An attachment arrangement for a gun module of a carrier, such as a vehicle, a craft, or a structure fixedly mounted on a foundation, including, fixedly mounted on the carrier, a carrier frame. The carrier frame has at least two elongated frame portions, and the attachment arrangement includes an intermediate beam, on which the gun module is arranged. A subframe is arranged on the carrier frame, and a pair of interacting mounting plates are arranged on the subframe and the intermediate beam respectively. A weapons system includes an attachment arrangement and a superstructure module having storage spaces on top of the subframe.

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 method and apparatus for an unmanned aerial system is described herein. An unmanned aerial system capable of being launched from a grenade launcher includes a tubular body that encloses a compartment for a payload and a battery, a motor coupled to the tubular body, a propeller coupled to the motor, and a parachute disposed within the tubular body when the unmanned aerial system is in a stowed configuration and disposed outside of the tubular body when the unmanned aerial system is in a powered flight configuration.

A method and apparatus for an unmanned aerial system is described herein. An unmanned aerial system capable of being launched from a grenade launcher includes a tubular body that encloses a compartment for a payload and a battery, a motor coupled to the tubular body, a propeller coupled to the motor, and a parachute disposed within the tubular body when the unmanned aerial system is in a stowed configuration and disposed outside of the tubular body when the unmanned aerial system is in a powered flight configuration.

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, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

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, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

A firefighting aircraft with a body and wings comprises a firing means configured to fire at least one fire suppression container provided in the body. The at least one fire suppression container has a casing filled with a fire extinguishing material and formed of a material destroyed by an impact. The first extinguishing material includes at least one of a fire extinguishing liquid, a fire extinguishing powder, or a fire extinguishing foam.

A firefighting aircraft with a body and wings comprises a firing means configured to fire at least one fire suppression container provided in the body. The at least one fire suppression container has a casing filled with a fire extinguishing material and formed of a material destroyed by an impact. The first extinguishing material includes at least one of a fire extinguishing liquid, a fire extinguishing powder, or a fire extinguishing foam.

A grenade launcher apparatus having an integral fire control system includes a receiver having a fore end portion, a pivotally attached to the fore end portion, the barrel having a muzzle end and a breech end. A trigger assembly is coupled to the receiver adjacent the breech end of the barrel and a hand grip is attached to the receiver adjacent the trigger assembly. A buttstock assembly is coupled to the receiver and a fire control system secured to the fore end portion of the receiver. In another aspect, a fire control system is provided. In yet another aspect, a method aiming a grenade launcher apparatus is provided.