A launch container apparatus for ejection from a submerged launch platform and a method for ejecting a launch container apparatus are disclosed. The apparatus comprises an enclosure for carrying an unmanned aerial device and a surfacing sensor configured to generate a control signal in response to detection of surfacing of the launch container apparatus. Petals are configured to provide buoyancy and stabilization for the launch container apparatus are also provided. A petal drive mechanism moves, in response to the control signal, the petals from a folded position to an expanded position.

A rocket extraction device and method is disclosed. In one embodiment, the device comprises an upper and a lower casing; an interior cutout in each of the upper and lower casings, the interior cutouts having contours matching exterior surface contours of a rocket fuze; an upper fuze clamp and a lower fuze clamp disposed respectively within the upper and lower casings, each upper and lower fuze clamp having interior surface contours matching exterior surface contours of the rocket fuze; a clamp adjustment screw onto which the upper fuze clamp is mountable; an adjustment wheel mountable at the exterior end of the clamp adjustment screw by which the clamp adjustment screw and the upper fuse clamp are movable to secure the upper and lower fuze clamps to the fuze and force the fuze into the contours of the lower fuze clamp and the interior cutout of the lower casing to lock the fuze into the rocket extraction device. There is an eyebolt or similar type device mountable to the exterior of the rocket extraction device, to which force is applied to remove a rocket from a storage tube. In another embodiment, the method comprises attaching the rocket extraction device securely to a fuze on a rocket and pulling on the rocket extraction device to remove the rocket from a storage tube.

An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate.

An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate.

A method of executing a mission for at least one mobile munition assembly in a mission environment is provided, the at least one mobile munition assembly having a container that encloses one or more launchers configured to receive and launch a munition. One or more electronic devices in communicatively coupling with one another in the mission environment form a secure network. A status of a situational awareness (SA) corresponding to each of the one or more electronic devices in the mission environment is transmitted. An input of parameters of the mission for the at least one mobile munition assembly is enabled, the parameters having one or more predefined rules associated therewith and configured to be applied to the parameters based on at least the status of the situational awareness (SA). An authorization or a denial of the mission for the at least one mobile munition assembly is requested.

Heavy inert gas insulation layer(s) are provided for containers configured to contain components that include an energetic material. The heavy inert gas insulation layer delays desensitization or inhibits premature reaction of the energetic material due to high external temperatures. The layers may be formed in hollow walls of the container itself or as inserts that are attached to the container. An inert gas fills a sealed void space in the walls or the insert. The inert gas has a density of at least 1.5 Kg/m.sup.3 and a thermal conductivity (Tcond_gas) of no greater than two-thirds of a thermal conductivity of air (Tcond_air) to form the heavy inert gas insulation layer. The inert gas may be Argon, Krypton, Xenon or a synthetic gas and is suitably held at a pressure of 760 Torr (1 atmosphere) or greater at sea level.

In one embodiment, a method of automated missile launcher reloading includes aligning one or more collars of a shelving system with a path of a canister and activating one or more rollers of the shelving system to translate the canister into the one or more collars. The method also includes coupling a first collar of the one or more collars to the canister and adjusting the one or more collars to align the canister with a path of a launcher cell. The method further includes translating the one or more collars into the path of the launcher cell to feed the canister into the launcher cell.

A deployment apparatus comprising a deployment mechanism and a deployable module, wherein the deployable module is moveable between a stowed position within a housing and a deployed position at least partially outside the housing, wherein the deployment mechanism comprises independent lift and tilt arrangements, wherein the lift arrangement controls the elevation of the deployable module relative to the housing and the tilt arrangement controls the relative tilt angle of the deployable module relative to the housing.

A deployment apparatus comprising a deployment mechanism and a deployable module, wherein the deployable module is moveable between a stowed position within a housing and a deployed position at least partially outside the housing, wherein the deployment mechanism comprises independent lift and tilt arrangements, wherein the lift arrangement controls the elevation of the deployable module relative to the housing and the tilt arrangement controls the relative tilt angle of the deployable module relative to the housing.