Patents by Inventor Mark B. Hood

Mark B. Hood 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).

  • Method and system for in-flight fault monitoring of flight control actuators
    Patent number: 6622972
    Abstract: A method and system for detecting in-flight fault characteristics of flight control actuators is provided. Commands are sequentially sent to sets of actuators during flight in a manner that is expected to produce little or no net aircraft motion. The detection of motion indicates the possibility of a faulty actuator. If additional tests confirm the failure, the actuator is isolated and other actuators are compensated to adjust for the failed actuator, permitting continuation of safe and controllable fight by the flight crew and control for a safe landing. This isolation of the suspect failed actuator serves to prevent a possible upset of the aircraft control should the suspect actuator completely fail to a large offset condition, due to continued use during flight, a situation that may cause loss of control of the aircraft.
    Type: Grant
    Filed: October 31, 2001
    Date of Patent: September 23, 2003
    Assignee: The Boeing Company
    Inventors: James M. Urnes, Sr., Mark B. Hood
  • Method and system for in-flight fault monitoring of flight control actuators
    Publication number: 20030080256
    Abstract: A method and system for detecting in-flight fault characteristics of flight control actuators is provided. Commands are sequentially sent to sets of actuators during flight in a manner that is expected to produce little or no net aircraft motion. The detection of motion indicates the possibility of a faulty actuator. If additional tests confirm the failure, the actuator is isolated and other actuators are compensated to adjust for the failed actuator, permitting continuation of safe and controllable fight by the flight crew and control for a safe landing. This isolation of the suspect failed actuator serves to prevent a possible upset of the aircraft control should the suspect actuator completely fail to a large offset condition, due to continued use during flight, a situation that may cause loss of control of the aircraft.
    Type: Application
    Filed: October 31, 2001
    Publication date: May 1, 2003
    Inventors: James M. Urnes, Mark B. Hood