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 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: 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: 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: 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 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: 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 wall element has a noise attenuating characteristic and is suitable for use as an aircraft cabin interior panel element that is mounted directly on the aircraft fuselage structure. The wall element includes a rigid lightweight composite panel having a core arranged between two cover layers, and an outer layer arranged adjacent and spaced away from one of the cover layers. The core and the cover layers of the composite panel are air permeable in a direction through the thickness of the panel, while the outer layer is non-air-permeable and is relatively soft and flexible. The outer layer is connected to the composite panel preferably only along the perimeter edge thereof. The non-permeable outer layer faces the aircraft cabin space, while the permeable composite panel is mounted on the fuselage structure. With this structure, acoustic vibrations of the fuselage, to which the wall element is attached, are attenuated and do not result in substantial noise radiation from the outer layer into the cabin.

Abstract: In order to reuse dishes, cutlery, glassware and other food service utensils onboard an aircraft, a washing apparatus is provided as a part of the food service system onboard the aircraft. The apparatus includes a service trolley and a washing unit that may be coupled together to form a washing chamber within the trolley. The washing unit is installed within a trolley parking bay in a galley of the aircraft and is connected to a water supply and a power supply. The trolley is equipped with racks for receiving the dirty utensils, and the washing unit is equipped with water spray arms that reach into the trolley into clearance spaces between the racks. The dirty utensils are collected from passengers directly into the service trolley, which is then wheeled into position in the trolley parking bay, and coupled to the washing unit. Thereby, the utensils may be collected, cleaned, stored, and reused, with only minimal handling, cost, and space requirements.

Abstract: A cable binder includes a cable binder head (1) and a cable binder band (3) extending therefrom. The cable binder head includes first and second planar contact surfaces (11, 18) that intersect each other at a contact angle (.alpha.) in the range from 145.degree. to 160.degree., and are adapted to establish a substantially uniform and continuous contact of the cable binder head (1) with the substantially circular outer contour of a cable or other elongate component (6) that is to be secured. The cable binder head has an opening (2) extending at an incline therethrough and adjoining an edge of the contact surface (11). This arrangement ensures the maximum contact of the binder band (3) and contact surfaces (11, 18) of the head (1) with the outer contour of the component (6) being secured, and minimizes or eliminates the formation of a triangular open gap (4) between the binder head and the component (6).

Abstract: A leading edge structure for an aerodynamic surface includes a support structure made of fiber-reinforced synthetic material and a skin structure made of metal mounted on the support structure. The support structure includes an inner laminate, an outer laminate, and longitudinally extending tubes and channels arranged between the inner and outer laminates, as well as a synthetic foam filler material in the spaces between the tubes, channels, and laminates. The skin structure includes an outer skin having perforations, especially in the form of suction holes, an inner skin, and spacer members interconnected therebetween so as to form a substantially form-stable metal skin structure. Respective holes pass through the inner skin, the outer laminate, and the walls of the tubes and channels in order to communicate the suction hole perforations of the outer skin with the interior spaces within the tubes and channels. The skin structure is adhesively bonded to the support structure.

Abstract: An injector air outlet includes a temperature sensor and a smoke sensor to simultaneously carry out the functions of air recirculation and temperature and smoke monitoring within a closed interior space, such as a passenger cabin or a freight or cargo hold in an aircraft. The injector air outlet includes a housing wall (2) with an injector mixing chamber (3) therein. A primary supply air inlet (4) receives primary supply air (5) from the aircraft's air distribution duct network, and blows the primary supply air through an injection nozzle (7) into the mixing chamber (3) so as to create a reduced or negative pressure in the mixing chamber. Cabin exhaust air (10) is sucked through a secondary air inlet (9) and a secondary air channel (8) into the mixing chamber (3), due to the reduced pressure or suction effect therein. The primary air and secondary air are mixed together and then ejected forcefully back into the cabin or cargo hold.

Abstract: A bi-directional power conversion system interconnects hydraulic and electrical power systems on-board a vehicle such as an air-craft, whereby the power conversion system can selectively convert available electrical power to needed hydraulic power or vice versa. The power conversion system includes a hydraulic machine (15) connected to the hydraulic system (10) of the vehicle, an electrical machine (20) connected to the electrical system (3) of the vehicle through a power converter and control unit (22), a rotational drive shaft (14) mechanically interconnecting the hydraulic machine (15) and the electrical machine (20), and a priority and safety control unit (26) that controls the operation of the system.

Abstract: A door and its frame especially in an aircraft are constructed for circulating air through the structure for preventing cold air from forming near the door in an aircraft cabin. For this purpose at least one air flow channel is provided in the door construction. The air flow channel communicates with at least one inlet port with at least one outlet port so positioned that air circulation is maintained through the door structure. The outlet port passes preferably through a cabin floor for discharging cold air into a space below the cabin floor.

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, 14) electrically coupled together by respective extension cables (3) and electrical coupling elements (42). Each heater unit comprises one or more heating conductor bands, tapes or strips (2, 21, 22) connected to respective connection modules (5, 51, 52, 52', 53) at the ends thereof. The connection modules may connect together several heater bands within one heater unit, and may connect the terminal ends of the heater bands of one heater unit to the extension cables by which several respective heater units may be connected together. Each connection module includes a housing (6) enclosing an inner chamber (61) therein, and at least one electrical connector element (7) such as a crimpable connector fixed within the housing (6).

Abstract: A window for an aircraft cabin has a first pane (3) with a high fatigue strength on the inside facing the cabin and a second pane (4) with a lower fatigue strength smaller than the first fatigue strength on the outside facing the atmosphere. The space (3A) between the window panes (3, 4) is sealed but connected through a pipe to an air pressure controller responsive to the atmospheric pressure. The pressure controller may be an air pump (12) or variable volume chambers (19, 20) for keeping the pressure in the space between the panes at the prevailing atmospheric pressure without actually venting the space to the atmosphere.

Abstract: In a passenger service unit, particularly in a passenger cabin of an aircraft, comfort and service elements such as a reading lamp, a flight attendant call button, a loudspeaker, an air nozzle, an oxygen mask and generator, optical display elements, are integrated into a service column. Feeder lines between a main supply line and the passenger service columns are flexible to facilitate the mounting or placement of the columns as a complement to a passenger seat. The column is positioned in the lateral area of a seat to which the column is allocated.

Abstract: An apparatus for detecting high frequency interference radiation signals, such as radio frequency emissions, on board a passenger aircraft includes at least two receiver units for receiving and measuring the interference radiation signal, and a monitoring unit for evaluating the signal measurement results. Each receiver unit respectively includes at least one antenna, the monitoring unit includes an interference computer, and a digital data signal transmission path connects the receiver units to the monitoring unit. The interference computer evaluates the data signals received from the receiver units to determine the location of an interference radiation source within the aircraft, and indicates corresponding location and warning information on a display unit connected to the interference computer.