Abstract: In a propellant tank, which especially stores cryogenic propellants, for example a fuel or an oxidizer for a spacecraft, and which operates with a driving gas to drive or convey the propellant, the propellant is separated from the driving gas in a propellant extraction apparatus using sieves with hydrostatic forces and capillary forces. The extraction apparatus includes a refillable reservoir, which is mounted near the tank floor outside of the tank shell, and which is connected via plural holes with the interior of the propellant tank. The extraction apparatus includes a double-walled housing that is thermally insulated. Capillary plates and struts are inserted in an L-shape into the reservoir. To substantially prevent the penetration of gas out of the propellant line, a cylinder-shaped pleated sieve is mounted at the end of the propellant line.

Abstract: In a propellant tank, which especially serves for storing cryogenic propellants, for example of spacecraft, and which is operated with a driving gas serving as a conveying medium, the separation of the propellant from the driving gas occurs in a propellant extraction apparatus by means of sieves and with the use of hydrostatic forces and capillary forces. The extraction apparatus has the form of a refillable reservoir, which is mounted in the vicinity of the tank floor outside of the tank shell on the floor region of the propellant tank, and which is connected via a number of holes with the interior of the propellant tank. The extraction apparatus itself consists of a double-walled housing and is additionally thermally insulated. Capillary plates and additional struts are inserted in an L-shape into the reservoir. Furthermore, to substantially prevent the penetration of gas out of the propellant line, a cylinder-shaped pleated sieve is mounted at the end of the propellant line.

Abstract: An apparatus for launching and dispensing multiple satellites into orbit includes a central structure and a plurality of satellites releasably bundled around the central structure to form a cohesive, single payload mounted on an upper stage of a launcher rocket. The central structure includes a central tube and an adapter shell that fits onto the upper stage of the rocket. Each satellite has the shape of a partial cylinder segment of which an outer wall is a cylindrical segment shell. The satellites are bundled and secured together around the central structure by tension bands, whereby the cylindrical segment shells form a load-bearing complete outer cylindrical shell that surrounds the central tube. This structure provides sufficient stiffness and strength to withstand the loads that arise during launch, while having a reduced mass. The satellites themselves, rather than the central structure, bear the loads during launch. This allows the central structure to be of relatively lightweight construction.

Abstract: Cylindrical bodies of structural components, such as a spacecraft and a rocket section or two rocket sections, are coupled to each other by a releasable coupling device. The structural components have radially protruding flanges that face each other and are encircled by the coupling device. The coupling device includes a flexible tensioning element, such as a steel belt or link chain, the ends of which are interconnected by a clamping or locking device. The clamping or locking device is constructed as a two-armed lever, one end of which is connected to each of the ends of the tensioning element. The two-armed lever is rotatably supported and driven by an operating member such as a pipe section or rod. The two-armed lever is thus rotatable through an angle of about 180.degree. so that the ends of the tensioning element are brought into overlapping positions. When the ends are in such overlapping positions the device is locked. Rotation of the two-armed lever into the opposite direction unlocks the device.