John Y Ho

Address:

22404 SE 33 Pl, Sammamish, WA 98075

VIN:

JTHBJ46G072072282

Make:

LEXUS

Model:

ES 350

Year:

2007

US Patent:

6915989, Jul 12, 2005

Filed:

May 1, 2002

Appl. No.:

10/136907

Inventors:

Kioumars Najmabadi - Bellevue WA, US
Chuong B. Tran - Mukilteo WA, US
John Koon-Hung Ho - Shoreline WA, US

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C013/16

US Classification:

244195, 244177, 244 75 R

Abstract:

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.

US Patent:

7191985, Mar 20, 2007

Filed:

Jul 12, 2005

Appl. No.:

11/180309

Inventors:

Kioumars Najmabadi - Bellevue WA, US
Chuong B. Tran - Mukilteo WA, US
John Koon-Hung Ho - Shoreline WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 13/16

US Classification:

244195, 244177, 244 751

Abstract:

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.

US Patent:

8024079, Sep 20, 2011

Filed:

May 20, 2008

Appl. No.:

12/123942

Inventors:

Kioumars Najmabadi - Clyde Hill WA, US
William F. Shivitz - Renton WA, US
Edward Ernest Coleman - Forest Park WA, US
John Koon-hung Ho - Shoreline WA, US
Richard D. Johnson - Edmonds WA, US
William F. Carver - Shoreline WA, US
David W. Grubb - Monroe WA, US
Robert James McIntosh - Bothell WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G01C 23/00
G06F 17/10
B64C 3/58

US Classification:

701 3, 701124, 244 49, 244213

Abstract:

A computer implemented method, apparatus, and computer usable program product for symmetric and anti-symmetric control of aircraft flight control surfaces to reduce wing-body loads. Commands are sent to symmetrically deploy outboard control surfaces to shift wing air-loads inboard based on airplane state and speed brake deployment. Surface rate retraction on a wing with peak loads is limited to reduce maximum loads due to wheel checkback accompanied by utilization of opposite wing control surfaces to retain roll characteristics. Airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform a positive gravity maneuver. In a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads. High gain feedback commands are filtered from wing structural modes above one hertz by a set of linear and non-linear filters.

US Patent:

20100139680, Jun 10, 2010

Filed:

Dec 10, 2008

Appl. No.:

12/331970

Inventors:

John Ho - Alexandria VA, US
Yvonne Le - Alexandria VA, US

International Classification:

A61H 33/00

US Classification:

132200

Abstract:

A method of treatment of the skin of a human individual by fish which eat the top layer of skin includes providing a separate supply of fish for the individual, and suspending the skin to be treated in water in a fish container which may be adapted to receive a specific body part, such as a single foot or two feet, or a single hand or two hands. Each fish must be large enough to eat the top layer of skin of the individual, but should not have matured to the point of being capable of reproduction.

US Patent:

59496770, Sep 7, 1999

Filed:

Jan 9, 1997

Appl. No.:

8/780906

Inventors:

John K. Ho - Scottsdale AZ

Assignee:

Honeywell Inc. - Minneapolis MN

International Classification:

G05B 902
G05B 1101
G05B 1304
G06F 1100

US Classification:

364185

Abstract:

A control architecture having improved fault detection and correction capabilities is disclosed. The system comprises primary and monitor control systems, each having an associated control signal. A fault detector generates an alarm signal based upon differences observed between the primary and monitor control signal. The detector comprises an integrator and a memory means, and alarm signals are generated based upon the total amount of difference observed over a predetermined period of time. In one embodiment of the invention, primary and monitor control signals are averaged to provide a signal that is more fault tolerant than the individual control signals.

US Patent:

59019271, May 11, 1999

Filed:

Jul 18, 1996

Appl. No.:

8/683492

Inventors:

John Koon-Hung Ho - Scottsdale AZ

Assignee:

Honeywell Inc. - Minneapolis MN

International Classification:

B64C13/18

US Classification:

244183

Abstract:

A method and apparatus for use with an aircraft autopilot to prevent an aircraft part from striking the ground during near ground maneuvers by employing a protection circuit between the outer loop and the inner loop of the control chain between the autopilot and the control surface, the prevention circuit producing an output signal when there is a possibility of ground strike which output signal operates to reduce the control surface command signal from the inner loop to the control surface and thus be rapidly responsive to aircraft attitude changes that could produce ground strike.