Stephen J Robinson

US Patent:

6577282, Jun 10, 2003

Filed:

Jul 19, 2000

Appl. No.:

09/619042

Inventors:

Sudhakar K. Rao - Torrance CA
Chih-Chien Hsu - Torrance CA
George Voulelikas - El Segun CA
Stephen A. Robinson - North Hills CA

Assignee:

Hughes Electronics Corporation - El Segundo CA

International Classification:

H01Q 1300

US Classification:

343781CA, 343840, 343781 P

Abstract:

A method and system for reconfiguring an antenna system are disclosed. The system comprises a feed horn, a subreflector, and a main reflector. The feed horn is pointed at an axis removed from the bisector axis of the subreflector. The distance between the feed horn and the subreflector can be changed to defocus the feed horn with respect to the subreflector, wherein a size of the outgoing beam emanating from the main reflector changes when the distance between the feed horn and the subreflector is changed. The method comprises pointing an axis of a feed horn at a subreflector, wherein the axis of the feed horn is aligned differently from the bisector axis of the subreflector, and changing the distance between the feed horn and the subreflector to defocus the feed horn with respect to the subreflector, wherein a size of an outgoing beam emanating from a main reflector changes when the distance between the feed horn and the subreflector is changed.

US Patent:

55744729, Nov 12, 1996

Filed:

Jun 30, 1995

Appl. No.:

8/491331

Inventors:

Stephen A. Robinson - Sepulveda CA

Assignee:

Hughes Electronics - Los Angeles CA

International Classification:

H01Q 1520

US Classification:

343915

Abstract:

A method for stowing a unitary flexible antenna reflector 10 in a confining envelope and deploying the reflector from the envelope. In a most general sense, the invention includes the steps of: a) applying a deforming force to diametrically opposed positions 16 and 18 near an edge of the reflector 10 to place the reflector in a deformed state; b) maintaining the reflector 10 in the deformed state until deployment; and c) releasing the reflector 10 from the deformed state. In a specific embodiment, the step of maintaining the reflector 10 in a deformed state includes the step of attaching a restraining element between the diametrically opposed positions on the edge of the reflector which is released on deployment.

US Patent:

56140339, Mar 25, 1997

Filed:

Aug 8, 1995

Appl. No.:

8/512727

Inventors:

Stephen A. Robinson - North Hills CA
Stanley J. Krause - Northridge CA

Assignee:

Hughes Aircraft Company - Los Angeles CA

International Classification:

H01L 31052

US Classification:

136246

Abstract:

Discrete carrier and lattice structures are bonded together to form a lightweight rigid solar panel. The carrier includes a pair of electrically inert face sheets bonded on opposite sides of a thin thermoconductive honeycomb core. The face sheets provide an electrically inert surface for receiving a solar cell array and the honeycomb core forms a heat sink for conducting heat away from the solar cell array. The lattice includes a pair of patterned face sheets having a high elastic modulus bonded on opposite sides of a lattice base. The patterned face sheets provide axial stiffness and the lattice base separates them to provide bending stiffness. By splitting the solar panel into discrete carrier and lattice components, the present invention reduces the weight of existing solar panels by approximately 40% and increases power efficiency by approximately 10%.

US Patent:

63238179, Nov 27, 2001

Filed:

Jan 19, 2000

Appl. No.:

9/488205

Inventors:

Parthasarathy Ramanujam - Redondo Beach CA
Stephen A. Robinson - North Hills CA
Philip H. Law - Encino CA

Assignee:

Hughes Electronics Corporation - El Segundo CA

International Classification:

H01Q 1300

US Classification:

343781P

Abstract:

A method and apparatus for producing contiguous spot beam communications coverage on the Earth's surface are disclosed. The apparatus comprises an antenna system including two wide scan antennas and two narrow scan antennas. The two wide scan antennas are disposed substantially opposite each other, and the two narrow scan antennas are disposed substantially opposite each other and substantially normal to the wide scan antennas. The first wide scan antenna, second wide scan antenna, and first narrow scan antenna produce a first beam pattern on a planetary surface and the first wide scan antenna, second wide scan antenna, and second narrow scan antenna produce a second beam pattern on the planetary surface.

US Patent:

62083171, Mar 27, 2001

Filed:

Feb 15, 2000

Appl. No.:

9/504544

Inventors:

Robert M. Taylor - Redondo Beach CA
James R. Gillett - Northridge CA
Stephen A. Robinson - North Hills CA
Hans P. Naepflin - Manhattan Beach CA

Assignee:

Hughes Electronics Corporation - El Segundo CA

International Classification:

H01Q15/20

US Classification:

343915

Abstract:

The present invention is directed to a method of and a device for adjusting the concavity of a springback antenna reflector. The method and device of the present invention can be used to adjust the concavity of the springback reflector prior to stowage within a satellite to correct actual or anticipated variations in the desired shape of reflector that are caused by storage of the reflector, fabrication of the reflector, thermal effects on the reflector, and moisture absorption by the material from which the reflector is fabricated. By adjusting the concavity of the reflector to correct the variations in the shape of the reflector, degradation of the performance of the reflector due to distortions in the shape of the reflector may be greatly reduced.

US Patent:

43007376, Nov 17, 1981

Filed:

Apr 21, 1980

Appl. No.:

6/142483

Inventors:

Allan B. Byrne - Los Angeles CA
Richard G. Otis - Whittier CA
Stephen A. Robinson - Sepulveda CA

Assignee:

Hughes Aircraft Company - Culver City CA

International Classification:

B64G 100
B64D 900

US Classification:

244158R

Abstract:

A spacecraft specifically adapted for launch from the space shuttle by means of a cradle having locking and ejection mechanisms mounted therein. The cradle fastens into the payload bay of the space shuttle and returns therewith for reuse in subsequent launches. The spacecraft mounts at three points to the cradle, and the cradle mounts at three points to the shuttle such that a plane through the attachment points passes through the roll axis of the spacecraft at approximately the center of mass thereof. The cradle utilizes the truss structure of the spacecraft to produce the required stiffness by providing a structural tie between the two ends and the bottom of the cradle. At launch, the spacecraft is ejected with both linear and angular momentum, the spin providing gyroscopic stability. The locking mechanisms in the cradle can be remotely controlled to relock the spacecraft to the cradle in the event of an unsuccessful deployment attempt. The spacecraft includes a safety circuit employing acceleration sensing switches which sense spin-up of the spacecraft and prevent premature ignition of the perigee boost motor.

US Patent:

20160378701, Dec 29, 2016

Filed:

Jun 26, 2015

Appl. No.:

14/751899

Inventors:

- Santa Clara CA, US
Daniel F. Cutter - Maynard MA, US
Stephen J. Robinson - Austin TX, US
Mukesh K. Patel - Round Rock TX, US

International Classification:

G06F 13/28
G06F 12/08
G06F 13/40

Abstract:

An apparatus having a fabric interconnect that supports multiple topologies and method for using the same are disclosed. In one embodiment, the apparatus comprises mode memory to store information indicative of one of the plurality of modes; and a first fabric operable in a plurality of modes, where the fabric comprises logic coupled to the mode memory to control processing of read and write requests to memory received by the first fabric according to the mode identified by the information indicative.