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.

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. Various antenna arrays and configurations are disclosed, some of which can cooperate for a specific aiming or targeting effect.

Described herein is a method of constructing a landing pad using a rocket engine while in-flight. Among other benefits, this method can reduce ejecta that otherwise would occur during landing on an unimproved surface. While a spacecraft is hovering over an unimproved surface, the spacecraft can inject particles into its rocket engine, after which the particles absorb heat from the engine and are projected at ballistic speeds toward the unimproved surface to create a landing pad. After constructing the landing pad and waiting for the landing pad to cool, the spacecraft can land on the landing pad. Also described herein are landing pads created from such particles as they impact the surface in a disc splat mode into the unimproved surface.

Described herein is a method of constructing a landing pad using a rocket engine while in-flight. Among other benefits, this method can reduce ejecta that otherwise would occur during landing on an unimproved surface. While a spacecraft is hovering over an unimproved surface, the spacecraft can inject particles into its rocket engine, after which the particles absorb heat from the engine and are projected at ballistic speeds toward the unimproved surface to create a landing pad. After constructing the landing pad and waiting for the landing pad to cool, the spacecraft can land on the landing pad. Also described herein are landing pads created from such particles as they impact the surface in a disc splat mode into the unimproved surface.

Methods for producing oxide/metal composite components for use in high temperature systems, and components produced thereby. The methods use a fluid reactant and a porous preform that contains a solid oxide reactant. The fluid reactant contains yttrium as a displacing metal and the solid oxide reactant of the preform contains niobium oxide, of which niobium cations are displaceable species. The preform is infiltrated with the fluid reactant to react its yttrium with the niobium oxide of the solid oxide reactant and produce an yttria/niobium composite component, during which yttrium at least partially replaces the niobium cations of the solid oxide reactant to produce yttria and niobium metal, which together define a reaction product. The pore volume of the preform is at least partially filled by the reaction product, whose volume is greater than the volume lost by the solid oxide reactant as a result of reacting yttrium and niobium oxide.

Methods for producing oxide/metal composite components for use in high temperature systems, and components produced thereby. The methods use a fluid reactant and a porous preform that contains a solid oxide reactant. The fluid reactant contains yttrium as a displacing metal and the solid oxide reactant of the preform contains niobium oxide, of which niobium cations are displaceable species. The preform is infiltrated with the fluid reactant to react its yttrium with the niobium oxide of the solid oxide reactant and produce an yttria/niobium composite component, during which yttrium at least partially replaces the niobium cations of the solid oxide reactant to produce yttria and niobium metal, which together define a reaction product. The pore volume of the preform is at least partially filled by the reaction product, whose volume is greater than the volume lost by the solid oxide reactant as a result of reacting yttrium and niobium oxide.

In a method of hybrid power generation in an environment with a gas pressure below the earth's atmospheric pressure, liquid water is extracted from a subsurface water ice deposit by pumping superheated-supercritical fluid heated by a heater through an extraction well into the subsurface water ice deposit in order to form a liquid water reservoir. Liquid water is pumped from the liquid water reservoir through the extraction well to the buffer tank. The liquid water is pumped from the buffer tank into a high pressure feeder system (HPFS) and a low pressure feeder system (LPFS), which are each also heated by the heater. The HPFS outputs supercritical water and the LPFS outputs flash steam into a combined injector and the mixture is injected into a turbine at near environmental pressure. This mixture explosively expands into superheated steam and passes through the turbine, powering an electrical generator.

A deformable device includes a deformable beam or hinge having an extended state, a flattened state, and a rolled state if a beam, where a stiffness and strength in the extended state is greater than a different stiffness and strength in the flattened state, the deformable beam or the hinge deformable along a long axis. An end face cross section transverse to the long axis includes a first periodic curved member which defines at least two shaped curves. A second periodic curved member defines at least two shaped curves. The second periodic curved member is mechanically coupled to the first periodic curved member at respective ends of the end face cross section. The first arc length of the first periodic curved member and the second arc length of the second periodic curved member are of about a same arc length.

A deformable device includes a deformable beam or hinge having an extended state, a flattened state, and a rolled state if a beam, where a stiffness and strength in the extended state is greater than a different stiffness and strength in the flattened state, the deformable beam or the hinge deformable along a long axis. An end face cross section transverse to the long axis includes a first periodic curved member which defines at least two shaped curves. A second periodic curved member defines at least two shaped curves. The second periodic curved member is mechanically coupled to the first periodic curved member at respective ends of the end face cross section. The first arc length of the first periodic curved member and the second arc length of the second periodic curved member are of about a same arc length.

A rocket-powered space launch system comprises both a vehicle segment with an integrally designed propulsion subsystem and a supporting ground facility segment. Elements of a propulsion unit as easily accessed for removal and replacement of individual components. Said launch system is highly reusable, operable, and facilitates governmental agency regulatory compliant safety of occupants and public without passenger escape function and/or commanded vehicle destruction.