Abstract: In conjunction with an arrangement for the interferometric radar measurement in connection with a radar system operating according to the ROSAR principle, comprising one coherent transmitting antenna and two coherent receiving antennas and their receiving channels, in connection with which the difference in the path between the two distances of the antennas and the measured points of impact is calculated by the wavelength &lgr; of the emitted radar signal and the measured phase difference of the receiving echo of the two coherent receiving channels, it is proposed that the interferometric ROSAR system is integrated in or on a rotating device and positioned in such a way that each relevant area of the field to be measured can be detected.

Abstract: A flexible foldable solar generator having an array of a plurality of blankets carrying solar cells hingeably connected to be folded and unfolded. The solar cells are connected together by branches and the branches are connected by connector lines in inner and outer current conducting tracks system arranged outside the blankets. The branches connect the solar cells with the connecting lines in the outer track to form a U-shaped series connection of the cells and the U-shaped series connected cells are connected in parallel by the connecting lines in the inner track where they can be connected to energy systems of the space vehicle.

Abstract: A regeneratively coolable nozzle for a rocket engine is formed by winding a tubular material (6) onto a winding mandrel to produce a helical composite structure (5), through which a coolant can flow during operation of the nozzle. The spiral composite structure (5) is fixed temporarily and the fixed composite structure (5) is removed from the winding mandrel. Then an inner heat resistant, load bearing layer (9) is applied to the radially inner hot-gas facing surface (H) of the fixed composite structure (5). The present nozzle is lightweight and withstands a high coolant pressure.

Abstract: Device for supplying fuel for a rocket propulsion unit has a first and at least a second fuel circuit for respective different fuels. Each fuel is brought to an increased energy level by a pump and is supplied for combustion by way of injection elements. The first fuel is heated in cooling channels extending in a propulsion chamber wall before the fuel is supplied for combustion, and the first fuel is subsequently fed to at least the turbines assigned to the pumps. A heat exchanger is provided in which the fuel coming from the turbines is in a heat exchange with a fuel coming from a pump. A heat exchanger especially usable in the device for supplying fuel is provided.

Abstract: A recovery craft with a coupling arrangement captures, engages, and transports a defective or expended non-maneuverable spacecraft. The coupling arrangement includes a coupling mast (e.g. a telescoping pipe), a releasable rigid mount that secures one end of the coupling mast to the recovery craft, and spreader arms that are radially spreadable from the other end of the coupling mast. The spreader arms are initially radially inwardly retracted, and are inserted into an interface ring of the spacecraft. Then the spreader arms are radially outwardly extended to engage behind a protruding rim of the interface ring. A spring braces against the spacecraft. Next, the rigid mount is released and the coupling mast remains connected to the recovery craft only by a tension-transmitting cable. Thrusters of the recovery craft are activated to tow the spacecraft to a new target position, orbit, or trajectory.

Abstract: In a method of repairing a solar panel having a defective solar cell array, a solar cell replacement array is glued onto a defective solar cell array of the solar panel and is electrically integrated in the solar panel.

Abstract: A joint is provided for unfolding systems, e.g. for satellite solar generators that permits sufficiently large unfolding torque, low weight and small dimensions. A drive on one joint half acts on a small pulley to wind a cord on it. The other end of the cord is tautly connected to a large pulley that rotates on the hinge pin and is fixed to the second joint half. The large pulley rotates in the opposite direction of the small pulley when the cord is wound so that the second joint half folds away from the first joint half on the hinge pin into an unfolded state and is held In this state by a stop against the tension of the cord. The joint is used, for example, for unfolding joints for satellite solar generators that consist of two joint halves, a hinge pin and a drive.

Abstract: An injection element for a combustion component running on two propellants, includes a first, central injection channel, which is connectable to a first propellant supply for a first propellant, and a second injection channel, which annularly surrounds the first injection channel. The second injection channel is connectable to a second propellant supply for a second propellant. The injection element includes a third injection channel, which annularly surrounds the second injection channel and which is in fluid communication with the first injection channel.

Abstract: A thermal protection system suitable as a heat shield for a space vehicle includes a flexible insulation mat that is adhesively bonded onto the outer skin of the space vehicle, a cover layer made of at least one ply of a ceramic fiber composite material secured onto the insulation mat, and a coating of an inorganic material applied onto an outer surface of the ceramic cover layer. The cover layer is secured to the insulation mat by adhesive bonding, stitching with ceramic threads or the like, or by a snap fastener button connection. The ceramic fiber composite materials of the cover layer include inorganic fibers which are preferably oxides, carbides or mixtures thereof embedded in a matrix of the same compositional components, whereby the components can be selected appropriately depending on the requirements of the particular application.

Abstract: A rocket propulsion unit with an outer casing and an inner casing is described whereby the inner casing is arranged with space between the outer casing, and the inner casing forms a combustion chamber and has a contour adapted to the expulsion of propellants out of the combustion chamber with a constriction for forming a combustion chamber neck. The outer casing in contrast has a contour deviating from the contour of the inner casing.

Abstract: A centrally fed reflector antenna system has an effective reflector surface shaped so that the maximum of the copolar far field lies on the illuminated coverage area corresponding to the far field requirements, and the minimum of the copolar near field lies at the feed system, e.g. at the aperture of a feed horn.

Abstract: A joint is provided for unfolding systems, e.g. for satellite solar generators that permits sufficiently large unfolding torque, low weight and small dimensions. A drive on one joint half acts on a small pulley to wind a cord on it. The other end of the cord is tautly connected to a large pulley that rotates on the hinge pin and is fixed to the second joint half. The large pulley rotates in the opposite direction of the small pulley when the cord is wound so that the second joint half folds away from the first joint half on the hinge pin into an unfolded state and is held in this state by a stop against the tension of the cord. The joint is used, for example, for unfolding joints for satellite solar generators that consist of two joint halves, a hinge pin and a drive.

Abstract: A method for operating a space vehicle equipped with at least one device cooperating with a celestial body, wherein rotation of the space vehicle takes place around at least one axis of the space vehicle. The rotation of the space vehicle is slowed when the device cooperating with the celestial body is oriented substantially toward the celestial body. The device can be a solar panel intended to face the sun and produce electrical. energy.

Abstract: Described is a device for determining the attitude on board of a satellite (1) with a data transfer device for carrying out optical data exchange between at least two satellites (1, 3); a device for determining one's own attitude; a device for determining the directional vectors in an inertial co-ordinate system from one's own attitude and from attitude data of at least two satellites (1, 3), said attitude data having been transmitted by means of the data transmission device; a device for determining the directional vector directed to the satellites (1, 3) of which there are at least two, in a fixed-body co-ordinate system of the satellite; and a device for attitude determination from the directional vectors determined. Also described is a method for carrying out attitude determination.

Abstract: A liquid fuel rocket engine with a closed direct auxiliary flow cycle has a combustion chamber connected to each liquid fuel source through a respective main liquid fuel supply line. A turbo pump is provided in each main fuel supply line. The turbo pump is driven by a gas generator which is connected to a first bypass fuel supply line for supplying fuel to the gas generator. An exhaust gas duct (8, 9, 10) leads from the gas generator into at least one main fuel supply line for feeding gas generator exhaust gas into the main fuel supply line upstream of the turbo pump.

Abstract: A ring connects two rotationally symmetrical structural parts to form a rotationally symmetrical light-weight structure. At the transition between the two structural parts, there is a change of the slope of the meridian line of the light-weight structure. The ring comprises a surrounding layer of carbon fiber reinforced plastic CFRP with carbon fibers oriented in a circumferential direction of the structural parts.

Abstract: In a method for maintaining the orbital position of a geostationary satellite by compensating perturbational effects of interfering influences, a range of the satellite orbit is determined, relative to a space-fixed reference system, in which the perturbational effects on the satellite position by the interfering influences reaches a maximum. Position maintaining actuators of the satellite are activated within the determined range.

Abstract: The invention relates to a production method for a solar cell and to the solar cell itself which comprises an integrated bypass diode on the side facing away from the incidence of light and which can be produced in a simple manner by diffusion. A one-piece electric conductor serves to connect two successive solar cells in series and simultaneously effects the contacting of the corresponding bypass diode.

Abstract: A support structure includes at least one shaped component which is produced from a shape memory alloy and which, in a first operating state of the support structure, results in an increase in the strength of the support structure and, in a second operating state, results in a reduction in the thermal conductivity of the support structure. The first strut structure is surrounded by a second strut structure, which has a higher mechanical strength in comparison with the first strut structure, and the first strut structure is connected securely, at least at one of its ends, to the second strut structure. In addition, the first strut structure is connected to a holding device, and the second strut structure is releasably connected to the holding device by the at least one shaped component.

Abstract: The invention provides GPS navigational system for a satellite in space which comprises a front end section having an input for receiving GPS signals from a plurality of satellites, a digital preprocessor connected to the front end section for digitally preprocessing the GPS signals received from the front end section, and a signal processor connected to the digital preprocessor for decoding the GPS signals to determine a position of the satellite. An on-board computer is provided and a first data bus line connects the data processor and the signal processor for bi-directional data exchange therebetween and a second data bus line connects the signal processor and the on-board computer for bi-directional data exchange therebetween.