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: Thrust chamber housing for a driving mechanism for space travel applications which is fastened to an injection head with its first end and which includes a combustion chamber housing of a highly heat-resistant steel, a nozzle element of a platinum-iridium alloy, and an expansion nozzle housing of a highly heat-resistant steel, whereby the combustion chamber housing is welded through a first intermediate ring with the nozzle element and the nozzle element is welded through a second intermediate ring with the expansion nozzle housing by means of welded connections, whereby the first and the second intermediate ring are made of a platinum-rhodium alloy.

Abstract: Thrust-chamber assembly has an expansion nozzle and a combustion-chamber wall, to which an ejector head is affixed. The part of the combustion-chamber wall adjacent to the injector head comprising a precombustion-chamber wall, in which the combustible materials delivered to the assembly first form a cooling film. There is a heat-conducting layer in at least one area of the outside of the precombustion-chamber wall and in addition, it has a covering of platinum or gold.

Abstract: A three-axis attitude control for a low-orbiting satellite. A sensor which measures in two axes is a magnetometer, and a satellite is positioned on an inclined orbit at an inclination angle of approximately 25 degrees to approx. 90 degrees. The satellite has been provided with an overall spin by spin wheels, and actuators generate torque on all three axes of the satellite. Accordingly, this is applicable to three-axis attitude control of a low-orbiting satellite that includes a sensor which measures in two axes and that includes one or several spin wheels.

Abstract: A method of determining the position of geostationary satellites by means of signals of at least one navigation satellite. A determination is made of data concerning the transit times of the signals from the at least one navigation satellite to the geostationary satellite by a device of the geostationary satellite, and a determination is made of navigation data of the at least one navigation satellite by an independent navigation device. A determination is made of data concerning the system time of the at least one navigation satellite by an independent navigation device, and a data exchange occurs between the geostationary satellite and the navigation device in order to determine position data of the geostationary satellite from the transit times, the navigation data as well as the system time of the at least one navigation satellite.

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 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: An inductively coupled high-frequency electron source is disclosed having a plasma chamber, which is open at least at a first end, the total surface of the open regions of the plasma chamber defined by A0, and having a gas inlet for a gas to be ionized, as well as a high-frequency coil. The interior wall of the plasma chamber is formed at least partially by conductive regions which are connected with a current source, the total surface of the conductive regions defined by Ac, and the ratio of the surface amounts A0 to Ac not exceeding a defined maximal value.

Abstract: A high-frequency electron source includes a discharge chamber having at least one gas inlet for a gas to be ionized and at least one extraction opening for electrons. The high-frequency electron source also includes a first electrode at least partially surrounding the discharge chamber and a keeper electrode at least partially surround the discharge chamber. The first electrode and the keeper electrode are configured to provide a high-frequency electric field therebetween.

Abstract: A combustion chamber structure (1) comprising a plurality of cooling ducts (31, 41) extending in the longitudinal direction of the combustion chamber structure (1), whereby the combustion chamber structure (1) is rotationally symmetrical in relation to an axis (4) and comprised of an outer structure (11) and a base body (16) of the combustion chamber. The base body comprises ribs (25) preferably extending in the direction of the axis (4). The ribs are arranged in the peripheral direction of the combustion chamber structure and at least one first cooling duct (31) extends in the interior of the ribs.

Abstract: A combustion chamber for a rocket engine expels a hot stream of gas and has a cooling device. The inner wall of the combustion chamber adjoins the cooling device and contains depressions formed in such a way that the stable outer layer of the stream of gas that forms in the proximity of the inner wall of the combustion chamber during operation of the combustion chamber is destabilized in the area of the depressions.

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: A method is provided for soldering at least two metallic components, one end of each of the metallic components being soldered with the aid of a tube-shaped connection piece. Furthermore, a use of such a soldering process is provided for soldering a wire to a metallic contact, specifically for a use in the case of cryogenic devices.

Abstract: A person can safely descend from a burning high-rise building or the like using an inflatable flying body that has a hollow conical form in an inflated deployed condition, but is deflated and folded into a backpack form in a stowed condition. The flying body includes an upper stabilizing ring, a lower nose structure with a pneumatic damping body, spoke struts extending conically therebetween, a cover skin covering the abovementioned inflatable components to form the conical outer surface and provide aerodynamic braking drag, and gas generators to inflate the inflatable components. A person straps on the apparatus in the stowed backpack form and pulls a handle to actuate the gas generators for inflating the apparatus, whereby the expanding apparatus ejects the person from the building and then orients itself in a nose-down attitude during the descent. The pneumatic damping body damps and dissipates the landing impact energy.

Abstract: An inertial sensor includes an inertial reference for determining the attitude and position of a satellite or satellite parts. A test mass is situated in a space which is essentially free of electric and magnetic fields and is enclosed by a housing, and optical measuring sections are set up between reference elements on the housing and on the test mass, for determining the attitude and/or position of the test mass relative to the reference elements on the housing. A measuring arrangement is situated outside the housing for the optical measuring sections. The optical measuring sections are constructed as optical interferometric measuring elements; and the attitude and position of the test mass can be adjusted by means of the pressures of light exerted on the optical interferometric measuring sections upon the test mass.

Abstract: A solar simulator is provided having a radiation source for generating radiation with a spectral (energy) distribution that largely corresponds to the spectral distribution of sunlight. At least one filter is arranged in the region of the radiation source. This filter suppresses long wave or short wave radiation components of the radiation source. The filter is movable, basically perpendicular, to the irradiation direction of the radiation source. An irradiation plane capable of accommodating objects to be irradiated is set at a distance from the radiation source and the at least one filter such that the radiation coming directly from the radiation source, as well as the at least one filter, impinge on the irradiation plane as basically homogenous radiation of a punctiform light source.

Abstract: Two structural components are releasably connected to each other by a clamping mechanism (CM) which engages two interface rings (9, 10) secured to the respective structural component. The clamping mechanism is formed by tensioning elements (5) held together by at least one, preferably two tensioning members such as straps (1, 2). A lock (15) with two hinged tensioning levers (18, 19) hinged at (21) to a mounting (17), holds the tensioning strap or straps releasably together. For this purpose each strap end is journalled by a journal bolt (3, 4) to the respective tensioning lever (18, 19). Locking elements (25, 26, 28, 30) hold the tensioning levers (18, 19) in a locked position. An electromagnetic drive or the like is used to unlock the tension levers for releasing the tensioning strap or straps in a controlled manner without completely opening the ring formed by the clamping mechanism. The position of the journal bolt (3, 4) relative to its tensioning lever (18, 19) is adjustable by an adjustment screw (22).

Abstract: An ignition system for combustion chambers of rocket engines has a first fuel tank for a first fuel constituent and a second fuel tank for a second fuel constituent, both of which are separated from the fuel tanks of the rocket engine. Feed pipes (3, 4) for the respective fuel constituent are arranged between the igniter and a fuel tank.

Abstract: A separation frame for mounting and separating satellites in a launch vehicle, includes two congruent frames (10, 12) are arranged one inside the other. The frames are connected to each other by means of a swivel joint.

Abstract: An extendible solar generator has an extendible solar cell structure and an extendible support array structure which has a first cross member and is connected with a stowage housing for the solar cell structure. The support array structure can be rolled out independently of the solar cell structure and has guiding devices for rolling out the solar cell structure after the array structure has rolled out.