An electromagnetic launcher with a curved or spiral-shaped, open-ended guideway and conductors for launching a projectile. The projectile, movably retained on or within the guideway, is accelerated along the guideway using electromagnetic forces until it reaches an end of the guideway, then the projectile is launched in a desired direction. The direction of the launch of the projectile is determined by orienting the guideway in the desired direction using an actuator.

A testing device for study of a magnetized plasma artillery and gunpowder, comprising a pedestal, wherein a top end of the pedestal is provided with a sliding slot for mounting a buffer device, which penetrates through an upper part of the pedestal along a front-rear direction. The sliding slot for mounting the buffer device is internally provided with a buffering slider, which can slide back and forth along the sliding slot for mounting the buffer device. A top end of the buffering slider is provided with a gunpowder combustion chamber fixing groove, which penetrates through an upper part of the buffering slider along the front-rear direction. The gunpowder combustion chamber fixing groove is internally provided with a gunpowder combustion chamber, and an upper part of the gunpowder combustion chamber is provided with a positioning ferrule for fixing the gunpowder combustion chamber.

An energy recovery pulse forming network and method that recovers at least a portion of the energy in a railgun by transferring energy dissipated from the railgun inductance back to an initial source of the energy, such as an input capacitor, for use by the network. This reduces the amount of energy required from an external power source to charge the input capacitor during subsequent railgun firings.

A space launch system and method through electromagnetic pushing. The space launch system comprises an energy storage subsystem, an energy conversion subsystem, a linear motor subsystem, and a control maintenance subsystem. The space launch system converts the electric energy into an electromagnetic force. Through the electromagnetic force, a rocket is pushed to be accelerated to a certain speed along an electromagnetic launching track to realize the launching of the rocket.

Methods and systems for recuperated superheat return are provided. A coolant is supplied in a vapor state to a compressor. The coolant compressed by the compressor is cooled with a gas cooler. The coolant cooled by the gas cooler is supplied to an inlet of a high pressure side of a recuperator. The coolant from an outlet of the high pressure side of the recuperator is supplied to a portion of a coolant circuit. The coolant is supplied back from the portion of the coolant circuit to an inlet of a low pressure side of the recuperator. The coolant in the low pressure side of the recuperator is heated with thermal energy transferred by the recuperator from the coolant in the high pressure side of the recuperator. The coolant in the vapor state from an outlet of the low pressure side of the recuperator is supplied to the compressor.

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 system and method for magnetically launching projectiles or spacecraft includes an electromagnetic launcher including a launch tube, and a launch craft. The launch tube includes electrically conducting rails energized along the length of the rails, and a transverse direct current magnetic field is generated along the launch tube, and upper and lower conductors and loops of conducting material on the launch craft are provided for magnetic levitation, stabilization and propulsion of the launch craft in cooperation with the transverse direct current magnetic field. A transverse direct current magnetic field is applied to the launch tube and the launch craft during launching of the launch craft, and the launch craft is magnetically levitated and stabilized to minimize contact between the launch craft and the launch tube as the launch craft travels within the launch tube.

An electromagnetic launcher with a curved or spiral-shaped, open-ended guideway and conductors for launching a projectile. The projectile, movably retained on or within the guideway, is accelerated along the guideway using electromagnetic forces until it reaches an end of the guideway, then the projectile is launched in a desired direction. The direction of the launch of the projectile is determined by orienting the guideway in the desired direction using an actuator.

A rotary propulsion engine system designed to propel a craft. Such a rotary propulsion engine system comprises at least two reaction masses or armatures, at least two reaction mass driver assemblies, at least two travel pathways for said reaction masses or armatures, two counterrotating discs housing an equal number of the at least two said reaction mass driver assemblies, and a counterbalancing means used to maintain a balanced distribution of masses about the axis of rotation of each counterrotating disc in order to maintain a zero horizontal torque sum as each reaction mass or armature moves along its ballistic trajectory. Reaction masses are fired into a rotational environment wherein the kinetic energy of said reaction masses is recycled, thereby reducing or eliminating the need for chemical propellant-based propulsion systems, and transporting heavy, finite, and expensive fuels for combustion.

An electromagnetic launcher with a curved or spiral-shaped, open-ended guideway and conductors for launching a projectile. The projectile, movably retained on or within the guideway, is accelerated along the guideway using electromagnetic forces until it reaches an end of the guideway, then the projectile is launched in a desired direction. The direction of the launch of the projectile is determined by orienting the guideway in the desired direction using an actuator.