Patents by Inventor Tsun Ming Terry Ng

Tsun Ming 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).

  • Aircraft and missile afterbody flow control device and method of controlling flow
    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
  • Aircraft and missile afterbody flow control device and method of controlling flow
    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
  • Aircraft and missile afterbody flow control device and method of controlling flow
    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