Patents by Inventor Chuong B. Tran
Chuong B. Tran 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: 8752789Abstract: A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current operation parameters to form an identified position limit. Responsive to receiving a command to move the control surface on a vehicle to a new position, the control surface is commanded to move to a position within the identified position limit.Type: GrantFiled: December 16, 2012Date of Patent: June 17, 2014Assignee: The Boeing CompanyInventors: Chuong B. Tran, Kioumars Najmabadi, Edward E. Coleman, David W. Grubb
-
Patent number: 8342445Abstract: A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current operation parameters to form an identified position limit. Responsive to receiving a command to move the control surface on a vehicle to a new position, the control surface is commanded to move to a position within the identified position limit.Type: GrantFiled: September 26, 2008Date of Patent: January 1, 2013Assignee: The Boeing CompanyInventors: Chuong B. Tran, Kioumars Najmabadi, Edward E. Coleman, David W. Grubb
-
Publication number: 20100078518Abstract: A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current operation parameters to form an identified position limit. Responsive to receiving a command to move the control surface on a vehicle to a new position, the control surface is commanded to move to a position within the identified position limit.Type: ApplicationFiled: September 26, 2008Publication date: April 1, 2010Inventors: Chuong B. Tran, Kioumars Najmabadi, Edward E. Coleman, David W. Grubb
-
Patent number: 7191985Abstract: Vibrations due to excitation of the natural modes of an aircraft's body are suppressed by an active multi-axis modal suppression system. Dedicated sensors are positioned in the aircraft at optimal locations for sensing modal induced vibrations. The sensor produced signals are processed through control logic which, in response thereto, and in response to aircraft inertial, velocity and altitude related signals produces output control signals. The control signals effect control surface deployment creating forces to suppress the natural mode induced vibrations on multiple geometric axis's. More particularly, a symmetric and anti-symmetric control surface deployments are used on one or more geometric axis'to damp lateral, longitudinal, vertical and most importantly torsional vibrational modes.Type: GrantFiled: July 12, 2005Date of Patent: March 20, 2007Assignee: The Boeing CompanyInventors: Kioumars Najmabadi, Chuong B. Tran, John Koon-Hung Ho
-
Patent number: 6915989Abstract: Vibrations due to excitation of the natural modes of an aircraft's body are suppressed by an active multi-axis modal suppression system. Dedicated sensors are positioned in the aircraft at optimal locations for sensing modal induced vibrations. The sensor produced signals are processed through control logic which, in response thereto, and in response to aircraft inertial, velocity and altitude related signals produces output control signals. The control signals effect control surface deployment creating forces to suppress the natural mode induced vibrations on multiple geometric axis's. More particularly, symmetric and anti-symmetric control surface deployments are used on one or more geometric axis's to damp lateral, longitudinal, vertical and most importantly torsional vibrational modes.Type: GrantFiled: May 1, 2002Date of Patent: July 12, 2005Assignee: The Boeing CompanyInventors: Kioumars Najmabadi, Chuong B. Tran, John Koon-Hung Ho
-
Publication number: 20030205644Abstract: Vibrations due to excitation of the natural modes of an aircraft's body are suppressed by an active multi-axis modal suppression system. Dedicated sensors are positioned in the aircraft at optimal locations for sensing modal induced vibrations. The sensor produced signals are processed through control logic which, in response thereto, and in response to aircraft inertial, velocity and altitude related signals produces output control signals. The control signals effect control surface deployment creating forces to suppress the natural mode induced vibrations on multiple geometric axis's. More particularly, symmetric and anti-symmetric control surface deployments are used on one or more geometric axis's to damp lateral, longitudinal, vertical and most importantly torsional vibrational modes.Type: ApplicationFiled: May 1, 2002Publication date: November 6, 2003Inventors: Kioumars Najmabadi, Chuong B. Tran, John Koon-Hung Ho
-
Patent number: 5860625Abstract: An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.Type: GrantFiled: December 30, 1996Date of Patent: January 19, 1999Assignee: The Boeing CompanyInventors: Chuong B. Tran, Stephen White
-
Patent number: 5839697Abstract: An improved method and apparatus for determining the amount of turn coordination gain in an aircraft yaw damper during a turn maneuver is disclosed. The yaw damper includes inputs from the inertial reference units of the aircraft and also from the flight management computer of the aircraft. The flight management computer provides to the yaw damper a signal indicative of the position of the flaps of the aircraft. The yaw damper includes a turn coordination gain box that receives the flap position signal and outputs a turn coordination gain value, dependent upon the flap position. Generally, the turn coordination gain value increases as the flap position is more extended. The precise turn coordination gain value for each flap position is dependent upon the particular aerodynamic characteristics of the aircraft.Type: GrantFiled: May 14, 1996Date of Patent: November 24, 1998Assignee: The Boeing CompanyInventor: Chuong B. Tran
-
Patent number: 5833173Abstract: An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.Type: GrantFiled: October 8, 1996Date of Patent: November 10, 1998Assignee: The Boeing CompanyInventors: Chuong B. Tran, Stephen White
-
Patent number: 5667166Abstract: An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.Type: GrantFiled: February 13, 1996Date of Patent: September 16, 1997Assignee: The Boeing CompanyInventors: Chuong B. Tran, Stephen White
-
Patent number: 5452865Abstract: An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.Type: GrantFiled: June 28, 1993Date of Patent: September 26, 1995Assignee: The Boeing CompanyInventors: Chuong B. Tran, Stephen White
-
Patent number: 5072893Abstract: Accelerations due to excitation of the natural modes of an aircraft's body are suppressed by an active suppression system. Dedicated accelerometers are positioned in the aircraft at optimal locations for sensing modal induced lateral accelerations. The accelerometer produced signals are processed through control logic which, in response thereto, and in response to aircraft velocity and altitude related signals produces output control signals. The control signals effect rudder deployment creating forces to suppress the natural mode induced accelerations.Type: GrantFiled: May 28, 1987Date of Patent: December 17, 1991