Patents Examined by Tim Dinh
  • Patent number: 6357672
    Abstract: Brush seals formed in hemispherical rings are supported to the end of the convergent nozzle of the each of the clam shells of a multi-axis vector thrust nozzle of a gas turbine engine powering aircraft. The brush seal may be arced or straight and bear against the spherical surface of the collar formed on the end of the tail pipe and is mounted so that high pressure forces the bristles against the backing plate of the seals.
    Type: Grant
    Filed: July 6, 1995
    Date of Patent: March 19, 2002
    Assignee: United Technologies Corporation
    Inventors: Curtis C. Cowan, George F. Leblanc
  • Patent number: 6315245
    Abstract: An ejection seat having a blast protection system comprising a blast screen stowed on the ejection seat and deployable to at least substantially envelop an occupant of the seat.
    Type: Grant
    Filed: April 4, 2000
    Date of Patent: November 13, 2001
    Assignee: Martin-Baker Aircraft Company, Limited
    Inventor: Stephen Anthony George Ruff
  • Patent number: 6293500
    Abstract: The present invention provides an improved integrated translation tube for the movement of equipment and personnel through space modules, particularly for non-rigid type space modules such as the NASA Transhab module. In addition, the present invention provides an internal framework for the structural support of the space module itself, and the equipment installed internally to the space module. The present invention's arched shaped translation tube provides sufficient strength and rigidity to provide the required structural support, while simultaneously maximizing the uninterrupted interior volume of the space module.
    Type: Grant
    Filed: April 14, 2000
    Date of Patent: September 25, 2001
    Assignee: Bigelow Development Aerospace Division, Limited Liability Company
    Inventor: Robert T. Bigelow
  • Patent number: 6250584
    Abstract: A locking mechanism for moveable control fins extending from the surface of a missile. The locking mechanism includes a pin extending thru the outer surface of the missile into an opening provided in the movable fin. A link is pivotally connected between each of the pins and a slide member disposed internally of the missile and carried by a guide. The links are in a close to dead center position when the pins are extended into the openings in each of the fins. Upon a command signal from a controller, preparatory to missile launch, a restraining device holding the slide is removed and a spring commences movement of the slide toward a position which will take the links past their dead center position upon which additional springs which are loaded around each of the pins are activated to positively move the slide and extract the pins from the openings in the fins.
    Type: Grant
    Filed: October 18, 1999
    Date of Patent: June 26, 2001
    Assignee: HR Textron, Inc.
    Inventors: William W. Hsu, Duncan D. Bragg