An effector launching system includes an environment that has external components located within the environment. The effector launching system may include a modular controller located in the environment of an effector launching system and the external components may be located in the environment externally to the modular controller for executing an effector launching sequence. The modular controller may include a core processor module that is configured to execute a plurality of different effector launching sequences using the external components and a plurality of converting modules that each have an electro-mechanical interface and is connectable between the core processor module and one of the external components. The plurality of converting modules are configured to send and receive data with the core processor module and the plurality of external components.

A launcher for launching a projectile includes a launch piston for engaging and driving the projectile from the launcher and a launch brake that constrains the piston to enable separation of the piston from the projectile. The launch brake is configured to have minimal to no effect on projectile exit velocity and exit trajectory from the launcher. The launch brake is also configured to reduce the velocity of the launch piston via coupling of the masses of the launch piston and the launch brake. The coupling allows, separation of the projectile from the launch piston and reduces or prevents a negative effect on stabilization of the projectile upon exit from the launcher.

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

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

An effector launching system includes an environment that has external components located within the environment. The effector launching system may include a modular controller located in the environment of an effector launching system and the external components may be located in the environment externally to the modular controller for executing an effector launching sequence. The modular controller may include a core processor module that is configured to execute a plurality of different effector launching sequences using the external components and a plurality of converting modules that each have an electro-mechanical interface and is connectable between the core processor module and one of the external components. The plurality of converting modules are configured to send and receive data with the core processor module and the plurality of external components.

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.

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 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).

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.