An unmanned aerial vehicle (UAV) launch tube (100) that comprises at least one inner layer of prepreg substrate (370) disposed about a right parallelepiped aperture (305), at least one outer layer of prepreg substrate (380) disposed about the right parallelepiped aperture, and one or more structural panels (341-344) disposed between the at least one inner layer of prepreg substrate (340) and the at least one outer layer of prepreg substrate (380). An unmanned aerial vehicle (UAV) launch tube (100) that comprises a tethered sabot (700,740) configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot (700,740) dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot (700,740) is hollow having an open end oriented toward a high pressure volume and a tether (740) attached within a hollow (910) of the sabot (700) and attached to the inner wall retaining the high pressure volume or attach to the inner base wall (1013). A system comprising a communication node (1500-1505) and a launcher (1520) comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node (1500-1505).

A deployable, linear explosive structure includes a split tube, an explosive coupled to the split tube, and a fragmentable or non-fragmentable projectile disposed with respect to the explosive. The split tube can be rolled into a non-deployed state in which the split tube has a flat, rolled profile. The split tube also can be deployed from the non-deployed state to a deployed state in which the split tube is extended along its length and has a curved cross-section along its length. The split tube provides support of the explosive structure in the deployed state. The split tube also provides smaller storage and transportation volume for the explosive structure when rolled in the non-deployed state.

A deployable, linear explosive structure includes a split tube, an explosive coupled to the split tube, and a fragmentable or non-fragmentable projectile disposed with respect to the explosive. The split tube can be rolled into a non-deployed state in which the split tube has a flat, rolled profile. The split tube also can be deployed from the non-deployed state to a deployed state in which the split tube is extended along its length and has a curved cross-section along its length. The split tube provides support of the explosive structure in the deployed state. The split tube also provides smaller storage and transportation volume for the explosive structure when rolled in the non-deployed state.

A firearm sound suppressor having a one-piece monocore. The monocore comprises a mainframe and a central channel therein which is connected to the mainframe by support arms which form support chambers. The central channel has a circular central bore, through which a projectile passes, and a rectangular external shape with four sides with openings thereon, wherein each side rotates 60 to 120 degrees around the longitudinal axis of the central bore, forming a helical twist in the central channel. The support chambers are attached to connecting members at the circumference of the mainframe. The support chambers and connecting members form the same helical configuration as the central channel, producing a helical flow of propellant gases, coming out of the openings, from the rear end to the front end of the central channel. Compressed propellant gases are prevented from entering the central chamber in front of the projectile. This design improves sound suppression and accuracy of the firearm.

Movement of a disrupter cannon is arrested by a parachute. The parachute is coupled (e.g., tethered) to the disrupter cannon. Prior to firing the cannon, the parachute is held in a retainer. Movement of the disrupter cannon in response to firing pulls the parachute from the retainer. The parachute deploys and arrests the movement of the disrupter cannon. The retainer protects the parachute prior to firing the disrupter cannon. The retainer may hold the parachute during transport.

Movement of a disrupter cannon is arrested by a parachute. The parachute is coupled (e.g., tethered) to the disrupter cannon. Prior to firing the cannon, the parachute is held in a retainer. Movement of the disrupter cannon in response to firing pulls the parachute from the retainer. The parachute deploys and arrests the movement of the disrupter cannon. The retainer protects the parachute prior to firing the disrupter cannon. The retainer may hold the parachute during transport.

This disclosure relates to self-contained cartridges and launcher systems for discharging or launching payloads to downrange targets, and methods of attenuating or offsetting recoil when activating such cartridges. Examples of payloads that can be deployed with the disclosed launcher apparatus include chemical, biological, pyrotechnic, marker, tracer, signaling, non-lethal, explosive, smoke, and similar payloads.

This disclosure relates to self-contained cartridges and launcher systems for discharging or launching payloads to downrange targets, and methods of attenuating or offsetting recoil when activating such cartridges. Examples of payloads that can be deployed with the disclosed launcher apparatus include chemical, biological, pyrotechnic, marker, tracer, signaling, non-lethal, explosive, smoke, and similar payloads.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.