ThermaSat™ propulsion system uses water as a safe and non-explosive propellant, and which is unpressurized at liftoff. Utilizing solar thermal propulsion, the compact and efficient capacitor heats water to steam to produce high thrust and total impulse. The advanced optical system allows for the thermal capacitor to charge through solar power alone with no protruding concentrators or power draw from the main bus. Additional solar panels, body mounted to the ThermaSat, provide auxiliary heating of the thermal capacitor when not directly incident to sunlight to promote non-sun pointing operations.

An exploration method includes: a step of exploring a natural resource on a satellite, a minor planet, or a planet; a step of acquiring the natural resource detected by the exploration; and a step of storing the acquired natural resource.

A method for providing thermal balance of spacecraft electronics is provided. The spacecraft includes two or more electronic units wherein each electronic unit is capable of performing the same spacecraft operational task. The method for balancing the temperature of spacecraft electronics further includes providing each of the two or more electronic units with a temperature sensor for determining the temperature of that electronics unit. The electronic units and their respective temperature sensors are connected to a controller. In the event that the controller determines that the temperature of an activated first electronics unit has reached or exceeded a predetermined threshold, and the controller has determined that the temperature of a second deactivated electronics unit is below a predetermined threshold, the controller automatically deactivates the first electronics unit and activates the second electronics unit to perform the task previously being performed by the first electronics unit. This process continues automatically.

The invention relates to an aerial transport device by means of connections with supply lines and cables for the transport of electricity, liquids and goods, at the limit of the atmospheres of the planets, in areas with low gravitational attraction, so that the flight can take place in the formation. The aerial transport device by means of flight devices (A, A1n, B, Bn, A4) that are in motion and connected between them, characterized in that the system can supply (P1) and simultaneously transport physical objects, liquids, and energy (P) to and from the outer space of dense atmospheres (D) and to reach the maximum limit of the environment density suitable for space flight devices (A3) with aerodynamic load as well as for horizontal air transport (A4, A2, P, An, A3). The invention is technical device for transporting in space with flying devices and move in formation flight of at least three forming connections.

A space aircraft including a fuselage, two wings arranged on either side of the fuselage, and two nacelles arranged at the ends of the wings and each carrying a horizontal tail and a vertical tail, the fuselage having a cross section of variable size along the longitudinal axis with a maximum cross section being located in a longitudinal position located in front of the longitudinal position of the leading edges of the wings at the fuselage, making it possible in particular to help prevent the space aircraft from losing longitudinal static stability, the space aircraft thus having an optimized design and architecture which are suitable for the severe conditions encountered by such a space aircraft, in particular during atmospheric re-entry.

A propulsion system for a spacecraft includes a thrust generator for producing thrust to move the spacecraft. A propellant storage unit is in fluid communication with the thrust generator. A control assembly is in communication with the spacecraft. The control assembly includes a propellant management assembly configured to adjust a supply of propellant from the storage unit to the thrust generator. A controller is configured to control the propellant management assembly. The control assembly is configured to selectively operate the thrust generator in a first mode in which the thrust generator uses propellant to electrostatically generate thrust, and a second mode in which the thrust generator uses propellant to gas-dynamically generate thrust.

Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.

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.

Space vehicles with paraglider re-entry, and associated systems and methods are disclosed. A representative system includes a re-useable space vehicle, a collapsible, deployable and re-stowable re-entry heat shield carried by the space vehicle, and a collapsible, deployable and re-stowable flexible paraglider wing also carried by the space vehicle. The space vehicle can accordingly carry out repeated space-based missions, and can be refurbished and replenished on Earth and/or at an orbiting dock between missions.

A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure