Patents by Inventor Hamilton Wong

Hamilton Wong has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 9889951
    Abstract: A heat transfer assembly (HTA) includes an equipment panel having a first longitudinal length and a first radiator panel that is coupled to one of an east end and a west end of the equipment panel. The first radiator panel is longer in the longitudinal direction than the equipment panel and has least one longitudinal heat pipe. The HTA also includes at least one flexible heat pipe having a first rigid tube coupled to the equipment panel, a second rigid tube thermally coupled to the first longitudinal heat pipe, and a flexible tube coupled between the first and second rigid tubes. The equipment panel is configured to retain an equipment module in thermal contact with the first rigid tube.
    Type: Grant
    Filed: June 7, 2013
    Date of Patent: February 13, 2018
    Assignee: Lockheed Martin Corporation
    Inventors: Hamilton Wong, Rok Park Buckley
  • Patent number: 9352855
    Abstract: A system and apparatus are provided for preventing heat loss in a spacecraft during the upper stage launch phase and transfer orbit. A thermal control panel can be provided that can be positioned adjacent to exposed areas of radiator panels on the spacecraft in a collapsed configuration. The outer surface of the panel can have a high absorptivity, and the inner surface can have a high emissivity. During upper stage launch phase and transfer orbit, the panel can tend to emit heat toward the radiator panels on an inboard side of the spacecraft, thus reducing heat loss from the radiator panels to reduce the need for onboard electronic heaters and thereby preserve battery power for other onboard systems.
    Type: Grant
    Filed: March 4, 2014
    Date of Patent: May 31, 2016
    Assignee: Lockheed Martin Corporation
    Inventor: Hamilton Wong
  • Patent number: 8967547
    Abstract: A heat transfer assembly can include an equipment panel having an east end and a west end. East and west radiator panels are coupled to the east and west ends, respectively, of the equipment panel. The assembly also includes a plurality of flexible heat pipes each having a first rigid tube thermally coupled to the east radiator panel, a second rigid tube coupled to the equipment panel, a third rigid tube thermally coupled to the west radiator panel, a first flexible tube sealingly coupled between the first and second rigid tubes, and a second flexible tube sealingly coupled between the second and third rigid tubes. The equipment panel is configured to retain one or more equipment modules in thermal contact with the second rigid tube of at least one of the plurality of flexible heat pipes.
    Type: Grant
    Filed: February 12, 2013
    Date of Patent: March 3, 2015
    Assignee: Lockheed Martin Corporation
    Inventors: Hamilton Wong, Neil E. Goodzeit, Rok Park Buckley, David J. Hentosh
  • Patent number: 8960608
    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.
    Type: Grant
    Filed: February 12, 2013
    Date of Patent: February 24, 2015
    Assignee: Lockheed Martin Corporation
    Inventors: Neil E. Goodzeit, Hamilton Wong, David J. Hentosh
  • Publication number: 20140299714
    Abstract: A system and apparatus are provided for preventing heat loss in a spacecraft during the upper stage launch phase and transfer orbit. A thermal control panel can be provided that can be positioned adjacent to exposed areas of radiator panels on the spacecraft in a collapsed configuration. The outer surface of the panel can have a high absorptivity, and the inner surface can have a high emissivity. During upper stage launch phase and transfer orbit, the panel can tend to emit heat toward the radiator panels on an inboard side of the spacecraft, thus reducing heat loss from the radiator panels to reduce the need for onboard electronic heaters and thereby preserve battery power for other onboard systems.
    Type: Application
    Filed: March 4, 2014
    Publication date: October 9, 2014
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventor: Hamilton WONG
  • Patent number: 8714492
    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.
    Type: Grant
    Filed: February 7, 2012
    Date of Patent: May 6, 2014
    Assignee: Lockheed Martin Corporation
    Inventors: Neil E. Goodzeit, Hamilton Wong, David J. Hentosh
  • Publication number: 20130200220
    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.
    Type: Application
    Filed: February 7, 2012
    Publication date: August 8, 2013
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventors: Neil E. Goodzeit, Hamilton Wong, David J. Hentosh
  • Patent number: 7967256
    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.
    Type: Grant
    Filed: May 8, 2007
    Date of Patent: June 28, 2011
    Assignee: Lockheed Martin Corporation
    Inventor: Hamilton Wong
  • Patent number: 7691452
    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 (10) attachable to a spacecraft or other structure includes a plurality of metallized layers (20, 30, 40, 50) separated by mesh layers (60, 62, 64). An anti-contamination coating (80) comprised of a photocatalytic material is disposed between a high emittance layer (70) that overlies the outer surface (20A) of the outer metallized layer (20) and an outer electrically conductive layer (90).
    Type: Grant
    Filed: May 17, 2007
    Date of Patent: April 6, 2010
    Assignee: Lockheed Martin Corporation
    Inventor: Hamilton Wong
  • Publication number: 20080277532
    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.
    Type: Application
    Filed: May 8, 2007
    Publication date: November 13, 2008
    Applicant: Lockheed Martin Corporation
    Inventor: Hamilton Wong
  • Patent number: 7270302
    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.
    Type: Grant
    Filed: April 22, 2004
    Date of Patent: September 18, 2007
    Assignee: Lockheed Martin Corporation
    Inventors: Hamilton Wong, Neil Goodzeit
  • Patent number: 7252890
    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 (10) attachable to a spacecraft or other structure includes a plurality of metallized layers (20, 30, 40, 50) separated by mesh layers (60, 62, 64). An anti-contamination coating (80) comprised of a photocatalytic material is disposed between a high emittance layer (70) that overlies the outer surface (20A) of the outer metallized layer (20) and an outer electrically conductive layer (90).
    Type: Grant
    Filed: March 1, 2004
    Date of Patent: August 7, 2007
    Assignee: Lockheed Martin Corporation
    Inventor: Hamilton Wong
  • Patent number: 5373305
    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.
    Type: Grant
    Filed: April 22, 1993
    Date of Patent: December 13, 1994
    Assignee: Martin Marietta Corporation
    Inventors: Albert Lepore, Jr., Hamilton Wong, Susan L. Marr, Leo J. Amore