A lunar regolith reduction reactor system includes a housing, a crucible, and a pair of electrodes. The housing includes a base structure and a cover structure detachably connected to the base structure, a gas input port to permit input of hydrogen gas into the housing, and a gas output port to permit outgassing of water vapor and gases. The crucible is designed to hold an amount of lunar regolith in the housing. The electrodes are disposed apart from one another and adjacent the crucible, wherein the electrodes are connectable to a power source to generate an electric arc to heat lunar regolith in the crucible and initiate a reduction reaction to separate oxygen gas and reduce separated material into a molten state.

A lunar regolith reduction reactor system includes a housing, a crucible, and a pair of electrodes. The housing includes a base structure and a cover structure detachably connected to the base structure, a gas input port to permit input of hydrogen gas into the housing, and a gas output port to permit outgassing of water vapor and gases. The crucible is designed to hold an amount of lunar regolith in the housing. The electrodes are disposed apart from one another and adjacent the crucible, wherein the electrodes are connectable to a power source to generate an electric arc to heat lunar regolith in the crucible and initiate a reduction reaction to separate oxygen gas and reduce separated material into a molten state.

Solar thermal and chemical hybrid rocket configurations for mining and other space applications are disclosed. One aspect is a rocket propulsion system configured to provide rocket thrust, including a solar absorber, a rocket nozzle, and a solar power collection system configured to collect solar energy from the sun, generate an energy beam from the collected sunlight, heat the solar absorber to transfer heat to one or more pressurized propulsive gases, and expel the heated pressurized propulsive gases through a rocket nozzle. A solar absorber can be formed from a granular collection or agglomeration of solids (e.g., of beads), which can be layered with more transparent layer(s) above and more absorbing layer(s) below to create a temperature profile in propellant(s) flowing through the absorber. A hybrid motor can provide an energy (e.g., solar) absorber for absorbing and transferring radiative energy as well as a combustion area. Multiple propellants can be present in a single chamber and be forced from a nozzle to produce thrust. Pressure in a rocket can be achieved from heating inert gasses, and alternatively or simultaneously, from mixing and igniting non-inert gasses.

Solar thermal and chemical hybrid rocket configurations for mining and other space applications are disclosed. One aspect is a rocket propulsion system configured to provide rocket thrust, including a solar absorber, a rocket nozzle, and a solar power collection system configured to collect solar energy from the sun, generate an energy beam from the collected sunlight, heat the solar absorber to transfer heat to one or more pressurized propulsive gases, and expel the heated pressurized propulsive gases through a rocket nozzle. A solar absorber can be formed from a granular collection or agglomeration of solids (e.g., of beads), which can be layered with more transparent layer(s) above and more absorbing layer(s) below to create a temperature profile in propellant(s) flowing through the absorber. A hybrid motor can provide an energy (e.g., solar) absorber for absorbing and transferring radiative energy as well as a combustion area. Multiple propellants can be present in a single chamber and be forced from a nozzle to produce thrust. Pressure in a rocket can be achieved from heating inert gasses, and alternatively or simultaneously, from mixing and igniting non-inert gasses.

Systems and methods are disclosed for mining lunar and Martian polar permafrost to extract gas propellants. The method can comprise identifying a plurality of near-polar landing sites in craters in which the surface comprises permafrost in perpetual darkness, wherein such landing sites have perpetual sunlight available at altitudes of about 100 to 200 m. A mining outpost can be established in at least one of the sites and a high altitude solar array deployed at the landing site using a lightweight mast tall enough to generate near continuous power for the outpost. Systems and apparatus are disclosed for mining the permafrost at the landing sites using radiant gas dynamic mining procedures. The systems can comprise a rover vehicle with an integrated large area dome for cryotrapping gases released from the surface and multi-wavelength radiant heating systems to provide adjustable heating as a function of depth.

Systems and methods are disclosed for mining lunar and Martian polar permafrost to extract gas propellants. The method can comprise identifying a plurality of near-polar landing sites in craters in which the surface comprises permafrost in perpetual darkness, wherein such landing sites have perpetual sunlight available at altitudes of about 100 to 200 m. A mining outpost can be established in at least one of the sites and a high altitude solar array deployed at the landing site using a lightweight mast tall enough to generate near continuous power for the outpost. Systems and apparatus are disclosed for mining the permafrost at the landing sites using radiant gas dynamic mining procedures. The systems can comprise a rover vehicle with an integrated large area dome for cryotrapping gases released from the surface and multi-wavelength radiant heating systems to provide adjustable heating as a function of depth.