Patents by Inventor Jeffrey C. Coffman
Jeffrey C. Coffman 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: 11118610Abstract: In general, certain embodiments of the present disclosure provide an electro-hydrostatic actuator comprising a piston assembly and a hydraulic cylinder. The piston assembly, having a piston head and a piston rod extending from the piston head, is located and movable within the hydraulic cylinder. The hydraulic cylinder includes a hydraulic fluid chamber region including a piston side chamber and a rod side chamber, a reservoir for storing hydraulic fluid located within the hydraulic cylinder which is in fluid communication with the hydraulic fluid chamber region. The electro-hydrostatic actuator includes a hydraulic pump system for moving hydraulic fluid in the reservoir and the hydraulic fluid chamber region, the hydraulic pump system in fluid communication with a flow control network in a hydraulic cylinder boss for controlling a direction and flow magnitude of hydraulic fluid within the hydraulic fluid chamber region, and an electric motor for driving the hydraulic pump system.Type: GrantFiled: August 29, 2017Date of Patent: September 14, 2021Assignee: The Boeing CompanyInventors: David E. Blanding, Jeffrey C. Coffman
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Patent number: 11092175Abstract: A dual-independent hybrid actuator system includes an actuator body defining a hydraulic chamber. The actuator system includes a hydraulic piston assembly, including a hydraulic piston disposed within the hydraulic chamber and dividing the hydraulic chamber into a first hydraulic sub-chamber in fluid communication with a first hydraulic fluid passage and a second hydraulic sub-chamber in fluid communication with a second hydraulic fluid passage. The actuator system further includes a piston rod mounted to the hydraulic piston that passes through the second hydraulic sub-chamber with a distal end that projects outward from the actuator body. The actuator system further includes an electric motor mounted to the actuator body, and a threaded axle mechanically coupled to a motor shaft of the electric motor. The threaded axle passes through the first hydraulic sub-chamber and engages with a threaded port formed in the hydraulic piston assembly.Type: GrantFiled: March 23, 2020Date of Patent: August 17, 2021Assignee: THE BOEING COMPANYInventors: David E. Blanding, Jeffrey C. Coffman, Jimmy M. Quiambao
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Publication number: 20190063472Abstract: In general, certain embodiments of the present disclosure provide an electro-hydrostatic actuator comprising a piston assembly and a hydraulic cylinder. The piston assembly, having a piston head and a piston rod extending from the piston head, is located and movable within the hydraulic cylinder. The hydraulic cylinder includes a hydraulic fluid chamber region including a piston side chamber and a rod side chamber, a reservoir for storing hydraulic fluid located within the hydraulic cylinder which is in fluid communication with the hydraulic fluid chamber region. The electro-hydrostatic actuator includes a hydraulic pump system for moving hydraulic fluid in the reservoir and the hydraulic fluid chamber region, the hydraulic pump system in fluid communication with a flow control network in a hydraulic cylinder boss for controlling a direction and flow magnitude of hydraulic fluid within the hydraulic fluid chamber region, and an electric motor for driving the hydraulic pump system.Type: ApplicationFiled: August 29, 2017Publication date: February 28, 2019Applicant: The Boeing CompanyInventors: David E. Blanding, Jeffrey C. Coffman
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Patent number: 10152050Abstract: A control system may include a fault detection system, an electromechanical actuator, the electromechanical actuator electronically coupled to the fault detection system, and a failure simulation apparatus mechanically coupled between the electromechanical actuator and a load, the failure simulation apparatus selectively applies an external resistive force to the electromechanical actuator.Type: GrantFiled: March 4, 2016Date of Patent: December 11, 2018Assignee: The Boeing CompanyInventors: Jim L. Peck, Jeffrey C. Coffman
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Patent number: 10029808Abstract: Disclosed embodiments include a structurally integrated thermal management system that uses the structure of an aerospace vehicle as part of the heat dissipation system. In this system, structural elements of the aerospace vehicle function as a thermal bus, and are thermally connected with heat-generating electrical components, so that heat from those components is directed away from the component by the structure of the vehicle itself, into lower temperature surfaces of the vehicle.Type: GrantFiled: February 29, 2016Date of Patent: July 24, 2018Assignee: THE BOEING COMPANYInventors: David E. Blanding, Arun Muley, Jeffrey C. Coffman, Doug Van Affelen
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Publication number: 20170255190Abstract: A control system may include a fault detection system, an electromechanical actuator, the electromechanical actuator electronically coupled to the fault detection system, and a failure simulation apparatus mechanically coupled between the electromechanical actuator and a load, the failure simulation apparatus selectively applies an external resistive force to the electromechanical actuator.Type: ApplicationFiled: March 4, 2016Publication date: September 7, 2017Inventors: Jim L. Peck, Jeffrey C. Coffman
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Publication number: 20170247126Abstract: Disclosed embodiments include a structurally integrated thermal management system that uses the structure of an aerospace vehicle as part of the heat dissipation system. In this system, structural elements of the aerospace vehicle function as a thermal bus, and are thermally connected with heat-generating electrical components, so that heat from those components is directed away from the component by the structure of the vehicle itself, into lower temperature surfaces of the vehicle.Type: ApplicationFiled: February 29, 2016Publication date: August 31, 2017Inventors: David E. Blanding, Arun Muley, Jeffrey C. Coffman, Doug Van Affelen
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Patent number: 9604717Abstract: Systems and methods for operating flight control surfaces are provided. One system includes a control device having a two piece shaft including a first shaft portion and a second shaft portion, a spline key detachably coupling the first shaft portion and the second shaft portion, and a crankshaft operatively coupling the two piece shaft and a flight control surface. The control device further includes a driving mechanism coupled to the spline key and operable to move the spline key to engage and disengage the first and second shaft portions, wherein the first and second shaft portions are disengaged when a failure to the flight control surface is detected, causing the second shaft portion to drive the flight control surface to a safe position.Type: GrantFiled: June 16, 2014Date of Patent: March 28, 2017Assignee: The Boeing CompanyInventor: Jeffrey C. Coffman
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Patent number: 9586676Abstract: Provided are mechanisms and processes for a pneumatic shaft positioning system. According to various examples, the pneumatic shaft positioning system includes a pyrotechnic valve that is configured to control the flow of gas from a pressurized gas source into a pressure chamber. The pressure chamber includes a first piston that is slidably coupled to the pressure chamber. When gas from the pressurized gas source fills the pressure chamber, the piston is configured to slide through the pressure chamber and force a shaft into a predetermined position.Type: GrantFiled: April 1, 2014Date of Patent: March 7, 2017Assignee: The Boeing CompanyInventors: Jeffrey C. Coffman, David E. Blanding
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Publication number: 20160244152Abstract: Systems and methods for operating flight control surfaces are provided. One system includes a control device having a two piece shaft including a first shaft portion and a second shaft portion, a spline key detachably coupling the first shaft portion and the second shaft portion, and a crankshaft operatively coupling the two piece shaft and a flight control surface. The control device further includes a driving mechanism coupled to the spline key and operable to move the spline key to engage and disengage the first and second shaft portions, wherein the first and second shaft portions are disengaged when a failure to the flight control surface is detected, causing the second shaft portion to drive the flight control surface to a safe position.Type: ApplicationFiled: June 16, 2014Publication date: August 25, 2016Inventor: Jeffrey C. Coffman
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Publication number: 20150274281Abstract: Provided are mechanisms and processes for a pneumatic shaft positioning system. According to various examples, the pneumatic shaft positioning system includes a pyrotechnic valve that is configured to control the flow of gas from a pressurized gas source into a pressure chamber. The pressure chamber includes a first piston that is slidably coupled to the pressure chamber. When gas from the pressurized gas source fills the pressure chamber, the piston is configured to slide through the pressure chamber and force a shaft into a predetermined position.Type: ApplicationFiled: April 1, 2014Publication date: October 1, 2015Applicant: The Boeing CompanyInventors: Jeffrey C. Coffman, David E. Blanding