patent number: 10175700Abstract: Methods, apparatus, and articles of manufacture to minimize command dynamics of a satellite are disclosed. An example apparatus includes a steering law module to calculate a first set of vectors to maneuver a space vehicle, and calculate a second set of vectors based on projecting the first set of vectors onto a fixed plane. The apparatus further includes an attitude controller to generate an attitude command based on the first and the second sets of vectors to prevent an unplanned rotation by the space vehicle.Type: GrantFiled: March 22, 2017Date of Patent: January 8, 2019Assignee: THE BOEING COMPANYInventors: Timothy S. Lui, Gary E. Lemke
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Publication number: 20180275683Abstract: Methods, apparatus, and articles of manufacture to minimize command dynamics of a satellite are disclosed. An example apparatus includes a steering law module to calculate a first set of vectors to maneuver a space vehicle, and calculate a second set of vectors based on projecting the first set of vectors onto a fixed plane. The apparatus further includes an attitude controller to generate an attitude command based on the first and the second sets of vectors to prevent an unplanned rotation by the space vehicle.Type: ApplicationFiled: March 22, 2017Publication date: September 27, 2018Inventors: Timothy S. Lui, Gary E. Lemke
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Publication number: 20180162561Abstract: In an example, a spacecraft system includes a plurality of spacecraft in a stack. The stack has one or more layers, each layer includes at least two spacecraft, and each spacecraft is releasably coupled to one or more adjacent spacecraft in the stack. The spacecraft system also includes a controller configured to, for each layer, (i) cause the layer to release from the stack, and (ii) after the layer releases from the stack, cause the at least two spacecraft in the layer to release from each other.Type: ApplicationFiled: December 8, 2016Publication date: June 14, 2018Inventors: Miguel A. Estevez, Jason D. Flathom, Gary E. Lemke, Dennis Yoichi Nakasone, Christopher P. Volk, Elvis D. Silva