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.

An explosive device composed of: a flux compression generator operative to produce a high intensity electric current when activated; and an electrical payload connected to the generator and constructed to receive the high intensity electric current and cause energy in the current to generate a plate or shaped projectile in the payload and to launch the projectiles into an explosive or insensitive reactive material target for the purpose of initiating the reactive material at single or multiple points.

An explosive device composed of: a flux compression generator operative to produce a high intensity electric current when activated; and an electrical payload connected to the generator and constructed to receive the high intensity electric current and cause energy in the current to generate a plate or shaped projectile in the payload and to launch the projectiles into an explosive or insensitive reactive material target for the purpose of initiating the reactive material at single or multiple points.

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.

There is a firing and arming system, such as an activation system, of a munition for quickly and accurately activating a warhead or a propulsion system of the activation system. An initiator interface of the activation system activates the warhead or propulsion system. At least one power source is included in the activation system to provide the initial power for activation of the initiator interface and subsequent activating of the respective warhead or propulsion system. Logic elements are communicatively disposed between the at least one power source and a flux compression generator circuit to control activation of the generator. The flux compression generator circuit is at least partially detonated to transform current received from the at least one power source into sufficient current for activating the initiator interface.

There is a firing and arming system, such as an activation system, of a munition for quickly and accurately activating a warhead or a propulsion system of the activation system. An initiator interface of the activation system activates the warhead or propulsion system. At least one power source is included in the activation system to provide the initial power for activation of the initiator interface and subsequent activating of the respective warhead or propulsion system. Logic elements are communicatively disposed between the at least one power source and a flux compression generator circuit to control activation of the generator. The flux compression generator circuit is at least partially detonated to transform current received from the at least one power source into sufficient current for activating the initiator interface.

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 detonator assembly which includes a holder, a flexible elongate element which is engaged with the holder, a detonator connected to the element, an energy storage device on the holder and a coil arrangement for charging the energy storage device when the coil arrangement is coupled to a variable electromagnetic field.

An electronic time warhead (EOT) fuze for a hand grenade comprises a body housing a clamp with two terminals maintaining a spring and a handle in the armed position. The handle holds the spring in the armed position while the user wields the grenade. The spring is housed in a spring pin and this initializes the EOT. When throwing the grenade, the spring seeks a resting position, expelling the handle and activating a switch that energizes an electronic circuit. A battery is electrically connected to the electronic circuit. In addition, an initiator element is mounted on the body and the initiator element consists of a conductive filament impregnated with a chemical mixture generating a flame from the electrical signal applied by the electronic circuit. The initiating element can be an electrical or electronic component. The electronic circuit accounts for a delay time until the grenade's initiating flame is effectively activated. In some embodiments, the electronic circuit is a microprocessor circuit that applies the electrical signal to the conductive filament at the end of the delay time, activating the grenade.