Abstract: A thermal arcjet propulsion plant is particularly constructed for position and orbit corrections in a space flying body or spacecraft. A housing forms an anode and an expansion nozzle. An elongated rod mounted in an electrically insulating manner centrally in the housing forms the cathode which reaches with its tip into a plenum chamber just upstream of the nozzle. Propellant components formed by dissociating ammonia are injected into the plenum chamber. A small gap is provided between the tip of the cathode and the restrictor of the nozzle. An arc is ignited in this gap and the thermal arc energy is taken up by the by propellant. A dissociation chamber for the by propellant is arranged around the housing. The arrangement is such that the chamber in which the gas dissociation takes place is arranged in series with and upstream of the plenum chamber. The cathode is also arranged in series with the restrictor and the nozzle.

Abstract: An apparatus and a method of injecting a liquid are provided, especially for the intermittent, essentially drip-free injection of a liquid into a waste heat removal system in a spacecraft. The injection apparatus includes a housing having an inlet, an outlet, a discharge channel communicating with the outlet, and a receiving chamber controllably communicating with the discharge channel. A piston is movably arranged in the housing to define a boundary of the receiving chamber. A valve arrangement operates in response to the motion of the piston to respectively open or close the path of liquid communication between the receiving chamber and the discharge channel. This apparatus carries out the method, whereby when delivery of injection liquid is to be stopped any liquid remaining in the discharge channel is sucked out into the receiving chamber. Then, when delivery of injection liquid is to be resumed, the retained liquid is moved from the receiving chamber into the discharge channel.

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.

Abstract: A multi-ply three-dimensionally bonded textile fabric is provided, to be used especially in making protective space suits, protective space shielding and other protective garments or shields. The fabric is a three-dimensionally woven, knitted, netted, braided or otherwise interlocked structure of threads including organic fibers such as aramid, polyethylene and/or polytetrafluoroethylene fibers and preferably also metallic fibers such as copper, aluminum and/or stainless steel fibers. These fibers are chosen to provide protection against adverse thermal, chemical, electrical and mechanical environmental effects that may be hazardous to an astronaut, for example. The fibers are arranged substantially in respective plies, and each ply is bonded or interlocked only to respective adjacent plies over substantially the entire ply area to provide a flexible multi-ply fabric. The threads are arranged to provide a gradient or variation in characteristics or properties from an outer surface to an inner surface.

Abstract: Shock sensitive equipment, for example, instruments in a spacecraft, must be protected against impacts, for example, those caused by severing explosions that separate the spacecraft from a used up rocket. For this purpose a platform carrying the component to be protected is secured to support structures of the craft by elastic spring devices, each of which has a low eigenfrequency or resonant frequency and a low damping constant, whereby the mounting is preferably so that friction forces are minimized. For example, the spring devices have a U-configuration connected to an L-configuration. Contact surface area minimizing ring spacers may be inserted between the platform and the spring devices.

Abstract: A heat pipe has at least one liquid flow channel and one vapor flow channel for the movement of the heat carrier fluid from the evaporator end to the condenser end and vice versa. The liquid flow channel is so constructed that the capillary radius of its cross-sectional area increases from the evaporator end to the condenser end of the heat pipe, preferably in a continuous manner. Further, the evaporator end of the pipe is provided with a closure member for communicating the liquid flow channel with the vapor flow channel for replenishing the liquid in the evaporating end if necessary. Opening of the closure member also permits gas and/or vapor bubbles that have been collected in the liquid flow channel to pass into the vapor channel. The closure member may be operated by an electromagnetic valve.

Abstract: A heat pipe structure, especially for cooling in a spacecraft, is equipped with a main heat pipe and at least one smaller diameter auxiliary heat pipe arranged so that the main and auxiliary pipes are in thermal contact with each other at the evaporator end of the main heat pipe. The condenser end of the auxiliary heat pipe, or pipes, is connected in a heat exchange manner with an auxiliary radiator or heat exchanger which is smaller than and thermally insulated from a main heat exchanger, the latter being in thermal contact with the condenser end of the main heat pipe. The auxiliary heat pipe, or pipes, super cools a bubble trap in the main heat pipe for removing of gas and/or vapor bubbles from the liquid flow path of the main heat pipe.

Abstract: A heat exchanger for a spacecraft utilizes a droplet radiator, whereby the droplet collector has the shape of a rotation symmetrical ring body that is rotatable about a central rotational axis. Preferably, the rotation symmetric ring body has the shape of a wheel, whereby the droplet generator is arranged near the rotational axis of symmetry and the collector forms a wheel rim. The return flow of the coolant takes place either through the spokes of the wheel which connect the droplet collector wheel rim to the hub or through a separate suction conduit. A secondary coolant flow circuit may be integrated into the droplet collector.

Abstract: A heat pipe is equipped with a bubble trap. Such bubble trap takes the form of a baffle that restricts the liquid flow in the liquid flow channel of the heat pipe to divide the two-phase flow in the liquid channel into a liquid flow and into a bubble and liquid flow. A cage of wire mesh is positioned downstream of the baffle to entrap the bubbles. In another embodiment the bubble trapping cage is a chamber that extends all the way into the evaporating end of the pipe while the baffle is arranged upstream of such a chamber which is additionally connected through perforations to the liquid flow channels.

Abstract: A linear drive for use in air and space travel converts the rotational drive of an electromotor into a linear motion of a runner which is secured to at least one flexible coupling member. The flexible coupling member runs around at least one guide member at one end thereof, and around a drive wheel driven by the electric motor at the other end of the flexible coupling member. The rotating drive wheel and the guide member both change the movement direction of the flexible coupling member, whereby the runner can run back and forth between the drive wheel and the guide member.

Abstract: A heat pipe is divided longitudinally by a divider wall into a vapor channel and into a liquid channel. The divider wall is provided, preferably at uniform axial spacings with bulges that form a restriction in the flow cross-sectional area of the vapor channel and an increase in the flow cross-sectional area of the liquid channel. A small diameter through bore is positioned at the peak of each bulge to connect the liquid channel with the vapor channel at this point. The reduced pressure at the restriction in the vapor channel is sufficient to suck gas or vapor bubbles collected under the bulge into the vapor channel, but insufficient to pull liquid into the vapor channel. The cross-sectional flow area of the liquid channel increases steadily toward each bulge, either from a point centrally between two bulges or from a point directly downstream of a bulge toward the next bulge as viewed in the flow direction of the liquid.

Abstract: An evaporation heat exchanger having at least one active circulating circuit for a coolant liquid to be cooled, is constructed for removing heat in a spacecraft under a gravity-free operating condition and under different acceleration conditions. For this purpose, a housing encloses an evaporating space provided with at least one inlet valve for controlling the admission of a medium to be evaporated. The produced vapor or steam is discharged through a respective outlet port. A plurality of cooling tubes interconnected in a meandering shape form a number of tube panels in which the individual tubes are arranged with a different spacing from one another in a direction from the inlet valve to the outlet port. Preferably, these spacings increase in the flow direction from the inlet port to the outlet port to establish a constant flow speed for the evaporating medium. The tubes forming a panel may be arranged in a zig-zag pattern within the panel.

Abstract: Heat is removed from a spacecraft under zero gravity and under various accelerations, by a heat exchange contact between a cooling liquid or coolant and an evaporant or medium to be evaporated. The coolant flowing in at least one liquid cooling circulation circuit and the evaporant which is discharged in its vapor phase, are brought into heat exchange contact with each other in processing chambers forming at least two separate heat exchange stages, wherein different pressure and temperature conditions are set. The cooling liquid or coolant and the medium to be evaporated evaporant flow through these stages in sequence and in such a way that the coolant first flows through the stage with the highest pressure and the highest temperature, and then flows through the stages with successively lower pressure and/or temperature.

Abstract: Heat generated, for example, in a spacecraft under zero gravity conditions and different accelerations is discharged through an evaporation heat exchanger connected to at least one active coolant circulation circuit. The heat exchanger has a bundle of tubes axially arranged inside a cylindrical processing chamber. An evaporant passes through these tubes. A coolant flows into heat exchange contact with outer surfaces of said tubes. The outlet cross-sectional flow area for the evaporant, or rather its vapor, is variable so that the pressure of the evaporated medium, and thereby also its evaporation temperature are adjustable. The adjustment of the cross-sectional flow area for the vapor is controlled in response to the temperature of the cooling liquid or coolant where it enters into a processing chamber of the heat exchanger. Selectively closable apertures in an end plate (52) serve for changing the outlet cross-section flow area for the vapor.

Abstract: In a fuel supply system for a space missile or a spacecraft in which the thrusters are supplied with liquid or gaseous fuel from a fuel tank in which the tank pressure decreases continuously during the operational life of the system, the fuel throughput and thus the thrust of the respective thruster or thrusters is maintained substantially constant by the arrangement of a constant flow device in the fuel line between the tank and the reaction chamber of the system. The constant flow device is a self regulating pressure loss device realized by increasing or decreasing the through-flow area of the device in response to changing fuel supply pressures.

Abstract: An active cooling circuit through which cooling liquid circulates, is connected to an evaporation heat exchanger for cooling said cooling liquid when it has begun to warm. For this purpose, a housing encloses an evaporation chamber into which an evaporation fluid, such as water, is sprayed whereby the heat needed for the evaporation cools the cooling liquid passing through a gap between an inner and an outer wall forming said housing. The active cooling circuit passes through the gap in which eddy bodies are arranged in such positions relative to the normal flow direction of the cooling liquid through the gap to cause eddy currents in the cooling liquid flowing through the gap for an improved heat exchange. The discharge for the evaporated fluid is located at the same housing end where the spray nozzles for the injection of the evaporation fluid are located.

Abstract: An evaporation heat exchanger, especially for removing heat from a spacecraft, has a housing formed by an inner cylinder and an outer cylinder which enclose a ring gap between the cylinders. A medium to be evaporated is injected into an evaporation chamber inside the inner cylinder. A cooling liquid is passed through the ring gap. Flow influencing elements are arranged in the ring gap for enhancing the heat transfer onto the inner surface of the inner cylinder for the evaporation. The flow control elements cause an eddy current of the cooling liquid. Additionally, these elements are shaped with interlocking projections and recesses to provide a mechanical coupling between the inner and outer cylinders. This coupling is capable of taking up radially extending forces in a force-locking manner, thereby preventing the bulging of the cylinders, even if the pressure in the ring gap should increase.

Abstract: The parts are interconnected by means of split strap arrangement engaging clamping elements which, through wedge action engage flanges of the parts and hold them together.

Abstract: A fuel for use independently of atmospheric air by reaction with an oxidizer, has a metal hydride as a solid fuel component mixed into an inert liquid fuel component and 1.5 to 5.0 weight percent of a stearate as part of the solid fuel component. The liquid fuel component is preferably an easy flowing paraffin into which the stearate and the solid fuel component are mixed to form a liquified fuel that will react with a liquid oxidizer. The mixing is preferably performed at a temperature above 100.degree. C. and at a reduced pressure less than 10.sup.5 Pa.

Abstract: An evaporation heat exchanger having at least one active circulating circuit for a coolant liquid to be cooled, is constructed for removing heat in a spacecraft under a gravity-free operating condition and under different acceleration conditions. For this purpose, a housing encloses an evaporating space provided with at least one inlet valve for controlling the admission of a medium to be evaporated. The produced vapor or steam is discharged through a respective port. A plurality of cooling tubes interconnected in a meandering shape form a number of tube panels in which the individual tubes are arranged in a zig-zagging pattern to form respective flow passages for the medium to be evaporated. The individual tubes extend in parallel to each other and perpendicularly to the flow direction of the medium to be evaporated, while the meandering configuration is forming the zig-zag pattern.