Hamilton Gail Wong

US Patent:

7252890, Aug 7, 2007

Filed:

Mar 1, 2004

Appl. No.:

10/790591

Inventors:

Hamilton Wong - Skillman NJ, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B32B 15/08
B32B 9/00

US Classification:

428626, 428458, 428699

Abstract:

A multi-layer insulation (MLI) blanket with enhanced contamination inhibiting properties and a method for inhibiting the formation of organic residues on the outer surface of a MLI blanket are provided. In one embodiment, a MLI blanket () attachable to a spacecraft or other structure includes a plurality of metallized layers () separated by mesh layers (). An anti-contamination coating () comprised of a photocatalytic material is disposed between a high emittance layer () that overlies the outer surface (A) of the outer metallized layer () and an outer electrically conductive layer (). When exposed to ultraviolet or near-ultraviolet radiation components present in solar radiation, the anti-contamination coating () catalyzes the breakdown of organic residues on the outer surface of the MLI blanket () thereby maintaining the reflective properties of the MLI blanket () and ensuring that solar absorptance of the MLI blanket () is maintained at or below an acceptable threshold level.

US Patent:

7270302, Sep 18, 2007

Filed:

Apr 22, 2004

Appl. No.:

10/829358

Inventors:

Hamilton Wong - Skillman NJ, US
Neil Goodzeit - Princeton NJ, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B64G 1/58

US Classification:

2441718

Abstract:

A spacecraft instrument thermal control method and system providing scalable thermal control of on-board instrument temperature. Adapted for a spacecraft with bus supporting instrumentation and thermal radiator panels, cooling is carried out by one or more active coolers, such as cryocoolers, each mounted to the spacecraft at a radiator spatially separated from the instrument, with cold side of the cooler being thermally coupled to an instrument focal plane or other instrument location requiring cryogenic cooling and the warm side coupled to the radiator. A closed loop temperature control system measures the temperature of the controlled portion of the instrument, and adjusts active cooler drive signals to maintain a specified set point temperature.

US Patent:

7691452, Apr 6, 2010

Filed:

May 17, 2007

Appl. No.:

11/750253

Inventors:

Hamilton Wong - Skillman NJ, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B05D 5/05
B05D 5/12
B05D 3/06

US Classification:

427553, 427162, 427404, 4274193, 4274192

Abstract:

A multi-layer insulation (MLI) blanket with enhanced contamination inhibiting properties and a method for inhibiting the formation of organic residues on the outer surface of a MLI blanket are provided. In one embodiment, a MLI blanket () attachable to a spacecraft or other structure includes a plurality of metallized layers () separated by mesh layers (). An anti-contamination coating () comprised of a photocatalytic material is disposed between a high emittance layer () that overlies the outer surface (A) of the outer metallized layer () and an outer electrically conductive layer (). When exposed to ultraviolet or near-ultraviolet radiation components present in solar radiation, the anti-contamination coating () catalyzes the breakdown of organic residues on the outer surface of the MLI blanket () thereby maintaining the reflective properties of the MLI blanket () and ensuring that solar absorptance of the MLI blanket () is maintained at or below an acceptable threshold level.

US Patent:

7967256, Jun 28, 2011

Filed:

May 8, 2007

Appl. No.:

11/797798

Inventors:

Hamilton Wong - Skillman NJ, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B64G 1/58

US Classification:

2441718

Abstract:

A spacecraft battery thermal management system is provided that includes a battery, a first radiator panel and a second radiator panel. A first face of the first radiator panel is arranged to face a first direction and a first face of the second radiator panel is arranged to face a second direction opposite the first direction. A first heat pipe thermally couples the battery and the first radiator panel and is configured to control the transfer of heat between the battery and the first radiator panel. A second heat pipe thermally couples the battery and the second radiator panel and is configured to control the transfer of heat between the battery and the second radiator panel. Solar cells are optionally arranged on the faces of the first and/or second radiator panels.

US Patent:

20130200220, Aug 8, 2013

Filed:

Feb 7, 2012

Appl. No.:

13/368304

Inventors:

Neil E. Goodzeit - Princeton NJ, US
Hamilton Wong - Yardley PA, US
David J. Hentosh - Yardley PA, US

Assignee:

LOCKHEED MARTIN CORPORATION - Bethesda MD

International Classification:

B64G 1/58

US Classification:

2441718

Abstract:

A deployable radiator arrangement for cooling a geostationary earth orbit spacecraft is provided. In some aspects, the geostationary earth orbit spacecraft may comprise first and second deployable radiators mounted on an east or west surface of the spacecraft when stowed. The first and second deployable radiators are configured to rotate into a north and south facing position, respectively, when deployed. The geostationary earth orbit spacecraft may further comprise first and second fixed radiators disposed on a north and south surface of the spacecraft, respectively. The first and second deployable radiators are thermally coupled to the first and second fixed radiators, respectively.

US Patent:

20130200221, Aug 8, 2013

Filed:

Feb 12, 2013

Appl. No.:

13/765626

Inventors:

Lockheed Martin Corporation - Bethesda MD, US
Hamilton Wong - Yardley PA, US
David J. Hentosh - Yardley PA, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B64G 1/58
B23P 15/26

US Classification:

2441718, 2989003

Abstract:

A geostationary earth orbit (GEO) spacecraft is disclosed that includes a body with north, east, south, and west sides and a north-south axis. The spacecraft has at least one deployable radiator rotatably coupled to the body. The deployable radiator has a stowed position proximate to one of the east and west sides and a deployed position that is greater than 90 degrees from the north-south axis in a direction away from the respective one of the east and west sides.

US Patent:

53733053, Dec 13, 1994

Filed:

Apr 22, 1993

Appl. No.:

8/051510

Inventors:

Albert Lepore - Upper Holland PA
Hamilton Wong - Pennington NJ
Susan L. Marr - Northampton Township, Bucks County PA
Leo J. Amore - Phoenixville PA

Assignee:

Martin Marietta Corporation - East Windsor NJ

International Classification:

H01Q 142
H01Q 128
H01Q 140

US Classification:

343872

Abstract:

An RF-transparent sunshield membrane covers an antenna reflector such as a parabolic dish. The membrane includes at least two dielectric sheets of polyimide film 1 mil thick. The surface of the outer film facing away from the reflector is coated with an electrically semiconductive coating such as vapor-deposited germanium having a thickness in the range of 200. ANG. to 600. ANG. A member, such as a glass fiber mat, may be located in the space between the two dielectric sheets for maintaining the sheets in spaced-apart relationship. In another embodiment of the invention, the surface of the film facing the reflector may be reinforced by an adhesively attached polyester or glass fiber mesh.