In some embodiments A space-based sensor fabrication system contains a fluid containment system connected to a fluid deposition system. The fluid deposition system is set up to manufacture a SAM onto an electrode blank in a microgravity environment. A fabrication chamber that is set up to house and control a number of different fabrication systems in a microgravity, low gravity, and/or no gravity environment. A space-based sensor fabrication system can use surface tension to hold a fluid in place during sensor fabrication.

A service satellite for providing station keeping services to a host satellite is disclosed. The service satellite may have a body, and a gripping mechanism attached to the body. The gripping mechanism may be adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring may form an interconnected unit having a combined center of mass. The service satellite may have at least two thrusters and at least one controller. The at least one controller may maintain the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters avoid passing through the combined center of mass, and are each offset from the combined center of mass.

A service satellite for providing station keeping services to a host satellite is disclosed. The service satellite may have a body, and a gripping mechanism attached to the body. The gripping mechanism may be adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring may form an interconnected unit having a combined center of mass. The service satellite may have at least two thrusters and at least one controller. The at least one controller may maintain the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters avoid passing through the combined center of mass, and are each offset from the combined center of mass.

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.

A single-person spacecraft includes a pressurized crew enclosure, an external equipment bay, and an overhead crown assembly.

A single-person spacecraft includes a pressurized crew enclosure, an external equipment bay, and an overhead crown assembly.

Methods and systems to control stacked hexapod platforms for use as tools, which function with both high accuracy and high precision are provided. In some embodiments, the methods and systems include a convergence of modern control theory, and machine learning. Furthermore, some embodiments provide control algorithms to carry out autonomous in-space assembly operations using assemblers. Some embodiments provide methods and systems which combine long-reach low precision manipulators and smaller, high-precision assembler with interchangeable tools.

An outer space-based reusable manufacturing and assembly system including at least one joint that comprises at least one receiver component, at least one strut that engages the at least one receiver component on the at least one joint and a joining element that provides for engaging and disengaging the at least one joint with at least the at least one strut so that either the at least one joint and the at least one strut are usable for another mission. Two other systems are also disclosed.

An outer space-based reusable manufacturing and assembly system including at least one joint that comprises at least one receiver component, at least one strut that engages the at least one receiver component on the at least one joint and a joining element that provides for engaging and disengaging the at least one joint with at least the at least one strut so that either the at least one joint and the at least one strut are usable for another mission. Two other systems are also disclosed.