A transportation network for providing propellant in space can include optical mining vehicles that concentrate solar energy to spall captured asteroids, capture released volatiles, and store them in reservoirs as propellants. The network can also have orbital transfer vehicles that use solar thermal rocket modules that focus solar energy on heat exchangers to force propellant through nozzles, as well as separable aeromaneuvering tanker modules with reusable heatshields and storage tanks. The network can have propellant depots positioned between Earth and a transport destination. The depots can mechanically couple to accept propellant delivery and to supply it to visiting space vehicles.

To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant into a single phase, where the single phase is either liquid or gaseous; and supplying the single phase of the propellant to a thruster.

This proposed system provides a method to generate electrical power for space-based orbiting satellites, probes, stations, habitations, and interplanetary missions. Electricity is generated by collecting the flow of ionized plasma in the solar system for low earth applications and in the solar wind beyond the earth's magnetosphere, then directing the plasma through a channel using the principle of magneto-hydrodynamics (MHD). The channel has conducting electrodes on two sides and a magnetic field directed orthogonally to the plasma flow direction. This results in an electrical current to power spacecraft functions such as batteries, communications, propulsion, guidance, navigation and control. This MHD generator has the potential of providing higher power generation density (e.g., watts/kg) for spacecraft than photo-voltaic panels. The design includes a control system to maintain voltage quality, regulate electromagnet power and control ion inlet scoop RF frequency and voltage in response to changing space ionized plasma conditions.

An electromagnetic propulsion system for the movement of spacecraft by means of ejection of the perturbed dark matter. In the present invention, to perturb and accelerate the dark matter, the electromagnetic energy generated by microwave generators is supplied to a number of position-adjustable electromagnetic vibrators that form a phased antenna array inside the waveguide. Since the dark matter permeates the Universe and its reserves are unlimited, it can be used as a working medium in the constant acceleration propulsion system for as long as the electric power supply lasts. Since the electromagnetic propulsion system has infinite reserves of the working medium, the specific impulse is also infinite. The speed of the dark matter jet approaches the speed of light.

A transportation network for providing propellant in space can include optical mining vehicles that concentrate solar energy to spall captured asteroids, capture released volatiles, and store them in reservoirs as propellants. The network can also have orbital transfer vehicles that use solar thermal rocket modules that focus solar energy on heat exchangers to force propellant through nozzles, as well as separable aeromaneuvering tanker modules with reusable heatshields and storage tanks. The network can have propellant depots positioned between Earth and a transport destination. The depots can mechanically couple to accept propellant delivery and to supply it to visiting space vehicles.

A system operating in a spacecraft includes a tank storing a propellant, a thermal receiver configured to change the propellant from a first phase to a second phase by providing heat to the propellant, and an energy conversion device fluidically coupled to the tank and configured to generate electric energy using the propellant in the second phase.

A spacecraft propulsion system comprises two thrusters, each operating in accordance to a corresponding propulsion technique. A controller is configured to direct collected solar energy to heat a propellant for consumption in one of the two thrusters, or to generate electric energy for the other one of the two thrusters.

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.

An optical mining apparatus comprising: a light weight solar reflector; optics for controlling the delivery of concentrated sun light onto the surface of a target; and a temperature controlled gas enclosure that contains the target; wherein said solar reflector is oriented to reflect sun light onto said optics.

ThermaSat™ propulsion system uses water as a safe and non-explosive propellant, and which is unpressurized at liftoff. Utilizing solar thermal propulsion, the compact and efficient capacitor heats water to steam to produce high thrust and total impulse. The advanced optical system allows for the thermal capacitor to charge through solar power alone with no protruding concentrators or power draw from the main bus. Additional solar panels, body mounted to the ThermaSat, provide auxiliary heating of the thermal capacitor when not directly incident to sunlight to promote non-sun pointing operations.