An electromagnetic impact drive includes two electroconductive helical springs in meshing relationship, with their fixed ends supported on an abutment and their movable ends joined to an electroconductive armature. Electric terminals connect the fixed ends to a electricity source for feeding a current to flow from one of the electric terminals via an associated one of the helical springs in a first direction towards the armature and from there in an opposite second direction via the other one of the helical springs to the other one of the electric terminals so that adjacent windings of the helical springs repel one another by an oppositely directed force pair when an electric circuit is closed. A control device is provided to open and close the electric circuit with the electricity source.

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.

A vertical superjunction edge termination structure for the drift region of wide bandgap semiconductor devices that provides a low resistance and high off voltage allowing the breakdown voltage of the superjunction drift region to be raised.

Embodiments are directed to unpowered railgun field validation for safe-arm fuzing. Embodiments use a wire coil having an induced electromotive force voltage. At least one positive duration circuit measures the positive portion of the induced voltage. At least one positive peak duration circuit measures the peak value of the positive portion of the induced voltage. At least one negative duration circuit measures the duration value of the negative portion of the induced voltage. At least one negative peak detector circuit measures the peak value of the negative portion of the induced voltage.

The invention uses a propulsion mechanism in the form of electromagnetic force by current flowing through conductive material, a loaded spring or compressed air to expel a string attached to a strong adhesive, removable surface. An edge attached material allows the adhesive to be fired through a barrel onto surfaces it will adhere to and allow the user to pull on objects from a distance.

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.

Steady-field coilgun methods and devices based on a steady-field coil(s). The fundamental operational basis is to leave the current running in the solenoid/coil during the operation of the gun or other projectile launcher, where the field must be built up only once-initially, when turning the gun or launcher on. Then firing involves loading a bullet or other projectile in the barrel and releasing it to be accelerated by the established magnetic field. To fire again, the system loads the next bullet into the barrel and releases it again to be accelerated by the same steady magnetic field. To stop the firing, simply prevent the next bullet from loading, or load it but do not release it in the barrel. To turn off the system, simply disconnect the DC voltage driving the current in the solenoid(s)/coil(s).

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.

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 shaped projectile in the payload and to launch the projectile.

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.