The present invention relates to firearms. In some cases, the firearms include a firing pin; a first ignition chamber that is configured to house a round of ammunition and to move proximally with respect to the firing pin so that when the round is in the first chamber and the firearm is fired, a portion of the round is struck against the firing pin. In some cases, the firearms also include a follower configured to be movable proximally and distally within the firearm and to be biased against a primer or proximal end of the round such that the follower is configured to selectively hold the round within the first chamber as the first chamber moves proximally, and such that proximal movement of the follower stops when the round strikes the firing pin, so that the follower acts as a bolt face for the round. Other implementations are also described.

The present invention relates to firearms. In some cases, the firearms include a firing pin; a first ignition chamber that is configured to house a round of ammunition and to move proximally with respect to the firing pin so that when the round is in the first chamber and the firearm is fired, a portion of the round is struck against the firing pin. In some cases, the firearms also include a follower configured to be movable proximally and distally within the firearm and to be biased against a primer or proximal end of the round such that the follower is configured to selectively hold the round within the first chamber as the first chamber moves proximally, and such that proximal movement of the follower stops when the round strikes the firing pin, so that the follower acts as a bolt face for the round. Other implementations are also described.

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 a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

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 a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

A collapsible, rapidly-deployable unmanned aerial vehicle includes a cylindrical structural body, a plurality of deployable mechanisms, a control unit, and a portable power source. The cylindrical structural body is dimensioned to be stored in a small space and deployed rapidly. The plurality of deployable mechanisms includes a lift-generating device for generating an upward thrust that allows the unmanned aerial vehicle to fly. Further, the plurality of deployable mechanisms can collapse to reduce the overall footprint of the cylindrical structural body, thereby allowing the unmanned aerial vehicle to be stored in a confined area. The control unit is integrated into the cylindrical structural body, whereby the control unit controls the flight of the present invention. The portable power source provides electrical energy to the electrically operated components of the unmanned aerial vehicle such as the plurality of deployable mechanisms and the control unit.

Described embodiments include an electro-shock projectile launcher, a method, and a system. An electro-shock projectile launcher includes a deployment tube configured to launch an electro-shock projectile toward a target human. The launcher includes a recognition circuit configured to recognize a body portion of the target human authorized for administration of a selected electric shock by electro-shock projectiles. The launcher includes a guidance circuit configured to determine a flight path of the electro-shock projectile from the deployment tube to the recognized body portion of the target human. The launcher includes an activator circuit configured to initiate a launch from the deployment tube of the electro-shock projectile along the determined flight path in response a received authorization.

Described embodiments include an electro-shock projectile launcher, a method, and a system. An electro-shock projectile launcher includes a deployment tube configured to launch an electro-shock projectile toward a target human. The launcher includes a recognition circuit configured to recognize a body portion of the target human authorized for administration of a selected electric shock by electro-shock projectiles. The launcher includes a guidance circuit configured to determine a flight path of the electro-shock projectile from the deployment tube to the recognized body portion of the target human. The launcher includes an activator circuit configured to initiate a launch from the deployment tube of the electro-shock projectile along the determined flight path in response a received authorization.

Described embodiments include an electro-shock projectile launcher, a method, and a system. An electro-shock projectile launcher includes a deployment tube configured to launch an electro-shock projectile toward a target human. The launcher includes a recognition circuit configured to recognize a body portion of the target human authorized for administration of a selected electric shock by electro-shock projectiles. The launcher includes a guidance circuit configured to determine a flight path of the electro-shock projectile from the deployment tube to the recognized body portion of the target human. The launcher includes an activator circuit configured to initiate a launch from the deployment tube of the electro-shock projectile along the determined flight path in response a received authorization.

Described embodiments include an electro-shock projectile launcher, a method, and a system. An electro-shock projectile launcher includes a deployment tube configured to launch an electro-shock projectile toward a target human. The launcher includes a recognition circuit configured to recognize a body portion of the target human authorized for administration of a selected electric shock by electro-shock projectiles. The launcher includes a guidance circuit configured to determine a flight path of the electro-shock projectile from the deployment tube to the recognized body portion of the target human. The launcher includes an activator circuit configured to initiate a launch from the deployment tube of the electro-shock projectile along the determined flight path in response a received authorization.

A delinking feeder of a minigun includes an access door mounted to a delinking feeder housing and movable between a closed position and an open position. The access door has an enclosed recess for receiving a tongue that is rotationally coupled to the access door and is movable between a retracted position and a deployed position. When the access door is in the open position, the tongue is in the deployed position and a tongue first contact surface can contact and secure a linked cartridge positioned in the delinking feeder. When the access door is in the closed position, the tongue is in the retracted position and a tongue second contact surface can contact and guide a cartridge positioned in the delinking feeder. The enclosed recess is covered so that when the access door is in the closed position, the tongue does not protrude through the access door.