Patents by Inventor Terry Ng
Terry Ng 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: 11928204Abstract: A TEE system that includes a first platform that runs a first TEE, a second platform that runs a second TEE, and a merging unit that is adapted to merge a first output from the first TEE of the first platform, with a second output from the second TEE of the second platform, so as to form an output of the TEE system. The first TEE and the second TEE are based on different implementations. In this way, the security of the system is improved, as a malicious actor even be able to access “t” machines, still would not be able to retrieve the secret unless there are multiple exploitable TEE vulnerabilities on all executing TEE platforms at the same time.Type: GrantFiled: December 13, 2021Date of Patent: March 12, 2024Assignee: Foris Technology Pte LtdInventors: Kian Chuan Yap, Ming Sum Sam Ng, Jason Wai King Lau, Chun Ting Yip, Tung Ling Terry Young, Durgesh Pandey
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Patent number: 9683820Abstract: The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and a method for increasing the maneuverability or stability of an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to a method for increasing the maneuverability or stability of an aircraft, missile, underwater vehicle or projectile through the use of removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.Type: GrantFiled: January 4, 2013Date of Patent: June 20, 2017Assignee: Orbital Research Inc.Inventors: Mehul Patel, T. Terry Ng, Alan B. Cain, Zak Sowle, Jack DiCocco
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Patent number: 9664485Abstract: An aircraft, missile, projectile, or underwater vehicle with an improved control system, an improved control system, or a method of maneuvering an aircraft, missile, projectile, or underwater vehicle uses control surfaces that are movable along a track. The control system on a track (or “tracked control surface”) advantageously enables the aircraft, missile, projectile, or underwater vehicle to have an unlimited number of configurations, each configuration being tailored to the specific stability or maneuverability requirements during a specific portion of the flight by adjusting the center of pressure of the aircraft, missile, projectile, or underwater vehicle relative to its center of gravity.Type: GrantFiled: July 2, 2014Date of Patent: May 30, 2017Assignee: Orbital Research Inc.Inventors: Mehul P. Patel, T. Terry Ng, Paul Suchy
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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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Aircraft, missile, projectile or underwater vehicle with improved control system and method of using
Patent number: 8809755Abstract: The present invention relates to an aircraft, missile, projectile or underwater vehicle with an improved control system, an improved control system and a method of maneuvering an aircraft, missile, projectile or underwater vehicle. More particularly, the present invention relates to an aircraft, missile, projectile or underwater vehicle with control surfaces that are movable along a track. The present invention further relates to a method of controlling a aircraft, missile, projectile or underwater vehicle using such a control system. One of the technical advantages of the control system on a track (or “tracked control surface”) over other aircraft, missile, projectile or underwater vehicle control systems is that the tracked control surface system enables the aircraft, missile, projectile or underwater vehicle to have an unlimited number of configurations, each configuration being tailored to the specific stability or maneuverability requirements during a specific portion of the flight.Type: GrantFiled: December 2, 2005Date of Patent: August 19, 2014Assignee: Orbital Research Inc.Inventors: Mehul Patel, T. Terry Ng, Paul Suchy -
Patent number: 8367992Abstract: The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and a method for increasing the maneuverability or stability of an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to a method for increasing the maneuverability or stability of an aircraft, missile, underwater vehicle or projectile through the use of removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.Type: GrantFiled: December 23, 2010Date of Patent: February 5, 2013Assignee: Orbital Research Inc.Inventors: Mehul Patel, T Terry Ng, Alan B Cain, Zak Sowle, Jack DiCocco
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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: 8096507Abstract: An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section.Type: GrantFiled: January 23, 2009Date of Patent: January 17, 2012Assignees: Innovative Technology Applications, University of Notre Dame Du LacInventors: Alan B. Cain, Eric J. Jumper, Donald J. Wittich, III, Edward J. Kerschen, David Cavalieri, T. Terry Ng
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Patent number: 7880125Abstract: The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and an improved control system for maneuvering an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to an aircraft, missile, underwater vehicle or projectile with removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.Type: GrantFiled: March 19, 2008Date of Patent: February 1, 2011Assignee: Orbital Research Inc.Inventors: Mehul Patel, T. Terry Ng, Alan B. Cain, Zak Sowle, Jack DiCocco
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Patent number: 7709772Abstract: The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and an improved control system for maneuvering an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to an aircraft, missile, underwater vehicle or projectile with removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.Type: GrantFiled: December 2, 2005Date of Patent: May 4, 2010Assignee: Orbital Research Inc.Inventors: Mehul Patel, T. Terry Ng, Alan B. Cain, Zak Sowle, Jack DiCocco
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Publication number: 20090242702Abstract: An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section.Type: ApplicationFiled: January 23, 2009Publication date: October 1, 2009Inventors: Alan B. Cain, Eric J. Jumper, Donald J. Wittich, III, Edward J. Kerschen, David Cavalieri, T. Terry Ng
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Patent number: 7295292Abstract: Methods and systems are described for a system for measuring aberrations in a wave front. In the improved system multiple closely-spaced, small-aperture laser beams traverse an aberrating flow that introduces deflections of small-aperture laser beams from which aberrated wavefronts can be constructed. These beams may then be focused on position sensing devices using focusing lenses. The position sensing devices may then detect the positions of these beams and a difference between the detected position and the unaberrated position of the beams detected. This information may then be used to determine information regarding the optical aberrations introduced by the flow that may be used, for example, in improving communications systems and/or laser weapon systems.Type: GrantFiled: May 19, 2005Date of Patent: November 13, 2007Assignee: The University of Notre DameInventors: Eric Jumper, Stanislav Gordeyev, Alan Cain, Terry Ng
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Publication number: 20070104739Abstract: The present invention provides an immunogenically active component comprising inactivated Sarcocystis neurona cells and/or inactivated Neospora hughesi cells; antigens derived therefrom; DNA derived therefrom; or a mixture; or in combination with other vaccine components thereof. Further provided are vaccine compositions useful for preventing or ameliorating equine protozoal myeloencephalitis infection and disease and a method for the cell culture propagation of protozoan parasites.Type: ApplicationFiled: December 12, 2006Publication date: May 10, 2007Inventors: Rocky Bigbie, Terry Ng, Joseph Whalen
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Publication number: 20060269571Abstract: An immunotherapeutic composition and prophylactic and/or therapeutic methods of treatment are provided for West Nile virus in animals, and particularly non-human animals, such as horses, wherein said first flavivirus is less virulent and/or pathogenic flavivirus than said second flavivirus The composition and method of treatment include a monoclonal antibody to Kunjin virus E protein, wherein the monoclonal antibody is capable of neutralizing West Nile virus in the non-human animal notwithstanding that West Nile virus is more virulent and/or pathogenic than Kunjin virus.Type: ApplicationFiled: November 22, 2005Publication date: November 30, 2006Inventors: Roy Hall, Terry Ng, Hsien-Jue Chu
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Publication number: 20060222660Abstract: A method, composition and kit for reducing or preventing immunogenic interference in a multi-valent vaccine utilizes a nucleic acid or DNA component along with other non-nucleic acid immunogenic components.Type: ApplicationFiled: March 28, 2006Publication date: October 5, 2006Applicant: WyethInventors: Hsien-Jue Chu, Yu-Wei Chiang, Terry Ng
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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: 6302360Abstract: Apparatus for generating vortices to control the flow of air across a airfoil of an aircraft includes a series of pressure active regions arranged along the leading edge of the airfoil. The pressure active regions include spaced apart valves connected to a source of vacuum, a controller for activating the valves, and sensors for sensing air pressure. The controller is configured to activate the valves in response to the pressure sensed by the sensors, wherein the spaced apart valves are connected to a source of pressurized air as well as to the source of vacuum.Type: GrantFiled: January 10, 2000Date of Patent: October 16, 2001Assignee: The University of ToledoInventor: T. Terry Ng