A laser sample chamber for deep space exploration includes a sample chamber base and a sample chamber top cover. The sample chamber base is a hollow cylinder with bottom end being sealed and top end being open, and an internal cavity in the hollow cylinder is provided for receiving sample plates; and a body of the sample chamber top cover is a hollow cylinder with a top end being sealed and a bottom end being open, and the body consists of a plurality of components which comprise a hollow annulus positioned at a middle of the sample chamber top cover, a circular viewing window positioned at an opening at a top end of the hollow annulus, and a threaded port positioned at an opening at a bottom end of the hollow annulus and protruding outward.

A laser sample chamber for deep space exploration includes a sample chamber base and a sample chamber top cover. The sample chamber base is a hollow cylinder with bottom end being sealed and top end being open, and an internal cavity in the hollow cylinder is provided for receiving sample plates; and a body of the sample chamber top cover is a hollow cylinder with a top end being sealed and a bottom end being open, and the body consists of a plurality of components which comprise a hollow annulus positioned at a middle of the sample chamber top cover, a circular viewing window positioned at an opening at a top end of the hollow annulus, and a threaded port positioned at an opening at a bottom end of the hollow annulus and protruding outward.

A quick disconnect apparatus including a first end configured to interface with a legacy fill and drain valve (FDV) of a satellite to be serviced, a second end configured to interface with a refueling tool, and a middle portion including at least one redundant seal to prevent unwanted fuel transfer during connection of the FDV and refueling tool.

A quick disconnect apparatus including a first end configured to interface with a legacy fill and drain valve (FDV) of a satellite to be serviced, a second end configured to interface with a refueling tool, and a middle portion including at least one redundant seal to prevent unwanted fuel transfer during connection of the FDV and refueling tool.

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 robot including an extendable device capable of extending and contracting in at least one direction, at least two end effectors that are respectively connected to at least two end portions of the extendable device, and a control unit capable of causing the extendable device to extend and contract, wherein each of the at least two end effectors includes at least one grasping unit that extends outward, and the robot is operable to grasp a target by the at least two end effectors by the control unit causing the extendable device to extend or contract.

A robot including an extendable device capable of extending and contracting in at least one direction, at least two end effectors that are respectively connected to at least two end portions of the extendable device, and a control unit capable of causing the extendable device to extend and contract, wherein each of the at least two end effectors includes at least one grasping unit that extends outward, and the robot is operable to grasp a target by the at least two end effectors by the control unit causing the extendable device to extend or contract.

Omni-directional, extensible grasp mechanisms are disclosed. Such grasp mechanisms may be used as a robotic end effector for docking, grasping, and manipulating space structures, or to interconnect other structures or vehicles. Novel interconnected lattice structures may enable large arrays to be assembled. The grasp mechanisms may be used to create structures from parallel docking linkages. This may enable reconfiguration of multiple docked space vehicles and/or structures without the use of propellant. The grasp mechanisms have the ability to make and break connections multiple times, enabling a nondestructive and reversible docking process.

Omni-directional, extensible grasp mechanisms are disclosed. Such grasp mechanisms may be used as a robotic end effector for docking, grasping, and manipulating space structures, or to interconnect other structures or vehicles. Novel interconnected lattice structures may enable large arrays to be assembled. The grasp mechanisms may be used to create structures from parallel docking linkages. This may enable reconfiguration of multiple docked space vehicles and/or structures without the use of propellant. The grasp mechanisms have the ability to make and break connections multiple times, enabling a nondestructive and reversible docking process.