An optical mining apparatus comprising: a light weight solar reflector; optics for controlling the delivery of concentrated sun light onto the surface of a target; and a temperature controlled gas enclosure that contains the target; wherein said solar reflector is oriented to reflect sun light onto said optics.

The invention relates to a spacecraft comprising a body having two opposite faces; a first radiator carried by at least one face; the first radiator having an outer face; a first supporting arm extending substantially perpendicularly to the outer face of the first radiator; a drive motor suitable for rotating the first supporting arm about its longitudinal axis a first assembly carried by the first supporting arm, said first assembly comprising a plurality of slats stationary with respect to the first supporting arm; said slats being attached one above the other and separated from each other by a free space.

Disclosed is a thrust-producing device that can generate force in any medium (in air, in space, underwater). The device, in and of itself, does not have an external intake, or exhaust. Thrust is produced when electro-mechanical and/or thermal energy is applied to a closed, pressurized container of gas so as to produce an imbalance in the internal pressure within the container. A measure of corrosion prevention can be achieved by using N.sub.2, an inert gas, or some other gas that will not chemically react with the other constituents in the container. Although this invention was principally intended as an advancement in the field of space propulsion systems, it has wide applicability across all modes of transportation; and has applications in stability and control, as well as propulsion.

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.

A dynamic flex circuit includes a plurality of hole sets arranged along the dynamic flexible circuit. The dynamic flex circuit also includes a plurality of actuator wires coupled to the dynamic flexible circuit by way of intertwining each of the plurality of actuator wires through each hole set in the plurality of hole sets arrange along the dynamic flexible circuit. Each of the plurality of actuator wires are configured to impart a motion onto the dynamic flexible circuit depending on the amount of heat applied to each of the plurality of actuator wires.

A panel array and associated deployment system may include a first cable extending along a first row of panels and coupled to each panel of the first row of panels. The array and system may further include a second cable extending along a second row of panels and coupled to each panel of the second row of panels. The array and system may also include a first column of panels comprising a panel from the first row of panels and a panel from the second row of panels. The system may further include a spool positioned adjacent the first column of panels. The spool may be coupled to at least one of the first cable and the second cable and configured to apply tension to the first cable and/or the second cable.

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.

A mass propelled device includes an evaporation chamber and at least one nozzle. The evaporation chamber includes (i) at least one transparent substrate and (ii) a plurality of nanostructures disposed on a second surface opposite a first surface. The evaporation chamber receives light on the first surface and the plurality of nanostructures excites conduction electrons in response to the received light. The evaporation chamber heats propellent therein using the conduction electrons thereby generating heated propellant. The at least one nozzle produces thrust by exhausting the heated propellent from the evaporation chamber.