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.

A powered projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments a collar is rotatably mounted to a control support portion with a plurality of aerodynamic surfaces thereon for despinning the collar. An alternator configured as an axial flux machine with a stator arranged can be axially adjacent to one or more rotors, the stator including a plurality of windings and the one or more rotors each including a plurality of permanent magnets arranged about the face of the respective one or more rotor. In various embodiments the projectile includes an assembly of projectile control circuitry. In one or more embodiments, upon relative motion of the rotor with respect to the stator, magnetic flux from the magnets interacts with the windings of the stator and passes through an air gap between the one or more rotors and stator.

An arm-fire device comprises a capacitor charged by an arming signal; an acceleration switch for generating an operation signal if an acceleration more than a predetermined acceleration is sensed; a controller electrically connected with the capacitor and the acceleration switch, controlling generation of a firing signal; and a through bulkhead initiator provided with an ignition portion installed at a space separated by a bulkhead and configured to be electrically connected with the controller to ignite the ignition portion if the firing signal is transferred thereto, wherein the controller discharges the capacitor to generate the firing signal when the operation signal and a launching signal, which is applied from outside, are all sensed in a state that the capacitor is charged. The arm-fire device is applied to a multi-stage rocket, etc., whereby the probability of accidental ignition may be lowered.

An arm-fire device comprises a capacitor charged by an arming signal; an acceleration switch for generating an operation signal if an acceleration more than a predetermined acceleration is sensed; a controller electrically connected with the capacitor and the acceleration switch, controlling generation of a firing signal; and a through bulkhead initiator provided with an ignition portion installed at a space separated by a bulkhead and configured to be electrically connected with the controller to ignite the ignition portion if the firing signal is transferred thereto, wherein the controller discharges the capacitor to generate the firing signal when the operation signal and a launching signal, which is applied from outside, are all sensed in a state that the capacitor is charged. The arm-fire device is applied to a multi-stage rocket, etc., whereby the probability of accidental ignition may be lowered.

The munition employs an energetically initiated electromagnetic pulse through a coil which induces a voltage intended to be used for the operation of an electronic time delay circuit and subsequent ignition of a detonation device. Explosive energy from a primer is employed to move a generator core through a generator coil to induce the voltage. The voltage is supplied to a delay circuit. After a set time, the delay circuit supplies power to a laser igniter which detonates the munition. A striker assembly, in addition to initiating the primer, functions as an out of line safety as well as an electric safety.

The munition employs an energetically initiated electromagnetic pulse through a coil which induces a voltage intended to be used for the operation of an electronic time delay circuit and subsequent ignition of a detonation device. Explosive energy from a primer is employed to move a generator core through a generator coil to induce the voltage. The voltage is supplied to a delay circuit. After a set time, the delay circuit supplies power to a laser igniter which detonates the munition. A striker assembly, in addition to initiating the primer, functions as an out of line safety as well as an electric safety.

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 arm-fire device comprises a capacitor charged by an arming signal; an acceleration switch for generating an operation signal if an acceleration more than a predetermined acceleration is sensed; a controller electrically connected with the capacitor and the acceleration switch, controlling generation of a firing signal; and a through bulkhead initiator provided with an ignition portion installed at a space separated by a bulkhead and configured to be electrically connected with the controller to ignite the ignition portion if the firing signal is transferred thereto, wherein the controller discharges the capacitor to generate the firing signal when the operation signal and a launching signal, which is applied from outside, are all sensed in a state that the capacitor is charged. The arm-fire device is applied to a multi-stage rocket, etc., whereby the probability of accidental ignition may be lowered.