Abstract: A factory for manufacturing useful products while orbiting is space uses concentrated solar energy, high vacuum, and the low temperatures available in a space environment. Gyroscopic forces from rotating machinery are carefully controlled. Liquids, gases, and solid minerals are separated from asteroid and lunar regolith resources.

Abstract: Deployable lunar landing pads for space mining applications are disclosed. In one aspect, a landing pad for deployment on a celestial body includes a deployable surface configured to be stored in a stowed configuration on a spacecraft and be deployed into a deployed configuration on a surface of the celestial body, a landing system configured to land the landing pad on the surface of the celestial body, and a control system configured to control the landing system during landing of the landing pad on the surface of the celestial body and control the deployment of the deployable surface. The deployable surface is further configured to reduce or eliminate scattering of loose material from the surface of the celestial body in the deployed configuration.

Abstract: 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.

Abstract: 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. Various antenna arrays and configurations are disclosed, some of which can cooperate for a specific aiming or targeting effect.

Abstract: Pneumatically supported towers for low gravity applications are disclosed herein. In one aspect, an inflatable tower for use in vacuum environments can have a membrane configured to support a load when inflated with an inflation gas to a pressures less than 100,000 pascals and greater than 0.01 pascal. The inflation gas can be chosen to have a sufficiently low boiling temperature at the inflation pressure of the membrane that the gas will not condense to a liquid or solid within a defined range of temperatures in which the tower is designed to operate. The membrane can be configured to be packaged for transport in deflated condition and rolled onto cylinders from which the membrane can be later unfurled and inflated as part of the tower inflation process.

Abstract: 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.

Abstract: 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. Various antenna arrays and configurations are disclosed, some of which can cooperate for a specific aiming or targeting effect.

Abstract: Systems and methods for fabrication of ceramics from celestial materials using microwave sintering and mechanical compression for space mining applications are disclosed. In one aspect, a chamber for sintering loose mineral material into solid ceramic shapes includes a plurality of zirconia insulting plates configured to clamp the mineral material and forming a cavity in which the mineral loose material is contained, and at least one dipole array configured to generate microwave energy and apply the microwave energy to the mineral material.

Abstract: 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.

Abstract: Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, a rocket propulsion system is configured to produce thrust for a spacecraft and includes: one or more optical elements configured to receive solar energy. The optical elements include: a first window configured to allow energy to enter the rocket propulsion system and form a concentrated energy beam, and a second window positioned to allow the concentrated energy beam to pass to the heat exchanger. The second window is spaced away from the first window to form a pressurized plenum chamber therebetween. The system further includes: a heat exchanger configured to receive the energy and use it to heat and pressurize a propulsion gas, and a rocket nozzle configured to expel the pressurized propulsion gas.

Abstract: Pneumatically supported towers for low gravity applications are disclosed herein. In one aspect, an inflatable tower for use in vacuum environments can have a membrane configured to support a load when inflated with an inflation gas to a pressures less than 100,000 pascals and greater than 0.01 pascal. The inflation gas can be chosen to have a sufficiently low boiling temperature at the inflation pressure of the membrane that the gas will not condense to a liquid or solid within a defined range of temperatures in which the tower is designed to operate. The membrane can be configured to be packaged for transport in deflated condition and rolled onto cylinders from which the membrane can be later unfurled and inflated as part of the tower inflation process. The membrane can be further configured to progressively inflate beginning at a bottom or lowest level of the membrane during the tower inflation process.

Abstract: 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.

Abstract: Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, an apparatus for collecting solar energy and simultaneously protecting against damage from a resulting energy beam includes a solar energy collection system including at least one concentrator and a target configured to use, store, or convert the solar energy, the collection system configured to cause solar energy to focus on the target, at least one sensor configured to detect misalignment of the concentrator by determining that some or all of the collected solar energy is offset from the target, and a safety system configured to redirect the energy or interpose a safety structure for shielding other non-target systems from receiving too much solar energy from the collection system.

Abstract: Systems and methods for fabrication of ceramics from celestial materials using microwave sintering and mechanical compression for space mining applications are disclosed. In one aspect, a chamber for sintering loose mineral material into solid ceramic shapes includes a plurality of zirconia insulting plates configured to clamp the mineral material and forming a cavity in which the mineral loose material is contained, and at least one dipole array configured to generate microwave energy and apply the microwave energy to the mineral material.

Abstract: 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. Various antenna arrays and configurations are disclosed, some of which can cooperate for a specific aiming or targeting effect.

Abstract: 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.

Abstract: Pneumatically supported towers for low gravity applications are disclosed herein. In one aspect, an inflatable tower for use in vacuum environments can have a membrane configured to support a load when inflated with an inflation gas to a pressures less than 100,000 pascals and greater than 0.01 pascal. The inflation gas can be chosen to have a sufficiently low boiling temperature at the inflation pressure of the membrane that the gas will not condense to a liquid or solid within a defined range of temperatures in which the tower is designed to operate. The membrane can be configured to be packaged for transport in deflated condition and rolled onto cylinders from which the membrane can be later unfurled and inflated as part of the tower inflation process. The membrane can be further configured to progressively inflate beginning at a bottom or lowest level of the membrane during the tower inflation process.

Abstract: Systems and methods for fabrication of ceramics from celestial materials using microwave sintering and mechanical compression for space mining applications are disclosed. In one aspect, a chamber for sintering loose mineral material into solid ceramic shapes includes a plurality of zirconia insulting plates configured to clamp the mineral material and forming a cavity in which the mineral loose material is contained, and at least one dipole array configured to generate microwave energy and apply the microwave energy to the mineral material.

Abstract: 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.

Abstract: Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, a rocket propulsion system is configured to produce thrust for a spacecraft and includes: one or more optical elements configured to receive solar energy. The optical elements include: a first window configured to allow energy to enter the rocket propulsion system and form a concentrated energy beam, and a second window positioned to allow the concentrated energy beam to pass to the heat exchanger. The second window is spaced away from the first window to form a pressurized plenum chamber therebetween. The system further includes: a heat exchanger configured to receive the energy and use it to heat and pressurize a propulsion gas, and a rocket nozzle configured to expel the pressurized propulsion gas.