John S Eng296 Alta Loma Ave, Daly City, CA 94015

6370153, Apr 9, 2002

Apr 13, 1998

09/059381

John W. Eng - Southborough MA, 01772

H04J 102

370438, 370489, 370496

A method and system are disclosed for enabling point-to-point and multicast communication in a multiple access network using three types of communication channels, namely, one or more upstream payload channels, one or more upstream control channels and one or more downstream channels. Each channel illustratively is divided into slots or mini-slots. Each upstream payload channel is assigned for carrying upstream directed payload bitstreams from stations to a central controller. The central controller has an independent receiver for each upstream channel for simultaneous reception of control and payload bitstreams. Each station has at least one frequency agile programmable transmitter for sequential transmission of control and payload bitstreams or separate upstream control and payload channel transmitters, respectively, for simultaneous transmission of control and payload bitstreams. Each upstream control channel is assigned for carrying upstream directed control bitstreams, such as reservation request bitstreams requesting reservation of time slots of the upstream payload channel, from the stations to the central controller. At least one downstream channel is assigned for carrying at least downstream directed control bitstreams, such as bitstreams containing network configuration acknowledgments, collision, status of reservation request, and also containing indications of assigned slots in the upstream payload channel, from the central controller to the stations.

6489842, Dec 3, 2002

Jan 5, 2001

09/755392

John E. Eng - Buena Park CA

The Boeing Company - Seattle WA

H03F 358

330 43, 330124 R, 330127

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.

7138860, Nov 21, 2006

Nov 12, 2004

10/904498

John E Eng - Buena Park CA, US

The Boeing Company - Chicago IL

H03F 3/58

330 43, 315 35

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.

7139526, Nov 21, 2006

May 8, 2003

10/431903

Eric Nicol - San Pedro CA, US
John E. Eng - Buena Park CA, US

The Boeing Company - Chicago IL

H04B 7/185

455 134, 455 121, 455427, 370316, 370318

A power control system () for a satellite ( includes a high power amplifier circuit () that receives a saturated power output adjustment signal. The amplifier circuit () includes a programmable circuit (). An electronic power conditioner () is coupled to the programmable circuit () and is configured to reset an operating set-point of said high power amplifier circuit () in response to the saturated power output adjustment signal. A high power amplifier () has a variable output power range and amplifies a received signal in response to change in the operating set-point. A channel amplifier () is coupled to the programmable circuit () and is configured to gain offset the received signal in response to change in the operating set-point.

7170368, Jan 30, 2007

Nov 5, 2004

10/983282

John E. Eng - Buena Park CA, US

The Boeing Company - Chicago IL

H01P 5/12

333125, 333248

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.

7221907, May 22, 2007

Feb 12, 2003

10/365359

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

The Boeing Company - Chicago IL

H04B 7/185

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

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.

7358803, Apr 15, 2008

Dec 16, 2004

10/905119

David Ross Goldberg - Redondo Beach CA, US
John E. Eng - Buena Park CA, US
Eric F. Nicol - San Pedro CA, US

The Boeing Company - Chicago IL

H03F 3/58

330 43, 455 134, 455126, 4551271, 4551272

A power control system for a satellite receiving radio-frequency signals includes 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.

7484693, Feb 3, 2009

Sep 17, 2003

10/666664

John E. Eng - Buena Park CA, US

The Boeing Company - Chicago IL

B64G 1/44

2441733, 2441581

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.