Abstract: This invention discloses an engine for use in sustained space travel. The engine is of an electric type powered by a nuclear reactor. The electric engine includes a pulsed inductive magnetic thruster. A gas is discharged against an inductor comprising a series of parallel coils arranged in a spiral fashion. Each coil consists of four separate electrically connected coil sections. Each coil section traverses one-quarter of the distance around the inductor from an outer perimeter to an inner perimeter to form a single closed loop. A capacitor is electrically connected to two outer perimeter connector points for each coil forming a Marx Bank arrangement. All capacitors are charged to full charge and discharged simultaneously by a trigger generator immediately after a puff of propellant gas reaches the inductor. The high induced EMF in the inductor caused by the multiple capacitors in series in a single loop creates a rapidly rising magnetic field which ionizes the propellant gas.

Abstract: A hybrid chemical/electromagnetic propulsion system which combines thermal expansion of a chemically-reacted propellant with electromagnetic acceleration of the propellant to provide an efficient propulsion system that operates in the specific impulse I.sub.sp range of 800 to 2500 seconds. The hybrid chemical/electromagnetic propulsion system includes a reaction chamber, an expansion nozzle mounted to the exit of the reaction chamber, and an induction coil wound around a portion of the expansion nozzle. The reaction chamber supports the combustion or chemical reaction of a propellant to form high-temperature ionizable reaction products. The expansion nozzle then expands these high-temperature reaction products to generate thrust. The induction coil generates a varying electric and magnetic field which ionizes and magnetically accelerates the reaction products to generate additional thrust. A drive circuit supplies current to the induction coil in a manner that maximizes this additional thrust.

Abstract: A low pressure gas laser is provided with an aerodynamic window for the generated high power laser beam. The window comprises a duct with an oblique opening located in the supersonic part of and aligned with the axis of a Laval nozzle, having an atmospheric entrance. This permits extraction of the beam from the laser without any contact through a solid window.