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.

A moon-based in-situ condition-preserved coring multi-stage large-depth drilling system and method therefor. The system includes a rotary plate provided inside a lander, an in-situ condition-preserved coring tool provided on a surface of the rotary plate, a space frame provided on a surface of the rotary plate, a working platform provided on a top of the space frame, a mechanical arm provided on a bottom surface of the working platform, and a camera provided on the bottom surface of the working platform, the mechanical arm is fixedly connected to the working platform, and the camera is fixedly connected to the working platform. By controlling the mechanical arm to place the in-situ condition-preserved coring tool on the moon surface, and using the in-situ condition-preserved coring tool to sample the lunar soil on the moon surface, the coring operation problem of the lunar soil is solved.

A moon-based in-situ condition-preserved coring multi-stage large-depth drilling system and method therefor. The system includes a rotary plate provided inside a lander, an in-situ condition-preserved coring tool provided on a surface of the rotary plate, a space frame provided on a surface of the rotary plate, a working platform provided on a top of the space frame, a mechanical arm provided on a bottom surface of the working platform, and a camera provided on the bottom surface of the working platform, the mechanical arm is fixedly connected to the working platform, and the camera is fixedly connected to the working platform. By controlling the mechanical arm to place the in-situ condition-preserved coring tool on the moon surface, and using the in-situ condition-preserved coring tool to sample the lunar soil on the moon surface, the coring operation problem of the lunar soil is solved.

A lunar excavation and projectile transport system includes a projectile launcher having a base and a throwing arm and a projectile catcher. The throwing arm is rotatably coupled to the base and arranged at a mounting angle relative to a central axis defined by the base. The mounting angle defines a lunch angle for a processed core sample that is launched from within the throwing arm during rotation of the throwing arm by an electric motor. The projectile catcher includes a storage body, a plurality of telescoping arms coupled to the storage body, and a fabric wrapped around each of the plurality of telescoping arms to define a catching volume within which the processed core sample launched by the projectile launcher is caught.

A lunar excavation and projectile transport system includes a projectile launcher having a base and a throwing arm and a projectile catcher. The throwing arm is rotatably coupled to the base and arranged at a mounting angle relative to a central axis defined by the base. The mounting angle defines a lunch angle for a processed core sample that is launched from within the throwing arm during rotation of the throwing arm by an electric motor. The projectile catcher includes a storage body, a plurality of telescoping arms coupled to the storage body, and a fabric wrapped around each of the plurality of telescoping arms to define a catching volume within which the processed core sample launched by the projectile launcher is caught.

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 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.

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.

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.

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.