A retractable mast solar array includes a collapsible boom extensible by a boom deployer. At least one foldable upper arm assembly is coupled to the collapsible boom. At least one foldable lower arm assembly coupled to the collapsible boom. A foldable solar array includes two or more columns of blanket elements, each column of blanket elements is affixed at one end to the at least one foldable upper arm assembly and at an opposite end to the at least one foldable lower arm assembly. In a stowed state, the two or more columns of blanket elements are stowed folded in either or both of the at least one foldable upper arm assembly or the at least one foldable lower arm assembly, and in a deployed state, the two or more columns of blanket elements are unfolded to a deployed solar array.

A multistable compliant mechanism is formed by connecting sequentially multiple basic units front to end to form a closed annular structure. Each basic unit includes two flexible hinges perpendicular to each other on different planes and two rigid connection parts for connecting the flexible hinges. The two flexible hinges are connected by a rigid connection part, and one of the flexible hinges is connected to a flexible hinge of an adjacent basic unit through the other rigid connection part. Lengths of two rigid connection parts in a same basic unit are equal, but lengths of rigid connection parts of different basic units are not necessarily equal. The multistable compliant mechanism features the continuous rotation and multi-steady state of a tri-compliant mechanism. The multistable compliant mechanism also features variable mechanism topology, an adjustable unit number, easy implementation, and promotion. A method for steady state analysis of the multistable compliant mechanism is also provided.

A multistable compliant mechanism is formed by connecting sequentially multiple basic units front to end to form a closed annular structure. Each basic unit includes two flexible hinges perpendicular to each other on different planes and two rigid connection parts for connecting the flexible hinges. The two flexible hinges are connected by a rigid connection part, and one of the flexible hinges is connected to a flexible hinge of an adjacent basic unit through the other rigid connection part. Lengths of two rigid connection parts in a same basic unit are equal, but lengths of rigid connection parts of different basic units are not necessarily equal. The multistable compliant mechanism features the continuous rotation and multi-steady state of a tri-compliant mechanism. The multistable compliant mechanism also features variable mechanism topology, an adjustable unit number, easy implementation, and promotion. A method for steady state analysis of the multistable compliant mechanism is also provided.

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 method for generating a fissile material is described. The method includes positioning a fertile, non-fissile material within outer space, the position within an area of proton or other high energy particle radiation, rather naturally or artificially occurring, allowing the high energy particle radiation to impinge the fertile but non-fissile material over a time, the time based on amount of high energy particle radiation at the position, such that the non-fissile material gradually transmutes into a fissile material due to the impingement, and deploying the fissile material within a spacecraft.

A system includes rigid reservoirs, each divided by a flexible diaphragm into a hydraulic chamber and a delivery chamber. The hydraulic chamber is connected to a hydraulic liquid conduit via a valve and the delivery chamber is connected to a delivery conduit. A hydraulic actuator is operable to apply pressure to the hydraulic liquid so as to force the hydraulic liquid into a hydraulic chamber whose valve is open, pushing the diaphragm distally to force the delivery liquid from the delivery chamber into the connected delivery conduit. The actuator is also operable to apply suction to the hydraulic liquid in the hydraulic liquid conduit so as to draw hydraulic liquid from the hydraulic chamber, proximally pulling the flexible diaphragm to draw the delivery liquid from the delivery conduit into the delivery chamber.

A container for transporting satellite equipment and other equipment into low-orbit and deep space includes vacuum rigidizing structures covering the interior of each side wall and base of the container. The vacuum rigidizing structures contain microbeads and is connected to a pump mechanism able to transfer air into or out of the vacuum rigidizing structures. Before the equipment is added to the container, air is released from the vacuum rigidizing structures. After the equipment is added, the vacuum rigidizing structures are able to be inflated enough such that the microbeads compactly conform around the equipment, preventing movement while applying minimal pressure to the equipment. The container is capped with a lid lined with aerospace-grade foam.

An airlock for an extraplanetary environment includes an enclosed volume, an interior hatch separating the enclosed volume from a pressurized space, and an exterior hatch separating the enclosed volume from an external environment. The enclosed volume is selectably variable to reduce a mass of resources, lost into the external environment from the enclosed volume. A method of assembling an airlock for an extraplanetary environment includes defining an enclosed volume, positioning an interior hatch at the enclosed volume separating the enclosed volume from a pressurized space, and positioning an exterior hatch at the enclosed volume separating the enclosed volume from an external environment. The enclosed volume is selectably variable to reduce a mass of resources lost into the external environment from the enclosed volume.

An equipment cleaning apparatus for an extraplanetary environment includes a cleaner vessel positioned at an exterior of an extraplanetary habitat, and an exterior hatch located outside of the extraplanetary habitat and allowing access to an interior of the cleaner vessel. The cleaning apparatus is operable in one or more cleaning cycles to clean equipment located in the cleaner vessel. A method of cleaning equipment in an extraplanetary environment includes providing a cleaner vessel at an extraplanetary habitat, placing one or more articles of equipment into an interior of the cleaner vessel through an exterior hatch located outside of the extraplanetary habitat, closing the exterior hatch, and operating one or more cleaning cycles on the equipment in the cleaner vessel.

The disclosure relates to space science and space transportation, in particular, to the area of commercial exploitation of outer space, and, namely—to the structure of multiple-mission geospatial transportation complex and method of operation thereof, based on the principle of non-rocket ‘planet surface to planned circular orbit’ payload insertion. A general planetary geospatial transportation complex, according to a first variant includes a general planetary vehicle encircling the planet along the line of the planet surface cross-section by the plane parallel to plane of the equator, fastened, on launch overpass of specified altitude, and represents a linear bearing structure encircling the planet, comprising pressure hull with the special endless linear flywheels, equipped with systems of magnetic and/or electromagnetic suspension and linear electromagnetic drives. For a general planetary geospatial transportation complex, it is distinctive that the present intended use is to solve the set of geospatial problems in industrial-scale volumes, for instance, for the purpose of relocation of ecologically harmful portion of earth-based manufacturing into near space and non-rocket space industrialization, as well as stabilization of the global climate.