Abstract: A structural component, especially a substantially hollow aircraft structural component such as a wing or tail section having an upper chord or shell and a lower chord or shell interconnected to form a substantially hollow bending beam in use, is so constructed that the chord or shell which is primarily taking up tension stress is made of fiber reinforced composite material, while the other chord or shell which primarily takes up compression stress is made of metal. In an aircraft wing the upper wing shell will be made of metal and the lower shell will be made of fiber reinforced composite material. However, the tail plane and elevator assembly will have an upper shell made of fiber reinforced composite material while the lower shell will be made of metal.

Abstract: Digital data in the form of a light signal is to be transmitted through an optical network of optical waveguides joined together at passive node points. The node points split or branch off the light signal from a primary waveguide into secondary or branch waveguides. The passive node points include special coupling surfaces respectively a coupling body including a flat surface and a prismatic structure arranged at the junction or head end of the secondary waveguide. The respective coupling surface or coupling body achieves an exactly defined maximum reflection of the light in the primary waveguide, i.e. constrains a major proportion of the light within the primary waveguide. Thus, maximum light power is maintained and transmitted along the primary waveguide, and at each node point a defined minimum light power is coupled into the respective secondary waveguides.

Abstract: The invention relates to a system for removing the heat that is incident upon an aircraft, and especially a supersonic aircraft, during flight. The incident heat is generated by the constant heating effect of aerodynamic friction on the outer skin of the fuselage, by compression heating at the ram or stagnation point and stagnation edges of the aircraft fuselage, and by the heating of external air as it is compressed to cabin pressure. In the present system, the used cabin air is exhausted out of the cabin through a space between the cabin interior panels and the fuselage outer skin, where the airflow absorbs the heat incident through the outer skin and is heated to approximately the temperature of the outer skin. Next, the heated airflow is preferably first filtered through a filter and is then expanded and cooled through an expansion turbine. The output shaft of the turbine can drive a generator to recover useful electrical energy.

Abstract: A passenger service terminal, for example in an aircraft, includes comfort and service components such as a reading lamp, a flight attendant call button, a loudspeaker, an air nozzle, an oxygen mask, an oxygen generator, and an optical display element incorporated in a separate support bail or support rod that cooperates with but remains separate from a passenger seat. An air supply duct and electrical and optical conductors pass through seat components. A bail or bow (8) forming a support, at least partly, frames the backrest and holds at least certain service and comfort components while simultaneously forming a privacy hood (19). Alternatively, side rods (8A) are arranged laterally and alongside the backrest (5) to hold lateral curtains (19A) also providing some privacy. The side rods are preferably hollow to hold an air supply duct, wiring and optical conductors. A seated passenger can easily and comfortably operate the service functions without disturbing a neighbor.

Abstract: A water supply system for an aircraft includes a ventilatable water tank, a water supply line to supply water to water-using devices such as galleys and handwash basins, fill and drain lines, and a multi-function valve for carrying out filling and draining, and other system functions. The multi-function valve is interposed between the water tank, the water supply line, the fill line, and the drain line. The valve includes a filling port connected to the filling line, a tank port connected to the water tank, a supply port connected to the supply line, a drain port connected to the drain line, and preferably also a tank overflow port and an outside overflow port. The valve includes a shut-off element arranged within a housing, wherein the shut-off element has therein a water passage which includes first, second, and third branches, and preferably also an air passage.

Abstract: An apparatus is provided for removing stackable units containing food service items from a container having the form of a typical freight container, on board an aircraft. The apparatus cooperates with means for further transporting and then delivering the stackable units to an aircraft galley, and cooperates with a program controllable unit to allow the programmable handling of the stackable units. Arranged in the container (1) is a plurality of partition walls (10), each having a plurality of shelf ledges (15) to form a plurality of storage compartments (13) on the two opposite sides of an access alley (9). A handling unit (12) including a tower (22) on an undercarriage (12A) rides along rails (11) in the access alley (9). The tower (22) includes a plurality of receiver bins (19), with a motor driven engaging and entraining member (21) respectively arranged in each receiver bin (19).

Abstract: It is a problem in conventional aircraft having a fuselage of substantially circular cross-section, that a conventional lower deck would have an insufficient standing height for passengers if the lower deck were to be equipped as a passenger cabin space including seats, sleeping cabins, or other passenger service facilities. In the present aircraft, the lower deck floor (2, 2') is depressed or dropped at least in a certain area (14) that will form an aisle (16), so that the free height of the lower deck in the area of the depressed floor provides at least the normal standing height (HS) for a person. A module (15, 15') containing passenger service facilities is arranged in the lower deck area at least to one side of the depressed floor area. A modular construction provides a great flexibility and convenience in reconfiguring a lower deck from a cargo hold configuration to a passenger cabin configuration and vice versa.

Abstract: A method and an apparatus are provided for optimizing the aerodynamic effect of the airfoil of an aircraft by defined changes in camber. The method includes the following steps:a. determining the flow for the flight condition caused by the change in camber,b. comparing the ascertained characteristic values with stored nominal reference values for an optimal flow,c. forming differential values between the characteristic values and the stored nominal reference values,d. deriving actuator signals from the differential values, ande. changing the camber by motor, based on the actuator signals, for minimizing the differential values.The optimum wing flow is thereby maintained more exactly. For transonic wings, the position and strength of compression shocks is also effectively controlled, which leads to a reduction of the direct shock induced separation.

Abstract: In an energy generating system, which is preferably suitable for satellites and space stations, a total of four Stirling engines are assembled together into a cross-shaped unit, at the center of which is arranged a cross-gear drive that is acted upon by the pistons of the Stirling engines. The heaters of the Stirling engines are impinged upon by solar energy. The incident sun's rays either are guided by a radiation trap that is arranged in the center of a collector onto an umbrella-shaped tubular heating heat exchanger, or are absorbed by disk collectors that are arranged inside a fusion heat reservoir.

Abstract: A conveyor system for transporting menu boxes (14) in an aircraft is equipped with at least one heater element (17) or groups of such elements (17/17A . . . ) which tilt automatically into spaces (16) between neighboring boxes (14) or pairs of boxes within the conveyor which is stopped during heating. When the heating is completed the elements (17) are again tilted into a rest position (17') outside the conveyor. Induction heating is preferably used.

Abstract: A conductor channel is used for the laying of insulated electrical conductors (3) in an air- or spacecraft, whereby the channel can be integrated into a conductor channel system. The conductor channel is made of at least one open hollow section (2), wherein the conductors (3) are held by a retaining strip (8) held in place by edges (7) of the hollow section (2). The strip (8) closes the hollow section. A tension relief element (11) for the conductors (3) is arranged at each channel end. A mounting (13) having upper and lower parts (20, 20') for electrically grounding the hollow section (2) is installed to hold the hollow section (2) next to each tension relief element (11). Spacers (14) may be distributed between the two mountings (13) along the length of the hollow section (2). The mountings (13) are fastened to a support (23). The hollow section (2) is fixed in and fastened to the mountings (13), whereby the free ends of the hollow section .

Abstract: A power supply circuit generates an alternating driving voltage for switching a pane or panel between a transparent state and a substantially opaque state. The pane or panel is, for example, a window with a variable transparency in an aircraft cabin divider. The circuit converts a D.C. voltage that is available, for example, from the aircraft's on-board power supply, into a positive and negative D.C. voltage. These voltages pass through a push-pull output amplifier that is under the control of a clock signal generator to produce the alternating driving voltage at the output of the push-pull amplifier connected to transparent electrodes of the pane or panel that contains liquid crystals. Status sensors may influence the operation of the clock signal generator and/or of the push-pull amplifier.

Abstract: A vacuum plumbing system especially in an aircraft equipped with jet engines, is provided with a tap air supply source (4) that receives the tap air from the engine exhaust and is connected with a nozzle (1A) of at least one ejector or jet air pump (1) while the suction port (1C) of the pump (1) is connected through ducts or pipes (7, 11, 12) to a refuse collecting duct (15) either directly or indirectly through refuse collecting tank (9). Filters in the tank and conveying pumps are thus avoided.

Abstract: An air supply system for an aircraft cabin reduces the concentration of contaminations of the air in the cabin by a flexibly controllable valve system that comprises pairs of valves which on the one hand are ganged to respective air openings. One valve of a pair is connected to a fresh air or mixed air supply line. The other valve of a pair is connected to a suction or exhaust duct. Thus, depending on which valve in a pair is open and which is closed, the respective air opening can function as an air outlet for supply of mixed or fresh air into the cabin or as a suction port. Such a system permits a flexible volume control of the supply of fresh air into selectable cabin sections as well as a flexible volume control for the removal of used air from respective cabin sections. Additionally, it is now possible to increase the size of the non-smoking section at the expense of the smoking section or vice versa simply by a respective valve control.

Abstract: A two-part screw-type coupling suitable for coupling together electrical and/or mechanical components in an aircraft, for example, has a rotation lock feature that prevents the unintentional spontaneous loosening of the screwed connection as a result of vibration and shock. The coupling includes a generally cylindrical support body and a collar nut rotatably mounted thereon and retained by a retaining element. A rotation lock element locks the collar nut and the support body together against relative rotation. The lock element includes a spring or a spring-loaded ring, which is rigidly connected to the collar nut or the support body and which applies a sufficient clamping tension against the other part of the coupling to achieve the desired locking function. The rotation lock can provide a finely stepped static adjustment and locking, or a fine step-less dynamic adjustment and locking of the tightening torque of the collar nut on a component to which the coupling is screw-connected.

Abstract: A waste water drain apparatus (1) is to be attached to the fuselage belly (2) of an aircraft. The apparatus (1) essentially includes a drain pipe (3), an aerodynamically shaped fairing (7) enclosing the drain pipe (3), an attachment flange (6) for connecting the apparatus to the aircraft, at least one temperature sensor (9), and either at least one heating element (8) or hot air inlet (13) for heating the drain pipe (3). An inlet end (4) of the drain pipe (3) is to be connected to a waste water system of the aircraft. An outlet end (5) of the drain pipe (3) exits rearward at the trailing edge of the fairing so that the lengthwise axis of the drain pipe outlet is substantially parallel with the air flow during flight.

Abstract: A passenger service apparatus in a passenger cabin, especially of an aircraft, includes a service module having comfort and service elements such as reading lamps, flight attendant call buttons, loudspeakers, air nozzles, and the like. The service module is mounted on a spring-biased yielding support arm below the bottom shell of an overhead baggage compartment. An end of the support arm is mounted on the cabin wall and extends generally inwardly toward the middle of the cabin, to position the service module generally centrally above the passenger seats that are to be served by the service module. Connector lines such as electrical conductors and air conduits run along the support arm to connect the service module to a service channel extending along the length of the passenger cabin and including electrical conductors, an air duct, and the like.

Abstract: An effective grounding of electrical equipment, electrical cables, housings, and the like, is accomplished by grounding lugs that are initially formed as an integral part, for example, of a grounding sleeve of electrically conducting material that surrounds a protective cable casing of electrically conducting material in a crimping manner. The lugs are only bent out of the sleeve when needed. A grounding conductor is then secured to the lug. The grounding lugs may be incorporated in all systems that are provided for protection against surge currents or excessive voltages produced by a thunderstorm, especially in a vehicle or a craft, e.g. an aircraft. A cable connector includes a hollow support body that reaches with an inner end into the grounding sleeve to provide a backing for holding an end of the cable casing clamped between the grounding sleeve and the inner end of the support body. The outer end of the support body carries a coupling nut.

Abstract: Freeze-up is prevented in a tap pipe connectable to a main liquid supply line, by a liquid circulator directly inside the tap pipe. The liquid circulator is either a Pitot tube that takes advantage of the liquid flow in the main line to establish a circulation in the tap line, or the liquid circulator is a driven pump directly in the tap line. The pump is driven by an electric motor or by a turbine rotor. The turbine rotor may be an axial flow wheel, or a paddle wheel driven by the liquid flow in the main line for driving the pump. The pump itself may be a paddle wheel. The Pitot tube, the turbine rotor, and the paddle wheel are very energy efficient by using the flow or dynamic head in the main line.

Abstract: A cable end with its terminal or connector is maintained in a curved installed position with the aid of a bent retaining jacket (25A). The jacket is preferably a corrugated metal hose having one end formed into a bushing that is clamped in place on a support body of the connector or terminal together with other cable components such as a protective hose system. The bend maintaining jacket has an inner diameter that is larger than the outer diameter of the protection hose system of the cable so that the jacket may be freely pushed over the cable end prior to the installation of the terminal or connector. The opposite end of the jacket remains open or rather unconnected, thus enabling the jacket to accommodate any twists that result from bending the cable end. Although the jacket is bendable, it has a bend retaining characteristic that will not change its curved configuration in response to impacts, vibrations, or the like. Only an intentional renewed bending can bring the jacket into a new curved shape.