Patents by Inventor Troy Prince
Troy Prince 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: 10137979Abstract: A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal associated therewith, the at least one sensor being used for determining or estimating flow separation or side forces on the missile forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.Type: GrantFiled: June 2, 2011Date of Patent: November 27, 2018Assignee: Orbital Research Inc.Inventors: Troy Prince, Frederick J. Lisy, Mehul P. Patel, Jack M. DiCocco, Reed Carver, Robert N. Schmidt
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Patent number: 9637223Abstract: An afterbody flow control system is used for aircraft or missile flow control to provide enhanced maneuverability and stabilization. A method of operating the flow control system is also described. The missile or aircraft comprises an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.Type: GrantFiled: April 27, 2012Date of Patent: May 2, 2017Assignee: Orbital Reseach Inc.Inventors: Jack DiCocco, Troy Prince, Mehul Patel, Tsun Ming Terry Ng
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Patent number: 9624836Abstract: The present invention relates to a method of determining both pressures and temperatures in a high temperature environment. The present invention also relates to a method of determining temperatures about a pressure-sensing element using a bi-functional heater. In addition, the present invention preferably relates to a pressure sensor with the pressure-sensing element and a heating element both integrated into the sensor's packaging, preferably onto the diaphragm of the pressure sensor, and particularly to such a pressure sensor capable of operating at high or elevated temperatures, and even more particularly to such a pressure sensor wherein the heating element is capable of both heating, at least in part, the pressure-sensing element and monitoring the temperature of the application area. Preferably, the pressure-sensing element is formed from shape memory alloy (SMA) materials that can be used at high or elevated temperatures as a pressure sensor with high sensitivity.Type: GrantFiled: October 2, 2015Date of Patent: April 18, 2017Assignee: Orbital Research IncInventors: Greg S Shaw, Troy Prince, Joseph Snyder, Michael C Willett, Frederick J Lisy
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Patent number: 9157392Abstract: The present invention relates to a method of determining both pressures and temperatures in a high temperature environment. The present invention also relates to a method of determining temperatures about a pressure-sensing element using a bi-functional heater. In addition, the present invention preferably relates to a pressure sensor with the pressure-sensing element and a heating element both integrated into the sensor's packaging, preferably onto the diaphragm of the pressure sensor, and particularly to such a pressure sensor capable of operating at high or elevated temperatures, and even more particularly to such a pressure sensor wherein the heating element is capable of both heating, at least in part, the pressure-sensing element and monitoring the temperature of the application area. Preferably, the pressure-sensing element is formed from shape memory alloy (SMA) materials that can be used at high or elevated temperatures as a pressure sensor with high sensitivity.Type: GrantFiled: August 26, 2013Date of Patent: October 13, 2015Assignee: Orbital Research Inc.Inventors: Greg S Shaw, Troy Prince, Joseph Snyder, Michael C Willett, Frederick J Lisy
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Publication number: 20150060593Abstract: The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization, and to a method of operating the flow control system. Various embodiments of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft. The active flow control device or activatable flow effectors create on-demand flow disturbances, preferably micro-disturbances, at different points along the various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect.Type: ApplicationFiled: August 27, 2013Publication date: March 5, 2015Inventors: Troy Prince, Richard Kolacinski, Mehul Patel
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Patent number: 8596131Abstract: The present invention relates, in general, to pressure sensors capable of operating at high temperatures. The present invention further relates to a high temperature pressure sensor with an improved gage factor. The present invention still further provides a pressure sensor with a smaller sized diaphragm, which is capable of reading higher pressures. The present invention also provides a method and sensor for detecting strain using shape memory alloys.Type: GrantFiled: January 31, 2012Date of Patent: December 3, 2013Assignee: Orbital Research Inc.Inventors: Reed Carver, Joseph Snyder, Frederick J Lisy, Troy Prince
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Patent number: 8544335Abstract: The present invention relates to a method of determining both pressures and temperatures in a high temperature environment. The present invention also relates to a method of determining temperatures about a pressure-sensing element using a bi-functional heater. In addition, the present invention preferably relates to a pressure sensor with the pressure-sensing element and a heating element both integrated into the sensor's packaging, preferably onto the diaphragm of the pressure sensor, and particularly to such a pressure sensor capable of operating at high or elevated temperatures, and even more particularly to such a pressure sensor wherein the heating element is capable of both heating, at least in part, the pressure-sensing element and monitoring the temperature of the application area. Preferably, the pressure-sensing element is formed from shape memory alloy (SMA) materials that can be used at high or elevated temperatures as a pressure sensor with high sensitivity.Type: GrantFiled: July 26, 2011Date of Patent: October 1, 2013Assignee: Orbital Research Inc.Inventors: Greg S. Shaw, Troy Prince, Joseph Snyder, Michael C. Willet, Frederick J. Lisy
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Patent number: 8417395Abstract: The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors of these various embodiments are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft.Type: GrantFiled: December 1, 2003Date of Patent: April 9, 2013Assignee: Orbitol Research Inc.Inventors: Troy Prince, Richard Kolacinski, Mehul Patel
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Patent number: 8191833Abstract: The present invention relates to an afterbody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor each having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.Type: GrantFiled: May 2, 2006Date of Patent: June 5, 2012Assignee: Orbital Research Inc.Inventors: Jack DiCocco, Troy Prince, Mehul Patel, Tsun Ming Terry Ng
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Patent number: 8127616Abstract: The present invention relates, in general, to pressure sensors capable of operating at high temperatures. The present invention further relates to a high temperature pressure sensor with an improved gage factor. The present invention still further provides a pressure sensor with a smaller sized diaphragm, which is capable of reading higher pressures. The present invention also provides a method and sensor for detecting strain using shape memory alloys.Type: GrantFiled: April 2, 2008Date of Patent: March 6, 2012Inventors: Reed Carver, Joseph Snyder, Frederick J. Lisy, Troy Prince
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Patent number: 8006564Abstract: The present invention relates to a method of determining both pressures and temperatures in a high temperature environment. The present invention also relates to a method of determining temperatures about a pressure-sensing element using a bi-functional heater. In addition, the present invention preferably relates to a pressure sensor with the pressure-sensing element and a heating element both integrated into the sensor's packaging, preferably onto the diaphragm of the pressure sensor, and particularly to such a pressure sensor capable of operating at high or elevated temperatures, and even more particularly to such a pressure sensor wherein the heating element is capable of both heating, at least in part, the pressure-sensing element and monitoring the temperature of the application area. Preferably, the pressure-sensing element is formed from shape memory alloy (SMA) materials that can be used at high or elevated temperatures as a pressure sensor with high sensitivity.Type: GrantFiled: August 11, 2009Date of Patent: August 30, 2011Assignee: Orbital Research Inc.Inventors: Greg S. Shaw, Troy Prince, Joseph Snyder, Michael C. Willett, Frederick J. Lisy
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Patent number: 7977615Abstract: A forebody flow control system and more particularly to aircraft or missile flow control systems for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one flow effector on the missile or aircraft forebody; at least one sensor having a signal associated therewith, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one flow effector based on at least in part the signal of the at least one sensor.Type: GrantFiled: May 7, 2007Date of Patent: July 12, 2011Assignee: Orbital Research Inc.Inventors: Troy Prince, Frederick J. Lisy, Mehul P. Patel, Jack M. DiCocco, Reed Carver, Robert N. Schmidt
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Patent number: 7587944Abstract: The present invention relates to a method of determining both pressures and temperatures in a high temperature environment. The present invention also relates to a method of determining temperatures about a pressure-sensing element using a bi-functional heater. In addition, the present invention preferably relates to a pressure sensor with the pressure-sensing element and a heating element both integrated into the sensor's packaging, preferably onto the diaphragm of the pressure sensor, and particularly to such a pressure sensor capable of operating at high or elevated temperatures, and even more particularly to such a pressure sensor wherein the heating element is capable of both heating, at least in part, the pressure-sensing element and monitoring the temperature of the application area. Preferably, the pressure-sensing element is formed from shape memory alloy (SMA) materials that can be used at high or elevated temperatures as a pressure sensor with high sensitivity.Type: GrantFiled: July 21, 2008Date of Patent: September 15, 2009Assignee: Orbital Research Inc.Inventors: Greg Shaw, Troy Prince, Joseph Snyder, Mike Willett, Frederick Lisy
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Patent number: 7415884Abstract: The present invention relates to a method of determining both pressures and temperatures in a high temperature environment. The present invention also relates to a method of determining temperatures about a pressure-sensing element using a bi-functional heater. In addition, the present invention preferably relates to a pressure sensor with the pressure-sensing element and a heating element both integrated into the sensor's packaging, preferably onto the diaphragm of the pressure sensor, and particularly to such a pressure sensor capable of operating at high or elevated temperatures, and even more particularly to such a pressure sensor wherein the heating element is capable of both heating, at least in part, the pressure-sensing element and monitoring the temperature of the application area. Preferably, the pressure-sensing element is formed from shape memory alloy (SMA) materials that can be used at high or elevated temperatures as a pressure sensor with high sensitivity.Type: GrantFiled: June 19, 2007Date of Patent: August 26, 2008Assignee: Orbital Research Inc.Inventors: Greg Shaw, Troy Prince, Joseph Snyder, Mike Willett, Frederick Lisy
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Patent number: 7387028Abstract: The present invention relates, in general, to pressure sensors capable of operating at high temperatures. The present invention further relates to a high temperature pressure sensor with an improved gage factor. The present invention still further provides a pressure sensor with a smaller sized diaphragm, which is capable of reading higher pressures. The present invention also provides a method and sensor for detecting strain using shape memory alloys.Type: GrantFiled: April 21, 2006Date of Patent: June 17, 2008Assignee: Orbital Research Inc.Inventors: Reed Carver, Joseph Snyder, Frederick J. Lisy, Troy Prince
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Patent number: 7334760Abstract: The present invention relates to a flow control device and more particularly to reactive self-contained modular flow control device with deployable flow effectors. The present invention further relates to a method of operating the flow control device. One embodiment of the present invention includes a method of controlling air flow across a surface of an aircraft under certain flight conditions comprising the steps of sensing fluid separation from the surface by measuring the pressure on the surface; determining a standard deviation of the pressure measurements over a period of time; and deploying a flow effector in response to the standard deviation of the pressure measurements exceeding a predetermined threshold number.Type: GrantFiled: September 19, 2006Date of Patent: February 26, 2008Assignee: Orbital Research Inc.Inventors: Frederick J. Lisy, Mohammed Modarreszadah, Mehul P. Patel, Jack M. DiCocco, Reed Carver, Robert N. Schmidt, Troy Prince
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Patent number: 7258015Abstract: The present invention relates to a method of determining both pressures and temperatures in a high temperature environment. The present invention also relates to a method of determining temperatures about a pressure-sensing element using a bi-functional heater. In addition, the present invention preferably relates to a pressure sensor with the pressure-sensing element and a heating element both integrated into the sensor's packaging, preferably onto the diaphragm of the pressure sensor, and particularly to such a pressure sensor capable of operating at high or elevated temperatures, and even more particularly to such a pressure sensor wherein the heating element is capable of both heating, at least in part, the pressure-sensing element and monitoring the temperature of the application area. Preferably, the pressure-sensing element is formed from shape memory alloy (SMA) materials that can be used at high or elevated temperatures as a pressure sensor with high sensitivity.Type: GrantFiled: September 14, 2005Date of Patent: August 21, 2007Assignee: Orbital Research Inc.Inventors: Greg S. Shaw, Troy Prince, Joseph Snyder, Mike Willett, Frederick Lisy
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Patent number: 7226015Abstract: The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.Type: GrantFiled: January 28, 2004Date of Patent: June 5, 2007Assignee: Orbital Research IncInventors: Troy Prince, Frederick J. Lisy, Mehul P. Patel, Jack M. DiCocco, Reed Carver, Robert N. Schmidt
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Patent number: 7070144Abstract: The present invention relates to an afterbody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor each having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.Type: GrantFiled: December 30, 2003Date of Patent: July 4, 2006Assignee: Orbital Research Inc.Inventors: Jack DiCocco, Troy Prince, Mehul Patel, Tsun Ming Terry Ng
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Patent number: 6866233Abstract: The present invention relates to a reconfigurable porous technology for fluid flow control system and more particularly to reconfigurable porosity fluid flow control system for vehicles such as aircraft, missiles, ground and water vehicles to improve the performance of such vehicles. The present invention further relates to a method of operating the reconfigurable fluid flow control system. In one embodiment, the present invention includes a reconfigurable porosity system for fluid flow control on the surface of an aircraft, missile, water-craft or ground vehicle comprising a porous outer skin comprising individual pores; individually addressable valves corresponding and connected to the individual pores for opening and closing the pores; and a pneumatic system for connecting the pores wherein fluid from a high pressure area of the porous outer skin can be directed to a low pressure area of the porous outer skin by opening and closing the individually addressable valves.Type: GrantFiled: January 3, 2003Date of Patent: March 15, 2005Assignee: Orbital Research Inc.Inventors: Mehul P. Patel, Jack M DiCocco, Troy Prince