John Eng

US Patent:

6489842, Dec 3, 2002

Filed:

Jan 5, 2001

Appl. No.:

09/755392

Inventors:

John E. Eng - Buena Park CA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H03F 358

US Classification:

330 43, 330124 R, 330127

Abstract:

A microwave tube system for use with a spacecraft telecommunication system is provided. The system includes a traveling wave tube subsystem, a high voltage converter subsystem, and a low voltage converter subsystem. The traveling wave tube subsystem includes a plurality of traveling wave tubes. The high voltage converter subsystem powers the traveling wave tube subsystem. The high voltage converter subsystem includes a plurality of high voltage converter members that are paired with the traveling wave tubes on a one-to-one basis. The low voltage converter subsystem is a central power conditioner subsystem including a plurality of low voltage power conditioners that are connected in parallel to one another. A common power output of the central power conditioner subsystem is received by the high voltage converter members which in turn power the traveling wave tubes that are paired with the high voltage converters. Such configured central power conditioner subsystem requires less circuitry and fewer low voltage power conditioners thereby resulting in lower spacecraft weight and volume.

US Patent:

7138860, Nov 21, 2006

Filed:

Nov 12, 2004

Appl. No.:

10/904498

Inventors:

John E Eng - Buena Park CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

H03F 3/58

US Classification:

330 43, 315 35

Abstract:

A power control system for a satellite receiving radio-frequency signals includes a digital processor and a traveling wave tube amplifier system and corresponding traveling wave tube. An anode voltage of the traveling wave tube amplifier system is used to modulate or saturate the current of the electron beam of the traveling wave tube so that the output power of the traveling wave tube amplifier system, from the saturated electron beam, is proportional to a waveform envelope of the radio-frequency signals. The digital processor controls anode and RF input signal amplitudes to the traveling wave tube and predicts necessary corrections.

US Patent:

7170368, Jan 30, 2007

Filed:

Nov 5, 2004

Appl. No.:

10/983282

Inventors:

John E. Eng - Buena Park CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

H01P 5/12

US Classification:

333125, 333248

Abstract:

An apparatuses and methods for phase matching power combined signals are described. A typical apparatus includes at least a waveguide portion in at least a first branch conducting a first electromagnetic signal of a combiner, the waveguide portion having an effective size and a thermal control system effecting a temperature change in the waveguide portion to alter the effective size. Altering the effective size of the waveguide portion adjusts phase matching between the first electromagnetic signal of the first branch and at least a second electromagnetic signal of a second branch of the combiner. High thermal expansion coefficient materials including silver plated polyetherimide can be used. In addition, composite materials having anisotropic thermal expansion may be used.

US Patent:

7221907, May 22, 2007

Filed:

Feb 12, 2003

Appl. No.:

10/365359

Inventors:

John E. Eng - Buena Park CA, US
Donald J. Mirrione - Gilbert AZ, US
Dale H. Claxton - Encino CA, US
Brian J. Behler - Lomita CA, US
James Lee - Monterey Park CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

H04B 7/185

US Classification:

455 121, 455 132, 455 133, 455 134, 370318

Abstract:

A power system for a satellite includes a high power amplifier that has a control input. The high power amplifier has a minimum effective isotropic radiated power. A controller is coupled to the control input. The controller generates a control signal to adjust a saturated power output of the high power amplifier to the minimum effective isotropic radiated power.

US Patent:

7484693, Feb 3, 2009

Filed:

Sep 17, 2003

Appl. No.:

10/666664

Inventors:

John E. Eng - Buena Park CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64G 1/44

US Classification:

2441733, 2441581

Abstract:

A system for single wire secondary distribution comprising a spacecraft platform; a central bus interface unit coupled to the spacecraft platform; a payload unit coupled to the central bus interface unit; and a centralized power supply for powering the central bus interface unit and the payload unit; wherein the spacecraft platform provides a command to the central bus interface unit; wherein the central bus interface unit interrupts the power to the payload unit in a manner corresponding to the commands received by the central bus interface unit; wherein the payload unit decodes the interruption to the power and executes the command from the spacecraft platform.

US Patent:

8245979, Aug 21, 2012

Filed:

Dec 12, 2008

Appl. No.:

12/333978

Inventors:

John E. Eng - Buena Park CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64G 1/00

US Classification:

2441581, 244 751, 2441291, 244227, 34087019, 34087024, 340538, 3408558

Abstract:

A system for single wire secondary distribution comprising a spacecraft platform; a central bus interface unit coupled to the spacecraft platform; a payload unit coupled to the central bus interface unit; and a centralized power supply for powering the central bus interface unit and the payload unit; wherein the spacecraft platform provides a command to the central bus interface unit; wherein the central bus interface unit interrupts the power to the payload unit in a manner corresponding to the commands received by the central bus interface unit; wherein the payload unit decodes the interruption to the power and executes the command from the spacecraft platform.

US Patent:

47852070, Nov 15, 1988

Filed:

Jan 21, 1987

Appl. No.:

7/005716

Inventors:

John E. Eng - Buena Park CA

Assignee:

Hughes Aircraft Company - Los Angeles CA

International Classification:

H03K 1716

US Classification:

307577

Abstract:

A leakage regulator for use with switching power supplies which include a field effect transistor (FET) is disclosed. The leakage regulator comprises a bias circuit coupled in a feedback arrangement with the FET to provide a self-generated bias voltage. The bias circuit includes a current transformer coupled to receive a drain-source leakage current. A bias voltage is generated from the transformed leakage current and this bias voltage is applied to the FET gate to help decrease the leakage current.

US Patent:

61011045, Aug 8, 2000

Filed:

Jun 4, 1998

Appl. No.:

9/090728

Inventors:

John E. Eng - Buena Park CA

Assignee:

Hughes Electronics Corporation - Los Angeles CA

International Classification:

H02M 7217

US Classification:

363 21

Abstract:

A method and apparatus are disclosed for controlling the operation of a synchronous rectifier used in power conversion circuitry. The disclosed method and apparatus senses the voltage across the synchronous rectifier, and turns the synchronous rectifier OFF when the voltage across the rectifier is about to change direction. Preferably, the synchronous rectifier is commanded OFF at the approximate instant when the voltage across the rectifier reaches approximately zero, which also corresponds to a current of approximately zero. Accordingly, currents are prevented from flowing in the reverse direction in the synchronous rectifier. This results in approximately zero voltage and zero current switching when the rectifier is turned OFF, thereby minimizing switching losses.