Patents by Inventor John Snediker

John Snediker 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: 8851786
    Abstract: A reversible sealing mechanism for sealing a bulkhead having a first central aperture defined along a central axis and disposed between first and second compartments includes a cover member having a recess defined therein by a substantially cylindrical sidewall and adapted to cover the first central aperture. A wedge ring having a generally cylindrical body is accommodated by the first and second central apertures and is configured to operatively engage the cover member. A mechanical input is operative to reversibly rotate the wedge ring about the central axis such that a rotation of the wedge ring in a first direction urges the cover member in the axial direction into a sealed position.
    Type: Grant
    Filed: December 1, 2009
    Date of Patent: October 7, 2014
    Assignee: Lockhead Martin Corporation
    Inventors: John Snediker, Daniel Skurdal
  • Patent number: 8534177
    Abstract: A system and method for providing a munitions launching system with dynamic shock isolation in which a spring plate skirt having an integral spring arrangement is provided between a munitions frame and a munitions extension, the spring plate skirt defining an opening that provides for the uninterrupted flow of expelled rocket gases, as well as underside access to the munitions frame.
    Type: Grant
    Filed: March 1, 2010
    Date of Patent: September 17, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: William Kalms, Tejbir Arora, John Snediker
  • Patent number: 8468924
    Abstract: A system and method for launching non-vertical launch munitions with a non-vertical launch trajectory from a launcher that is operationally coupled to a vertical launching system (VLS). The inventors of the present invention recognized that munitions that are unsuitable for vertical launches were unavailable for use with vertical launching systems, thus foreclosing important defense, attack, and cost-savings opportunities for VLS-equipped platforms. A VLS could be substantially more versatile if it accommodated munitions such as torpedoes, counter-measures, direct-fire munitions, point-and-shoot munitions, and a variety of other missiles and equipment. The launcher according to the present invention is also stowable in an upward orientation within a cell of the host vertical launching system.
    Type: Grant
    Filed: December 16, 2010
    Date of Patent: June 25, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: Daniel A. Skurdal, John Snediker, William Kalms
  • Patent number: 8443707
    Abstract: An apparatus is disclosed that is a self-contained gas management system (hereinafter “GMS”) that accommodates individual canisters of highly energetic small munitions, but is not so limited. By decoupling the gas management system for a given munition from an adjacent munition, the risk of downing a multi-pack launcher or munition adapter is reduced. Thermal wear, overheating, restrained firing and aft closure debris can be isolated through the separation of gas management systems. In addition, the GMS allows for ease of replenishment and maintenance of a given sub-cell of a multi-pack system. The GMS works with existing munitions and canisters without the need to modify them. Each GMS is dimensioned to fit the canistered munition it receives as well as the launch system with which it is used. The illustrative GMS comprises a plenum, and a first and a second uptake structure. The plenum receives the exhaust from the canistered munition when the munition fires.
    Type: Grant
    Filed: August 24, 2010
    Date of Patent: May 21, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: Daniel A. Skurdal, John Snediker
  • Patent number: 8397613
    Abstract: A launch system for use as a standalone munition launcher or as a guest launcher within a main battery host launcher.
    Type: Grant
    Filed: November 20, 2008
    Date of Patent: March 19, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: Daniel A. Skurdal, Timothy R. Fouts, Jennifer L. Houston-Manchester, John Snediker
  • Publication number: 20120152090
    Abstract: An apparatus is disclosed that is a self-contained gas management system (hereinafter “GMS”) that accommodates individual canisters of highly energetic small munitions, but is not so limited. By decoupling the gas management system for a given munition from an adjacent munition, the risk of downing a multi-pack launcher or munition adapter is reduced. Thermal wear, overheating, restrained firing and aft closure debris can be isolated through the separation of gas management systems. In addition, the GMS allows for ease of replenishment and maintenance of a given sub-cell of a multi-pack system. The GMS works with existing munitions and canisters without the need to modify them. Each GMS is dimensioned to fit the canistered munition it receives as well as the launch system with which it is used. The illustrative GMS comprises a plenum, and a first and a second uptake structure. The plenum receives the exhaust from the canistered munition when the munition fires.
    Type: Application
    Filed: August 24, 2010
    Publication date: June 21, 2012
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventors: Daniel A. Skurdal, John Snediker
  • Publication number: 20120152092
    Abstract: A system and method for launching non-vertical launch munitions with a non-vertical launch trajectory from a launcher that is operationally coupled to a vertical launching system (VLS). The inventors of the present invention recognized that munitions that are unsuitable for vertical launches were unavailable for use with vertical launching systems, thus foreclosing important defense, attack, and cost-savings opportunities for VLS-equipped platforms. A VLS could be substantially more versatile if it accommodated munitions such as torpedoes, counter-measures, direct-fire munitions, point-and-shoot munitions, and a variety of other missiles and equipment. The launcher according to the present invention is also stowable in an upward orientation within a cell of the host vertical launching system.
    Type: Application
    Filed: December 16, 2010
    Publication date: June 21, 2012
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventors: Daniel A. Skurdal, John Snediker, William Kalms
  • Publication number: 20120104219
    Abstract: A system and method for providing a munitions launching system with dynamic shock isolation in which a spring plate skirt having an integral spring arrangement is provided between a munitions frame and a munitions extension, the spring plate skirt defining an opening that provides for the uninterrupted flow of expelled rocket gases, as well as underside access to the munitions frame.
    Type: Application
    Filed: March 1, 2010
    Publication date: May 3, 2012
    Applicant: Lockheed Martin Corpration
    Inventors: William Kalms, Tejbir Arora, John Snediker
  • Publication number: 20110126474
    Abstract: A reversible sealing mechanism for sealing a bulkhead having a first central aperture defined along a central axis and disposed between first and second compartments includes a cover member having a recess defined therein by a substantially cylindrical sidewall and adapted to cover the first central aperture. A wedge ring having a generally cylindrical body is accommodated by the first and second central apertures and is configured to operatively engage the cover member. A mechanical input is operative to reversibly rotate the wedge ring about the central axis such that a rotation of the wedge ring in a first direction urges the cover member in the axial direction into a sealed position.
    Type: Application
    Filed: December 1, 2009
    Publication date: June 2, 2011
    Applicant: Lockheed Martin Corpration
    Inventors: John Snediker, Daniel Skurdal
  • Publication number: 20090126556
    Abstract: A launch system for use as a standalone munition launcher or as a guest launcher within a main battery host launcher.
    Type: Application
    Filed: November 20, 2008
    Publication date: May 21, 2009
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventors: Daniel A. Skurdal, Timothy R. Fouts, Jennifer L. Houston-Manchester, John Snediker
  • Patent number: 7510145
    Abstract: A UAV recovery system is disclosed. In the illustrative embodiment for UAV recovery over water, the system includes ship-based elements and UAV-based elements. The UAV-based elements include a mass, such as ball, that is coupled to cord, which is in turn coupled to the tail of a UAV. The ship-based elements include a capture plate and a boom, wherein the boom is pivotably coupled to the deck of a ship. For use in recovery operations, the boom is rotated so that it extends over the side of the ship. A UAV is flown over the boom toward the capture plate at an altitude such that the mass that is attached to the tail of the UAV hangs lower than the capture plate. With continued forward motion, the cord that hangs from the UAV is captured by a grooves in the capture plate. The capture plate geometrically constrains the mass, thereby assuring positive capture of the UAV.
    Type: Grant
    Filed: January 6, 2006
    Date of Patent: March 31, 2009
    Assignee: Lockheed Martin Corporation
    Inventor: John Snediker
  • Publication number: 20070158498
    Abstract: A UAV recovery system is disclosed. In the illustrative embodiment for UAV recovery over water, the system includes ship-based elements and UAV-based elements. The UAV-based elements include a mass, such as ball, that is coupled to cord, which is in turn coupled to the tail of a UAV. The ship-based elements include a capture plate and a boom, wherein the boom is pivotably coupled to the deck of a ship. For use in recovery operations, the boom is rotated so that it extends over the side of the ship. A UAV is flown over the boom toward the capture plate at an altitude such that the mass that is attached to the tail of the UAV hangs lower than the capture plate. With continued forward motion, the cord that hangs from the UAV is captured by a grooves in the capture plate. The capture plate geometrically constrains the mass, thereby assuring positive capture of the UAV.
    Type: Application
    Filed: January 6, 2006
    Publication date: July 12, 2007
    Applicant: Lockheed Martin Corporation
    Inventor: John Snediker
  • Patent number: 7143976
    Abstract: A UAV arresting hook is disclosed. The arresting hook facilitates the capture of a UAV via a UAV recovery system. In the illustrative embodiment, the arresting hook has a rotation block, an arm, and a plurality of latches that are disposed on the arm. The arm is coupled to the UAV via the rotation block, which provides two rotational degrees of freedom to the arm. In a stowed position, the arm is flush against the surface of the UAV. To deploy the arm, a free end of the arm is rotated away from the surface of the UAV. The arm is additionally biased to rotate about its longitudinal axis as it rotates away from the surface of the UAV. This rotation positions the latches to capture an arresting line that is part of a UAV recovery system.
    Type: Grant
    Filed: February 4, 2005
    Date of Patent: December 5, 2006
    Assignee: Lockheed Martin Corp.
    Inventors: John Snediker, Michael A. Watts, Grant W. Corboy
  • Publication number: 20060175466
    Abstract: A UAV arresting hook is disclosed. The arresting hook facilitates the capture of a UAV via a UAV recovery system. In the illustrative embodiment, the arresting hook has a rotation block, an arm, and a plurality of latches that are disposed on the arm. The arm is coupled to the UAV via the rotation block, which provides two rotational degrees of freedom to the arm. In a stowed position, the arm is flush against the surface of the UAV. To deploy the arm, a free end of the arm is rotated away from the surface of the UAV. The arm is additionally biased to rotate about its longitudinal axis as it rotates away from the surface of the UAV. This rotation positions the latches to capture an arresting line that is part of a UAV recovery system.
    Type: Application
    Filed: February 4, 2005
    Publication date: August 10, 2006
    Applicant: Lockheed Martin Corporation
    Inventors: John Snediker, Michael Watts, Grant Corboy