A method of space travel using a high acceleration thrust vehicle in combination with a plurality of low acceleration thrust vehicles. A primary spacecraft has a kinetic launcher that is utilized to discharge a plurality of subsidiary spacecraft in order to navigate the primary spacecraft along a flight path. Each of the plurality of subsidiary spacecraft has a propulsion system, allowing each of the plurality of subsidiary spacecraft to navigate to a refueling point. The refueling point for each of the plurality of subsidiary spacecraft may be a central location or a unique position along a subsequent flight path. Each of the plurality of subsequent spacecraft is then reloaded onto the primary spacecraft or loaded onto a subsequent spacecraft for another voyage. The kinetic launcher can be repositioned in order to control the direction of the acceleration experienced by the primary spacecraft.

An electromagnetic energy momentum thruster has a cavity resonator and an electromagnetic radiation source for emitting an electromagnetic wave in evanescence into the cavity resonator. The electromagnetic wave produces a greater electromagnetic field amplitude and a greater electromagnetic radiation pressure on a primary interior surface area of the cavity resonator than on a secondary interior surface area of the cavity resonator. The difference between the electromagnetic field amplitude on the primary interior surface area and on the secondary interior surface area of the cavity resonator forms a highly directional electromagnetic energy momentum tensor and provides a highly directional general relativistic metric tensor. As a result, a force is produced on the cavity resonator in the form of a thrust or an acceleration that propels the device in a direction substantially perpendicular to the primary interior surface area.

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

A de-orbiting system for a space vehicle may include one or more lithium ion (Li-ion) batteries configured to release hot gases to be used for thrusting during de-orbiting of the apparatus. The system may also include one or more heaters surrounding each of the one or more Li-ion batteries, which are configured to send each of the one or more Li-ion batteries into a thermal runaway. The thermal runaway causes the one or more Li-ion batteries to release stored electrochemical energy within each of the one or more Li-ion batteries.

Described hereafter is a device for the conversion of electromagnetic momentum into mechanical momentum to be used in airless environment. The device is built from rotating disk, made of non-magnetic material, on the circumference of which plurality of bar magnets are mounted. The bar magnets are in a plane which is perpendicular to the plane of the disk and in a plane, which is perpendicular to the radius of the disk that meets the centre of the bar magnet. The disk is driven by a motor that causes it to rotate. The magnets are positioned in an angle relative to the rotation axis of the disk. When the disk rotates, mechanical momentum, perpendicular to the plane of the rotating disk is generated. This momentum acts on the disk and causes it to move along the axis of rotation of the disk.

The invention relates to an electromagnetic toroidal impeller in the field of physics applied to electromagnetism. The invention comprises a cylindrical arrangement of superconducting antennas (9) which are separated by a dielectric (8) over a superconducting cylindrical plate (7) and exposed in a resonant cavity (6). The radiation in the cavity is incident on the force ring having a superconducting surface (4) containing ferrite (11), the coolant (5) introduced through the pipes (1) flowing through the toroidal interior of same. The force received in the ring (4) is transmitted via the supporting members (3) to the support (2). The cavity is thermally insulated with insulation (12) and is cooled with the liquid (10) through the pipes (14). The invention provides a device capable of generating driving force from the conversion of the energy available in electromagnetic waves that are contained in a resonant cavity.

A space launch system includes a launch track and an elevating platform for horizontally launching aerospace vehicles at a takeoff velocity. The launch track includes a first portion horizontally oriented with respect to the horizon, a second portion positioned after the first portion and horizontally oriented with respect to the horizon, and a third curved transition portion disposed between the first portion and the second portion. The elevating platform is coupled to the launch track and is configured to receive and position an aerospace vehicle upon the launch track. A magnetic accelerator is disposed along the launch track for propelling the aerospace vehicle down the launch track to reach the takeoff velocity. The magnetic accelerator includes magnetic levitation trains, each comprising a respective plurality of carriers that couple to the aerospace vehicle.

The operation of the ultra-high frequency (UHF) electromagnetic motor or thruster, is based on generating extremely short and powerful electrical, magnetic or electromagnetic field pulses and separating (unrooting) or disassociating said field pulses from the originating source, so that subsequently the emitting device and a device that is the objective or target, a support structure that supports both devices and another elements connected to said support structure are for an instant disassociated from the field, waiting for the pulsed field to reach the objective or target. At that moment, the element emits a field with a polarization that allows the exertion of a force that attracts or repels the field pulse, with respect to the objective or target and consequently with respect to the motor of which they form part as a unit, both the emitter and the target being joined by a support structure.

An electrodeless plasma thruster with close ring-shaped gas discharge chamber (1,10) can include a gas discharge chamber (1,10) close ring shaped in fluid communication with a propellant storage system (10,70). An antenna (3,30) can be positioned on the exterior of the gas discharge tube (1,10). A guide tube (2,20) can be coupled with the gas discharge chamber (1,10) at a first end and have a second open end. A magnetic system (7,50) can be positioned on the second end of the guide tube (2,20). The magnetic system (7,50) can be electrically coupled with a power supply. The power supply can be electrically coupled with a power converter (11,80) and a control module (12,90).

A liquid-driven propulsion device includes a first and a second chamber. The first chamber includes a first seal movable or deformable within the first chamber, the first seal being configured to separate a working liquid in the first chamber from a first space having a first pressure. The second chamber includes a second seal movable or deformable within the second chamber and configured to separate a working liquid in the second chamber from a second space having a second pressure. The first and the second chambers are coupled to each other to enable a flow of liquid between the first and second chambers. When the first pressure is greater than the second pressure, the working liquid in the first chamber moves in a first direction and the working liquid in the second chamber moves in a second direction to provide a propulsion force applied to the liquid-driven propulsion device.