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).

  • Patent number: 10137979
    Abstract: 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: Grant
    Filed: June 2, 2011
    Date of Patent: November 27, 2018
    Assignee: Orbital Research Inc.
    Inventors: Troy Prince, Frederick J. Lisy, Mehul P. Patel, Jack M. DiCocco, Reed Carver, Robert N. Schmidt
  • Patent number: 9637223
    Abstract: 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: Grant
    Filed: April 27, 2012
    Date of Patent: May 2, 2017
    Assignee: Orbital Reseach Inc.
    Inventors: Jack DiCocco, Troy Prince, Mehul Patel, Tsun Ming Terry Ng
  • Patent number: 9624836
    Abstract: 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: Grant
    Filed: October 2, 2015
    Date of Patent: April 18, 2017
    Assignee: Orbital Research Inc
    Inventors: Greg S Shaw, Troy Prince, Joseph Snyder, Michael C Willett, Frederick J Lisy
  • Patent number: 9157392
    Abstract: 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: Grant
    Filed: August 26, 2013
    Date of Patent: October 13, 2015
    Assignee: Orbital Research Inc.
    Inventors: Greg S Shaw, Troy Prince, Joseph Snyder, Michael C Willett, Frederick J Lisy
  • Publication number: 20150060593
    Abstract: 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: Application
    Filed: August 27, 2013
    Publication date: March 5, 2015
    Inventors: Troy Prince, Richard Kolacinski, Mehul Patel
  • Patent number: 8596131
    Abstract: 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: Grant
    Filed: January 31, 2012
    Date of Patent: December 3, 2013
    Assignee: Orbital Research Inc.
    Inventors: Reed Carver, Joseph Snyder, Frederick J Lisy, Troy Prince
  • Patent number: 8544335
    Abstract: 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: Grant
    Filed: July 26, 2011
    Date of Patent: October 1, 2013
    Assignee: Orbital Research Inc.
    Inventors: Greg S. Shaw, Troy Prince, Joseph Snyder, Michael C. Willet, Frederick J. Lisy
  • Patent number: 8417395
    Abstract: 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: Grant
    Filed: December 1, 2003
    Date of Patent: April 9, 2013
    Assignee: Orbitol Research Inc.
    Inventors: Troy Prince, Richard Kolacinski, Mehul Patel
  • Patent number: 8191833
    Abstract: 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: Grant
    Filed: May 2, 2006
    Date of Patent: June 5, 2012
    Assignee: Orbital Research Inc.
    Inventors: Jack DiCocco, Troy Prince, Mehul Patel, Tsun Ming Terry Ng
  • Patent number: 8127616
    Abstract: 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: Grant
    Filed: April 2, 2008
    Date of Patent: March 6, 2012
    Inventors: Reed Carver, Joseph Snyder, Frederick J. Lisy, Troy Prince
  • Patent number: 8006564
    Abstract: 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: Grant
    Filed: August 11, 2009
    Date of Patent: August 30, 2011
    Assignee: Orbital Research Inc.
    Inventors: Greg S. Shaw, Troy Prince, Joseph Snyder, Michael C. Willett, Frederick J. Lisy
  • Patent number: 7977615
    Abstract: 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: Grant
    Filed: May 7, 2007
    Date of Patent: July 12, 2011
    Assignee: Orbital Research Inc.
    Inventors: Troy Prince, Frederick J. Lisy, Mehul P. Patel, Jack M. DiCocco, Reed Carver, Robert N. Schmidt
  • Patent number: 7587944
    Abstract: 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: Grant
    Filed: July 21, 2008
    Date of Patent: September 15, 2009
    Assignee: Orbital Research Inc.
    Inventors: Greg Shaw, Troy Prince, Joseph Snyder, Mike Willett, Frederick Lisy
  • Patent number: 7415884
    Abstract: 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: Grant
    Filed: June 19, 2007
    Date of Patent: August 26, 2008
    Assignee: Orbital Research Inc.
    Inventors: Greg Shaw, Troy Prince, Joseph Snyder, Mike Willett, Frederick Lisy
  • Patent number: 7387028
    Abstract: 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: Grant
    Filed: April 21, 2006
    Date of Patent: June 17, 2008
    Assignee: Orbital Research Inc.
    Inventors: Reed Carver, Joseph Snyder, Frederick J. Lisy, Troy Prince
  • Patent number: 7334760
    Abstract: 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: Grant
    Filed: September 19, 2006
    Date of Patent: February 26, 2008
    Assignee: Orbital Research Inc.
    Inventors: Frederick J. Lisy, Mohammed Modarreszadah, Mehul P. Patel, Jack M. DiCocco, Reed Carver, Robert N. Schmidt, Troy Prince
  • Patent number: 7258015
    Abstract: 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: Grant
    Filed: September 14, 2005
    Date of Patent: August 21, 2007
    Assignee: Orbital Research Inc.
    Inventors: Greg S. Shaw, Troy Prince, Joseph Snyder, Mike Willett, Frederick Lisy
  • Patent number: 7226015
    Abstract: 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: Grant
    Filed: January 28, 2004
    Date of Patent: June 5, 2007
    Assignee: Orbital Research Inc
    Inventors: Troy Prince, Frederick J. Lisy, Mehul P. Patel, Jack M. DiCocco, Reed Carver, Robert N. Schmidt
  • Patent number: 7070144
    Abstract: 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: Grant
    Filed: December 30, 2003
    Date of Patent: July 4, 2006
    Assignee: Orbital Research Inc.
    Inventors: Jack DiCocco, Troy Prince, Mehul Patel, Tsun Ming Terry Ng
  • Patent number: 6866233
    Abstract: 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: Grant
    Filed: January 3, 2003
    Date of Patent: March 15, 2005
    Assignee: Orbital Research Inc.
    Inventors: Mehul P. Patel, Jack M DiCocco, Troy Prince