Abstract: A plate burner for combusting hydrogen with air as an oxidizer forms a wall portion of a combustion chamber for example of a gas turbine. The plate burner is so constructed that air and hydrogen are separately guided to the downstream surface area facing into the combustion chamber for forming a large number of diffusive microcombustion flames, thus achieving a very low mixing scale simultaneously with a high nixing intensity. The number of diffusive micorcombustion flames is so selected that the NOx content in the exhaust gas from the combustion chamber is at the most 10×10−6 cubic foot per cubic foot of exhaust gas. The hydrogen enters the entrance area into the combustion chamber either through a porous wall, and air is injected into the hydrogen environment to form inverse diffusive microcombustion flames or the hydrogen is injected through a multitude of fine holes into high velocity air jets forming regular diffusion flames.

Abstract: In a method and evaporator device for evaporating a low temperature liquid medium, such as hydrogen for example, the hydrogen is first evaporated and at least partially superheated in a forward-flowing first channel, and is then directed to flow back in the opposite direction in a second return-flowing channel. The second channel is especially interposed between the first channel and a passage through which flows a heat-providing medium such as a hot exhaust gas. Thus, the superheated hydrogen flowing in the second channel serves as an intermediate layer for heat transfer from the heat-providing medium through the hydrogen in the second channel to the low temperature, initially liquid hydrogen in the first channel. The heat exchange surfaces in contact with the heat-providing medium are not directly adjacent the extremely cold surfaces in contact with the in-flowing low temperature liquid hydrogen, and the superheated hydrogen acts as a buffer between the hot side and the cold side of the evaporator.

Abstract: A fuselage is substantially simultaneously fabricated, equipped and outfitted in an assembly area including adjacent riveting, equipping and outfitting zones. The riveting zone includes an external riveting apparatus working from the outside of the aircraft fuselage, and an internal riveting apparatus working from the inside of the fuselage to fabricate and join a first fuselage section to an initial structure. The first fuselage section is moved from the riveting zone into an equipping zone, wherein equipment, such as pipes, ducts, hoses, pumps, blowers and structural components and fittings of the aircraft, is installed in the first fuselage section, while simultaneously a second fuselage section is being rivet-joined onto the first fuselage section in the riveting zone. The second fuselage section is moved from the riveting zone into the equipping zone, and the first fuselage section is moved from the equipping zone into the outfitting zone.

Abstract: A temperature regulating arrangement (7) at least partially surrounds a fuel or oxidizer storage tank (1). The tank (1) is divided by a polymer membrane (3) into a first partial chamber (2) receiving the fuel (2′) therein, and a second partial chamber (4) receiving a gaseous pressure medium (4′) therein. The temperature regulating arrangement (7) includes thermal insulation, at least one heater, at least one heat sensor, and a temperature control and regulating unit. By heating the second partial chamber containing the gaseous pressure medium, any fuel vapor permeating through the membrane (3) from the first partial chamber (2) into the second partial chamber (4) is prevented from condensing within the second partial chamber (4). The permeation process is also limited. It is simply necessary to maintain the second partial chamber (4) at a temperature a few degrees Celsius higher than the temperature of the liquid fuel.

Abstract: A system for achieving a boundary layer control by sucking at least a portion of the boundary layer air flow through perforated or porous suction areas on the outer skin of the wings or other areas of the aircraft, includes one or more jet pumps (7) arranged in the bypass engine (5) of the aircraft, and a system of suction conduits (4) connecting the jet pumps (7) to suction channels (3A) communicating with the perforated or porous suction areas (3). Each jet pump (7) includes an ejector pipe (101) that is driven by an external surrounding driving jet (8) or by an internal driving jet (8) flowing through an internal jet pipe (15). The jet pumps (7) are arranged at selected locations in the air intake upstream of the fan, in the bypass channel (18) just downstream of the fan, in the bypass channel near the outlet end thereof, in the core hot gas channel (19) upstream of a compressor assembly, and/or in the core channel downstream of a turbine assembly.

Abstract: A flexible coupling for flexibly connecting two rotary drive shafts includes a first coupling flange connected to the first shaft, a second coupling flange connected to the second shaft, a flexible disk arranged between the two coupling flanges, and four connector bolts that respectively connect the two flanges to the flexible disk. A first pair of the bolts is securely connected to the first flange and to the flexible disk, while passing with free play through a clearance hole in the second flange. A second pair of the bolts is securely connected to the second flange and to the flexible disk, while passing with free play through a clearance hole in the first flange. In ordinary operation, the connection and force transmission between the coupling flanges is carried out through the flexible disk.

Abstract: An electrostatic ion propulsion engine for satellites and spacecraft is equipped with an electron source for neutralizing the propellant gas ion beam or jet emitted by the engine. The electron source includes an anode housing, a hollow cathode tube with gas flowing therethrough, a cathode element at the outlet end of the cathode tube within the interior space of the anode housing, and a pin- or rod-shaped auxiliary electrode arranged along the lengthwise axis in the hollow cathode tube. An ignition pulse is applied to the auxiliary electrode relative to the cathode tube, which causes a pulse discharge in the cathode tube, and in turn ignites the gas discharge between the anode and the cathode which generates the electron current.

Abstract: A system for transporting an ill or injured patient includes a stretcher in combination with a plurality of medical care modules that respectively include medical devices such as an infusion pump, an oxygen supply device, a defibrillator, an EKG unit, or the like, and medical and first aid supplies such as bandages, splints, IV supplies, drugs, medical instruments, and the like. The stretcher includes a frame and a patient support surface, as well as module bays provided under the frame or a module carrier removably mounted on the frame. The several medical care modules each have the same dimensions and configuration so that they are modularly interchangeable to be received in any one of the module bays or on the module carrier. When the medical care modules are slidingly pushed into the module bays, electrical contacts are engaged to connect the modules with an electrical power supply and a data transfer bus, through the stretcher.

Abstract: A device (100) for producing fullerenes includes an IEC vacuum chamber (110) which has a central grid-like electrode (112) and a conductive outer shell (111) that are connected to a pulsed source of high voltage (114) and provide an electric field within the chamber (110). The applied voltage supports the creation of a plasma at the inner core of the chamber near the electrode (112). A carbon-based gas, which is introduced into the chamber (110), possibly along with an inert buffer gas, id dissociated into component carbon and hydrogen ions that are separated and the carbon ions recombined into fullerenes that appears as a soot. The device (100) includes a soot extraction mechanism for removing and collecting the fullerenes.

Abstract: A double pane window for an aircraft cabin has a passive air dehumidifying channel (5, 5A) that is in heat exchange contact with a window metal frame (1) which is in turn in heat exchange contact with the atmosphere outside the aircraft. The air dehumidifying channel (5, 5A) communicates through a first air flow port (6) with the cabin space and through a second air flow port (7) with a space enclosed between the double panes.

Abstract: A method of reducing the bending moment effect of wind gust loads acting on the wing of an aircraft involves adjusting the aerodynamic configuration of the wing so as to alter the distribution of lift generated by the wing during phases of flight in which critical wind gusts are expected to occur. Particularly, during climb and descent phases of flight below cruise altitude, the lift generated by outboard portions of the wings is reduced while the lift generated by inboard portions of the wings is increased. Thereby, the 1 g basis load acting on the outboard portions of the wings is reduced, and consequently the total load applied to the outboard portions of the wings, resulting from the 1 g basis load plus the additional wind gust load, is correspondingly reduced. This leads to a reduction of the bending moments effective on the wings, and of any rolling moment effective on the aircraft.

Abstract: When a turbine engine is operated near the ground, for example on a stationary static test stand, the ground effect as well as excessive lateral wind effects can lead to instabilities and unacceptable flow conditions of the air flow entering the air intake of the engine. A method for stabilizing or preventing such instabilities in the engine intake air flow involves preventing the generation or full development of a spiral vortex extending between the ground and the engine air intake. Specifically, by positively introducing air into the vortex core of any spiral vortex being formed, the vortex is destroyed and full development of the vortex is prevented. An apparatus for carrying out the method includes an air permeable element arranged between the ground and the engine air intake, such that a flow of air is provided through the air permeable element into the core of any spiral vortex being formed on the surface of the air permeable element.

Abstract: Connectors for joining protective ducts and/or hoses for the installation of insulated electrical conductors and/or cables in an aircraft are equipped with lids that are easily opened even without a tool. The lids are preferably permanently secured to the connectors. The lids are constructed as roll-up tapes or as flat or curved plates. The curved plates are held in place in the closed condition by springs. A flat plate lid is held in place, for example by a circlip, or by a leg spring or by a hinge.

Abstract: An apparatus advantageously influences the wing root airflow along the wing root of an aircraft having a high lift system including leading edge slats provided on the main wings. The apparatus includes a respective vortex generator arranged on the inboard end of each leading edge slat in the area of the wing root, and further includes a respective transition fairing arranged on a separation edge that is let into the leading edge of the wing root and that borders along the inboard edge of the respective slat. The vortex generator is a rigid member fixed to the leading edge slat and may be in the shape of a horn, a disk, or a winglet. The transition fairing may be a rigid member fixed to the wing root along the separation edge, or may be a flexible elastic member that can be inflated to have a variable outer contour. The present system avoids the need of additional independently movable auxiliary flaps, and thus achieves a reduced weight, complexity, and maintenance requirement.

Abstract: A lightweight pallet especially for holding payloads in a spacecraft has a sandwich construction with a core grid of longitudinal carrier beams and cross-connectors mounted between a top flat sheet metal plate and a bottom flat sheet metal plate and a bottom sheet metal plate. A cross-beam is secured to the front end and to the rear end of the pallet. The cross-beams carry journal pins for mounting the pallets to respective yokes in the cargo bay of a spacecraft. The cover plates are provided with cut-outs forming square or rectangular holes with rounded corners. Hole patterns or threaded holes are provided for the connection of junction plates and payloads to the pallet. The junction plates are secured where the longitudinal beams and the cross-connectors meet. At least one of the two laterally outer longitudinal beams has a recess for the recessed mounting of payload supply unit such as a power supply. The recess is then closed again by a plate capable of taking up shear stress.

Abstract: A YZ-latch for holding down a piece of freight on a loading floor in an aircraft which has a base holding an axle stub which in turn has mounted thereon two rollers for rolling contact with the freight piece. One roller holds against lateral displacement in the Y-direction. The other roller holds against vertical displacement in the Z-direction. Free movement is permitted in the X-direction. Either the axle stub with fixed rollers is rotatable, or the rollers are rotatable on the fixed axle stub, or at least one roller or both rollers are rotatable on a rotatable axle stub.

Abstract: A system of interconnected heating conductors, suitable for preventing freezing of water lines in an aircraft for example, includes a plurality of heater units (1, 12) electrically coupled together by respective coupling plugs (9, 10). Each heater unit comprises one or more heating conductor bands or cables (2, 21, 22), with a respective socket contact plug (9) connected to one end thereof and a respective pin contact plug (10) connected to the other end thereof. Each plug (9, 10) includes a housing (6) wherein the conductors of the heater band (2) are crimp-connected to electrical connectors (7), which include pin contacts (723) in the case of the pin contact plug (10) and socket contacts (77) in the case of the socket contact plug (9). The housing (6) is completely filled with a sealing compound (19) which is injected through a fill hole in the housing wall.

Abstract: A device for fastening an injection element 4 with its foot 5 in a hole of a base plate 1 of an injection head 2 of a rocket engine, the foot 5 is tapered in steps up to its end. A first shoulder 7 of the foot abuts against the base plate 1; a thread (6) screwed into the base plate 1 is present after the first shoulder 7; the thread 6 is followed by a second shoulder 8 and then by a first, smooth cylindrical piece 9. This is followed by a third shoulder 11, on which a solder ring 12 made of a gold alloy is seated. A second, smooth cylindrical piece 13, which has a solder gap 13a between it and the corresponding hole in the base plate 1, follows after the third shoulder 11 up to the end. A process for fastening the injection element 4 provides for the solder ring 12 being first placed on the third shoulder 11, after which the injection element 4 is screwed into the base plate by means of a hexagon 22, and the injection head 2 is subsequently heated to about 1,035.degree. C.

Abstract: A FMCW radar tank level gauge (14) that measures a level (13) in a tank (10) by obtaining a set of phase shift data points of mixed transmitted waves and received waves. The set of spectral data phase shift values has a received target marker indicating the level. An adaptive set of masking threshold phase shift values corresponding to at least a portion of the spectral data phase shift values are calculated. The adaptive set of masking threshold values are compared with the corresponding spectral data values to identify at least one spectral data value associated with the level. The level of the tank is calculated from at least one spectral data value and the level of the tank is reported.

Abstract: In a method and evaporator device for evaporating a low temperature liquid medium, such as hydrogen for example, the hydrogen is first evaporated and at least partially superheated in a forward-flowing first channel, and is then directed to flow back in the opposite direction in a second return-flowing channel. The second channel is especially interposed between the first channel and a passage through which flows a heat-providing medium such as a hot exhaust gas. Thus, the superheated hydrogen flowing in the second channel serves as an intermediate layer for heat transfer from the heat-providing medium through the hydrogen in the second channel to the low temperature, initially liquid hydrogen in the first channel. The heat exchange surfaces in contact with the heat-providing medium are not directly adjacent the extremely cold surfaces in contact with the in-flowing low temperature liquid hydrogen, and the superheated hydrogen acts as a buffer between the hot side and the cold side of the evaporator.