Patents by Inventor James N. Rozak
James N. Rozak 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: 10878645Abstract: A system and method for operating an aircraft. The system includes a health and usage monitoring system (HUMS) system for sensing health and usage data during flight of the aircraft, and a data transmission unit. The data transmission unit retrieves HUMS data from the HUMS system and generates a trigger signal when the retrieved HUMS data meets a selected criterion, the trigger signal being indicative of a condition of the aircraft. In response to the trigger signal, the data transmission unit transmits the retrieved HUMS data to a remote location.Type: GrantFiled: April 13, 2018Date of Patent: December 29, 2020Assignee: Sikorsky Aircraft CorporationInventors: Daniel A. Ciaburri, James N. Rozak
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Patent number: 10593134Abstract: A system for acceptance testing includes a data acquisition system operable to receive a plurality of sensor inputs from a component under test. The system also includes a health and usage monitoring system (HUMS) interface operable to receive data from a HUMS coupled to the sensor inputs. The system further includes a data processing system operable to determine a plurality of condition indicators based on the sensor inputs acquired by the data acquisition system, receive a plurality of HUMS data from the HUMS interface based on the sensor inputs, compare the condition indicators to the HUMS data, and output a test result based on results of the comparison.Type: GrantFiled: June 15, 2015Date of Patent: March 17, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: James N. Rozak, Michael C. Kingsley, Michael G. Mastrianni, Daniel Alfred Ciaburri
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Patent number: 10388087Abstract: A method of health management of a monitored system includes collecting component condition indicator data used to calculate a plurality of component health indicators. Component fault severity and potential failure modes are determined utilizing the component condition indicator data. The potential failure modes are ranked in order of likelihood to isolate the failure mode. A system of health management for monitored apparatus includes a fault severity module to derive a plurality of component health indicators from collected component condition indicator data, the plurality of component health indicators indicative of fault severity of a plurality of components. A fault isolation module separately derives a ranked listing of potential fault/failure modes utilizing the component condition indicator data.Type: GrantFiled: April 2, 2015Date of Patent: August 20, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Isaac Bandy, James P. Cycon, James N. Rozak, Mark W. Davis, Gregory J. Kacprzynski, Nicholos A. Mackos
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Publication number: 20180308297Abstract: A system and method for operating an aircraft. The system includes a health and usage monitoring system (HUMS) system for sensing health and usage data during flight of the aircraft, and a data transmission unit. The data transmission unit retrieves HUMS data from the HUMS system and generates a trigger signal when the retrieved HUMS data meets a selected criterion, the trigger signal being indicative of a condition of the aircraft. In response to the trigger signal, the data transmission unit transmits the retrieved HUMS data to a remote location.Type: ApplicationFiled: April 13, 2018Publication date: October 25, 2018Inventors: Daniel A. Ciaburri, James N. Rozak
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Publication number: 20170186249Abstract: A method of health management of a monitored system includes collecting component condition indicator data used to calculate a plurality of component health indicators. Component fault severity and potential failure modes are determined utilizing the component condition indicator data. The potential failure modes are ranked in order of likelihood to isolate the failure mode. A system of health management for monitored apparatus includes a fault severity module to derive a plurality of component health indicators from collected component condition indicator data, the plurality of component health indicators indicative of fault severity of a plurality of components. A fault isolation module separately derives a ranked listing of potential fault/failure modes utilizing the component condition indicator data.Type: ApplicationFiled: April 2, 2015Publication date: June 29, 2017Applicant: Sikorsky Aircraft CorporationInventors: Isaac Bandy, James P. Cycon, James N. Rozak, Mark W. Davis, Gregory J. Kacprzynski, Nicholos A. Mackos
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Publication number: 20170124785Abstract: A system for acceptance testing includes a data acquisition system operable to receive a plurality of sensor inputs from a component under test. The system also includes a health and usage monitoring system (HUMS) interface operable to receive data from a HUMS coupled to the sensor inputs. The system further includes a data processing system operable to determine a plurality of condition indicators based on the sensor inputs acquired by the data acquisition system, receive a plurality of HUMS data from the HUMS interface based on the sensor inputs, compare the condition indicators to the HUMS data, and output a test result based on results of the comparison.Type: ApplicationFiled: June 15, 2015Publication date: May 4, 2017Applicant: Sikorsky Aircraft CorporationInventors: James N. Rozak, Michael C. Kingsley, Michael G. Mastrianni, Daniel Alfred Ciaburri
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Patent number: 9026277Abstract: A method for reducing vibrations in an airframe of an aircraft includes determining, with a processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe; determining, with the processor, an initial adjustment solution for the aircraft in response to the determining of the information for the initial error value; receiving, with the processor, information indicative of a flight response to the initial adjustment solution; combining, with the processor, disturbance signals indicative of vibration noise with the information for the flight response; determining, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and determining, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value.Type: GrantFiled: September 12, 2013Date of Patent: May 5, 2015Assignee: Sikorsky Aircraft CorporationInventors: Austin Fang, Steven P. Lozano, James N. Rozak, Marlene T. Drost
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Publication number: 20150073627Abstract: A method for reducing vibrations in an airframe of an aircraft includes determining, with a processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe; determining, with the processor, an initial adjustment solution for the aircraft in response to the determining of the information for the initial error value; receiving, with the processor, information indicative of a flight response to the initial adjustment solution; combining, with the processor, disturbance signals indicative of vibration noise with the information for the flight response; determining, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and determining, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value.Type: ApplicationFiled: September 12, 2013Publication date: March 12, 2015Applicant: Sikorsky Aircraft CorporationInventors: Austin Fang, Steven P. Lozano, James N. Rozak, Marlene T. Drost
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Patent number: 7984146Abstract: A Health and Usage Monitoring System (HUMS) utilizes a common architecture which permits OEM and rotorcraft operators to view and trend HUMS data for an entire aircraft fleet independent of aircraft model, HUMS vendor, or raw data format. The system operates through a web portal that provides users with comparative information on HUMS parameters relative to fleet statistics. The user may view HUMS data for the entire fleet or drill down to a particular HUMS acquisition on a specific flight. The web based format also facilities display and communication of warnings in a timely manner.Type: GrantFiled: May 4, 2006Date of Patent: July 19, 2011Assignee: Sikorsky Aircraft CorporationInventors: James N. Rozak, James P. Cycon
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Patent number: 5156363Abstract: A helicopter collective control stick having a pilot grip positioned by a linkage assembly whose kinematics permits the control stick to occupy a small envelope and to have the pilot grip motion to be about a large radius. Our collective stick includes a biasing member to balance the control stick and linkage in the mid collective position and which provides a force gradient when the control stick is moved from the mid collective or trimmed position. Further, our collective stick is operable in concert with the full authority side arm controller to operate in either a tracking or a command mode.Type: GrantFiled: February 28, 1991Date of Patent: October 20, 1992Assignee: United Technologies CorporationInventors: Steven C. Cizewski, William F. Lange, James N. Rozak