Geoffrey Wm Marks

US Patent:

7759664, Jul 20, 2010

Filed:

Jan 5, 2007

Appl. No.:

11/650380

Inventors:

Geoffrey William Marks - Santa Barbara CA, US
James Trevor Renshall - Moorpark CA, US

Assignee:

Northrop Grumman Systems Corporation - Los Angeles CA

International Classification:

B64G 1/44
B64G 1/54
G21F 3/00

US Classification:

2505051, 2505151, 2505171, 2505191, 2441594, 2441718

Abstract:

An embodiment of the present method may comprise: heating up at least one structural element beyond a change state temperature thereof; changing the configuration of the structural element from an extended configuration to a reduced size configuration; cooling the structural element to below the change state temperature thereof; covering the structural element with a thermal protection device; removing the thermal protection device to expose the structural element to heat radiation; and heating, via the heat radiation, at least a portion of the structural element to thereby cause the structural element to change from the reduced size configuration to the extended configuration. In one embodiment each of the structural elements is formed from a thin elastic memory composite material.

US Patent:

20060270301, Nov 30, 2006

Filed:

May 25, 2005

Appl. No.:

11/137186

Inventors:

Geoffrey Marks - Santa Barbara CA, US

International Classification:

B32B 27/12
D04B 21/00
B32B 15/14

US Classification:

442316000, 442304000, 442038000

Abstract:

A radio frequency reflective film includes a radio frequency reflective mesh, a plurality of carbon nano-structure materials, and an elastomer. The elastomer encapsulates the radio frequency reflective mesh and the carbon nano-structure materials.

US Patent:

56801459, Oct 21, 1997

Filed:

Mar 12, 1996

Appl. No.:

8/614329

Inventors:

Mark W. Thomson - Ventura CA
Geoffrey W. Marks - Santa Barbara CA
John M. Hedgepeth - Santa Barbara CA

Assignee:

Astro Aerospace Corporation - Carpinteria CA

International Classification:

H01Q 1520

US Classification:

343915

Abstract:

A reflector assembly for use in antennas or solar collectors in which light weight and high reflector surface shape accuracy are essential for maintaining desired RF or light reflection requirements. The assembly is provided with a rigid, deployable outer support rim and at least one curved frame net supported by the outer rim. The frame net may be formed of a network of intersecting bands extending across the surface. A reflective material is placed against the frame net. A load is applied to the frame net to form a concave surface. The assembly is collapsible for convenient delivery into space prior to deployment.

US Patent:

61681164, Jan 2, 2001

Filed:

Jun 21, 1999

Appl. No.:

9/336788

Inventors:

James T. Renshall - Ojai CA
Geoffrey W. Marks - Santa Barbara CA

Assignee:

TRW Astro Aerospace - Carpinteria CA

International Classification:

B64G 144

US Classification:

244173

Abstract:

A spacecraft, such as a satellite, includes a panel array comprised of a plurality of panels that are stacked together and secured to the side of the satellite during launch. At least one shear tie device is configured to couple the panels together in shear to increase the resistance to deformation of the stack of panels. The shear tie device preferably comprises a male member that mates with a female member. A plurality of fingers secure the male member within the female member during launch. Upon reaching orbit, a bladder is inflated which deforms the fingers and releases the male member from engagement with the female member.

US Patent:

55207472, May 28, 1996

Filed:

May 2, 1994

Appl. No.:

8/236426

Inventors:

Geoffrey W. Marks - Santa Barbara CA

Assignee:

Astro Aerospace Corporation - Carpinteria CA

International Classification:

H01L 31045

US Classification:

136245

Abstract:

A low concentration solar array for spacecraft and other uses which has a series of solar panels which can be deployed from a folded stowed configuration to a planar configuration. When the solar panels are stowed, the padding of reflector panels cushions and protects the solar panels from the stresses and vibrations of launch and space flight. Once the solar panels are extended into a deployed planar configuration, the reflector panels are raised to concentrate sunlight upon the solar panels. These reflector panels are constructed from rigid honeycomb substrates and therefore are the active structural members of the solar array, providing the structural rigidity for the solar array.

US Patent:

20190144139, May 16, 2019

Filed:

Nov 13, 2017

Appl. No.:

15/811345

Inventors:

- FALLS CHURCH VA, US
GEOFFREY W. MARKS - SANTA BARBARA CA, US

International Classification:

B64G 1/22

Abstract:

A boom and reflector assembly for a spacecraft including a telescopic boom having a plurality of tubular sections that are nested together within a base section when the boom is in a stowed position, where the base section is mounted to a stowing cradle within the spacecraft by a root hinge. The assembly also includes a reflector having an outer truss structure including truss rods that are collapsible to allow the reflector to be collapsed into a stowed configuration, where the reflector is mounted to an outer one of the tubular sections having a smallest diameter by a wrist hinge. The assembly is configured to be released by the root hinge to rotate the boom and the reflector, rotate the collapsed reflector on the wrist hinge, deploy the reflector from the collapsed configuration to a deployed configuration, and then extend the boom to move the reflector away from the spacecraft.

US Patent:

20160159500, Jun 9, 2016

Filed:

Dec 9, 2015

Appl. No.:

14/964258

Inventors:

GEOFFREY W. MARKS - SANTA BARBARA CA, US
DAVID J. ROHWELLER - OJAI CA, US
CHRISTIAN J. PEDERSEN - VENTURA CA, US

Assignee:

NORTHROP GRUMMAN SYSTEMS CORPORATION - FALLS CHURCH VA

International Classification:

B64G 1/44
H02S 30/20
B64G 1/22

Abstract:

A solar panel assembly for a spacecraft includes a bracket and first and second booms each having a first end secured to the bracket and a second end extending away from the bracket. Each boom is formed from a plurality of tubes that telescope between a stowed condition nested within one another and a deployed condition aligned end-to-end with one another. A solar panel is secured to the first and second booms for receiving solar energy and converting the solar energy to electrical power. The solar panel has a stowed condition collapsed between the first and second booms and a deployed condition extending in a plane between the first and second booms.

US Patent:

20150194733, Jul 9, 2015

Filed:

Jan 9, 2014

Appl. No.:

14/151514

Inventors:

MEHRAN MOBREM - SANTA BARBARA CA, US
GEOFFREY W. MARKS - SANTA BARBARA CA, US

Assignee:

NORTHROP GRUMMAN SYSTEMS CORPORATION - FALLS CHURCH VA

International Classification:

H01Q 15/16
G02B 7/182
G02B 5/10

Abstract:

A reflector assembly includes a frame centered about a longitudinal axis and having a first height along the axis. A curved body extends from the frame and has a second height along the longitudinal axis could be greater than the first height. A stretchable membrane has an electromagnetically reflective surface and is secured to the curved body.