A fuze setter interface for substantially simultaneously and wirelessly transferring power and data between a fuze setter and fuze. The fuze setter interface includes separate power and communications interfaces. In the power interface, an induction coil is provided in each of the fuze setter and fuze. Power is transferred by magnetic field coupling between the induction coils. In the communications interface, a communications member is provided in each of the fuze setter and fuze, along with appropriate functions to generate alternating-current (AC) waveforms, and condition, modulate or demodulate signals. In one example, both communications members are induction coils that transfer data by magnetic field coupling. In another example, both communications members are radio-frequency (RF) transceivers that transfer data by radio signal. The RF transceiver in the fuze may be a Height of Burst (HoB) sensor. In another example, both communications members are optical transceivers that transfer data by optical signal.

A bullet projectile is described with an internal magnetic hammer providing electromagnetic induction upon impact.

A bullet projectile is described with an internal magnetic hammer providing electromagnetic induction upon impact.

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 capacitive discharge unit (CDU) for detonating an explosive in response to a control signal comprises a set of CDU components, including an exploding foil initiator (EFI), a trigger circuit, a firing capacitor, and an insulated-gate bipolar transistor (IGBT) firing switch. In various embodiments the components are arranged on a board for mechanically and electrically supporting the components in an ordered arrangement along a CDU axis where the CDU having an axial length defined by the ordered arrangement of two or more of the EFI, the firing capacitor, and the IBGT firing switch, wherein the trigger circuit is offset from the CDU axis such that the trigger circuit does not contribute to the axial length.

A capacitive discharge unit (CDU) for detonating an explosive in response to a control signal comprises a set of CDU components, including an exploding foil initiator (EFI), a trigger circuit, a firing capacitor, and an insulated-gate bipolar transistor (IGBT) firing switch. In various embodiments the components are arranged on a board for mechanically and electrically supporting the components in an ordered arrangement along a CDU axis where the CDU having an axial length defined by the ordered arrangement of two or more of the EFI, the firing capacitor, and the IBGT firing switch, wherein the trigger circuit is offset from the CDU axis such that the trigger circuit does not contribute to the axial length.

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.

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.

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.