A customizable thin plate fuel form and reactor core therefor are disclosed. The thin plate fuel will comprise a fuel material embedded within a matrix material, with the entire unit having a coating. The thin plate fuel may be flat or curved and will have flow channels formed within at least the top surface of the fuel plate. The structure of the thin plate fuel will make it easier for coating with Tungsten or any other suitable material that will help contain any byproducts, prevent reactions with the working fluid, and potentially provide structural support to the thin plate fuel.

A system includes a nuclear reactor having a plurality of fuel rods of radioactive decay material distributed within and embedded within a heat exchange matrix. A plurality of coolant tubes is distributed within and embedded within the heat exchange matrix, interspersed with the plurality of fuel rods. The heat exchange matrix is configured to conduct heat from the fuel rods to the coolant tubes.

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes means to use an electric propulsion system coupled to a frame of a spacecraft, the electric propulsion system including at least a first thruster and a second thruster, the first thruster adjacent a first side of the frame, the second thruster adjacent a second side of the frame, and means to allow at least one of the first thruster or the second thruster to control the spacecraft without using a chemical propulsion system.

This invention relates to a propulsion bay to be transported, at least temporarily, in a space launch vehicle and comprising an adapter that co-operates with at least one system located, at least temporarily, on board the bay, said system comprising an electrical power supply. The bay is characterized in that it also comprises at least one electric space propulsion engine that can be powered by the power supply of the system.

Disclosed are a method of flying on the moon and a device for flying using the method. A medium on a surface of a moon and a medium accelerating module are used in the flying method. The medium is transferred into the medium accelerating module, accelerated by the medium accelerating module, and ejected out of the medium accelerating module by using a power supply. A counterforce is generated in accordance with the momentum conservation, and the counterforce overcomes the lunar gravity and drives a load to take off. The method is suitable for the environment of the moon where flight by means of atmospheric buoyancy is impossible due to the shortage of atmosphere.

A continuous electrode (CE) inertial electrostatic confinement (IEC) device has particle paths radially extending from a central core region. Each particle path has a corresponding particle path aligned on an opposite side of the central core region. Sidewalls bounding the particle paths provide continuous surfaces radially extending from a cathode region proximal to the central core region to an anode region remote from the central core region. Electrodes are coupled to the sidewalls to provide an electric field that varies along each particle path from the cathode region to the anode region. The CE-IEC device can be used for particle fusion by directing ions along the particle paths to the central core region, for example, to generate power or to propel a spacecraft.

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An apparatus includes a space vehicle including means for performing propulsion operations without using a chemical propulsion system.

This present invention describes initial sequential methods for constructing and placing into operation a multi-purpose maintenance complex and a space dock in high geosynchronous orbit. This is dual function complex that can provide a orbital platforms to a commercial profitable enterprise or to the Department of Defense (DoD) to enhance their capabilities. A complex will have the capability to fabricate, assemble, test, and place into full operation any size orbital and planetary surface complexes and spacecraft. DoD mission capabilities embracing satellite repairs, research, national security and deterrence, space junk disposal support and other services while in orbit.

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example method includes deploying a space vehicle including an electric propulsion system; and using the electric propulsion system for attitude control and orbit control, no other propulsion system provided to enable the attitude control and the orbit control.

A thermal power reactor is provided. The thermal power reactor includes a reactor core arranged to generate thermal energy and a solid state thermal conductor including a graphene based metamaterial. The solid state thermal conductor extends into and is thermally integrated with the reactor core. The solid state thermal conductor is arranged to transfer thermal energy generated by the reactor core away from the reactor core.