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 spacecraft propulsion system comprises two thrusters, each operating in accordance to a corresponding propulsion technique. A controller is configured to direct collected solar energy to heat a propellant for consumption in one of the two thrusters, or to generate electric energy for the other one of the two thrusters.

To efficiently delivering payloads to respective orbits, a payload is received from a launch vehicle at a spacecraft operating as an orbital transfer vehicle. The payload is transferred, using the spacecraft, to a second orbit in accordance with a predefined fixed schedule that specifies at least the second orbit and a plurality of times at which the spacecraft transitions between the first and the at least second orbit.

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 solar power generation paddle includes a blanket that is stored by being taken up into a roll with using extension masts, and that is extended. Solar battery cells are disposed on one surface of the blanket, and thermoelectric conversion elements are disposed on the other surface of the blanket. A plurality of heat dissipation members are disposed on surfaces of the thermoelectric conversion elements which are opposite to surfaces near the blanket, along an extending direction, to cover the thermoelectric conversion elements.

To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant into a single phase, where the single phase is either liquid or gaseous; and supplying the single phase of the propellant to a thruster.

A spacecraft includes: a body a surface of revolution connected with the body, and a heat engine positioned at the center of the surface of revolution. The surface of revolution has a substantially open hollow torus shape with a transverse cross-section of a circle and two diametrically opposite portions each having a curvature extending from the circle. A first portion of the diametrically opposite portions has an opening and forms a solar concentrator for concentrating solar radiation in the direction of the heat engine. The first portion forms a primary solar radiation reflector. A second portion of the diametrically opposite portions is coaxial with the first portion and forms a secondary solar radiation reflector. The opening is configured so that the solar radiation passes in the direction of the center of the surface of revolution after reflection at the primary and secondary reflectors.

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 photovoltaic generator deployable for a satellite stabilized on three axes. The photovoltaic generator includes an assembly of planar panels articulated with respect to each other, and an attachment arm to the structure of the body of the satellite. In a first or launch position of the photovoltaic generator, the planar panels are folded one over the other. In a second or deployed position of the photovoltaic generator, the planar panels are fully deployed with at least a part of the planar panels being photovoltaic panels. At least one planar panel consists of a thermal radiator, with the radiative face thereof being orientated to be opposite the face of the photovoltaic panels carrying the photovoltaic sensors when the photovoltaic generator is in the deployed position. This radiative face is termed the shade face, and the face opposite the panel shaped radiator is termed the sun face.

A concentrated sunlight spacecraft architecture system comprising a sunlight concentrator assembly connectively attached to a spacecraft and configured to gather sunlight over a large area and direct the gathered sunlight to a smaller area, an optical waveguide, an optical distributor, and at least one of a plurality of spacecraft subsystems configured to receive and use the gathered sunlight. In an embodiment of the invention, the plurality of the spacecraft subsystems includes a solar thermal propulsion system, a power storage system, and a resource extraction system.