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.

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.

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.

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.

Abstract: A launch system for use as a standalone munition launcher or as a guest launcher within a main battery host launcher.

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.

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.

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.

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.

Abstract: A launch system for use as a standalone munition launcher or as a guest launcher within a main battery host launcher.

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.

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.

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.

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.