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.

A magnetic apparatus and related method and energy product-by-process to motivate linear or rotational motion, comprising: at least one magnet ring tier comprising a ring of a plurality of permanent magnets; a central core comprising a permanent magnet projectile movement channel, an axis of the channel aligned in a direction normal to a geometric plane defined by the magnet ring, and running through a geometric center of the magnet ring; and each of the permanent magnets mounted in the ring at a mount angle thereof, with the components of their polar alignments parallel to the central core all oriented in the same direction; wherein: if the polar alignment of a permanent magnet projectile was introduced with a particular duality-dependent orientation into the permanent magnet projectile movement channel, the magnetic forces between the ring magnets and the projectile would be capable of motivating the permanent magnet projectile relative to the channel.

A magnetic apparatus and related method and energy product-by-process to motivate linear or rotational motion, comprising: at least one magnet ring tier comprising a ring of a plurality of permanent magnets; a central core comprising a permanent magnet projectile movement channel, an axis of the channel aligned in a direction normal to a geometric plane defined by the magnet ring, and running through a geometric center of the magnet ring; and each of the permanent magnets mounted in the ring at a mount angle thereof, with the components of their polar alignments parallel to the central core all oriented in the same direction; wherein: if the polar alignment of a permanent magnet projectile was introduced with a particular duality-dependent orientation into the permanent magnet projectile movement channel, the magnetic forces between the ring magnets and the projectile would be capable of motivating the permanent magnet projectile relative to the channel.

This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.

A projectile includes a projectile housing with at least one compartment, an energizable energy storage means, a payload, a control circuit, and an initiator. The payload may be sequestered in one compartment of the projectile until the projectile is separated or opened. A ram element within the projectile may move within the projectile to cause the opening of a projectile. The projectile may include a means for activating the initiator via dynamic induction. In an example embodiment, the projectile comprises a coil that is operatively coupled to a magnetic element of a launcher. The projectile may be charged dynamically as via interaction between the coil and magnetic element as the projectile moves within the launcher.

A projectile includes a projectile housing with at least one compartment, an energizable energy storage means, a payload, a control circuit, and an initiator. The payload may be sequestered in one compartment of the projectile until the projectile is separated or opened. A ram element within the projectile may move within the projectile to cause the opening of a projectile. The projectile may include a means for activating the initiator via dynamic induction. In an example embodiment, the projectile comprises a coil that is operatively coupled to a magnetic element of a launcher. The projectile may be charged dynamically as via interaction between the coil and magnetic element as the projectile moves within the launcher.

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.

The present invention discloses an apparatus and method for electromagnetic spacecraft propulsion. The apparatus includes capacitor assemblies bracketed by electromagnetic solenoids configured in Helmholtz Coil geometries. The action of magnetic fields generated in the solenoids on segmented currents in conductive discharge elements during capacitor discharge produces unidirectional forces, while reaction momentum is carried away by Poynting Vector electromagnetic fields in conformity with the currently understood principles of electrodynamics.

The present invention relates to a launching apparatus and, more particularly, to a launching apparatus using a revolving magnetic body, wherein the apparatus is safe and is capable of being driven with low power consumption, the apparatus including: an acceleration pipe formed by spirally winding a hollow pipe made of a non-magnetic material; a stator wound with a plurality of coils to encompass an outside of the acceleration pipe, and forming a magnetic field by being magnetized when an electric current is applied thereto; and a magnetic body launched outside after revolving along a circumference of the acceleration pipe due to a force exerted thereto by the magnetic field.

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.