Abstract: A lighting system for passenger cabins, particularly aircraft passenger cabins, is equipped with at least one central light source cooperating with hollow light guides for distributing light in the passenger cabin. The light sources may be positioned in fixed locations within the aircraft or in fixed locations in the ceiling or in mobile locations within the hollow light guides. Light extractors are positioned where needed. The light guides are hollow preferably tubular light guides which may cooperate with optical light conductor fibers, and with lenses and mirrors where needed.

Abstract: A remote control driving mechanism works in the manner of an OR-gate for performing a mechanical switching operation by one of two or more operating control input levers at a time. For this purpose an operable member (2) to be driven is connected to a cam follower (17) which cooperates with two or more cam disks (9, 10) each connected to a respective operating lever (4, 5) through a corresponding push-pull cable (6, 7). Each cam disk (9, 10) has a cam track with a force transmitting section (13, 14) and with a guide section (15, 16) so arranged and configured that the cam follower (17) engages a force transmitting cam track section in one cam disk while engaging a guide cam track section in the other cam disk and vice versa. The sections of each cam track form a U- or V-configuration with a dead point (DP) between the cam track sections. The cam follower (17) is freely movable in the guide track sections, whereby the respective cam disk cannot be operated by its corresponding push-pull cable.

Abstract: A method for testing and determining the alloy class of an aluminum alloy may be simply and easily carried out, for unequivocally determining the correct alloy class among the aluminum alloy classes 2XXX, 5XXX or 6XXX, and 7XXX, of the test sample. According to the method, the material sample is dissolved in hydrochloric acid (HCL) to prepare a first solution, then nitric acid (HNO.sub.3) is added drop-wise to the first solution in order to cause oxidation of any insoluble copper (Cu) therein and form a second solution, then a potassiumhexacyanoferrate (II) solution (K.sub.4 ?Fe(CN).sub.6 !) is added to the second solution to bring about a discoloration and precipitation reaction and form a final resulting solution. Finally, the applicable alloy class of the tested material sample is determined by visually categorizing the color and precipitation state of the resulting solution.

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 a 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: A ventilation and air-conditioning system for a high capacity passenger aircraft having plural passenger decks one above another interconnected by stairways or the like, includes two air recycling units (6, 7) respectively incorporating filter units (61, 71) and blower units (62, 72). The inlets of the air recycling units are respectively connected to used air outlets (60, 70) arranged in an upper cabin (2), while the outlets of the recycling units are respectively connected to two air mixing junctions (9 and 10). The first air mixing junction (9) mixes a recirculation airstream from the first recycling unit (6) with an air-conditioned fresh airstream to provide a first mixed airstream into the upper cabin (2) through an air inlet (93). The second air mixing junction (10) mixes a deck transfer recirculation airstream provided by the second recycling unit (7) with an air-conditioned fresh airstream and directs the resulting second mixed airstream into the main cabin (3) through an air supply inlet (103).

Abstract: A double-pane aircraft cabin window arrangement avoids fogging, frosting, or icing of the window without using any active pressure regulating system or other active components. An inner pane and an outer pane are held in a window seal that is mounted in a frame connected to the aircraft fuselage. An interspace is formed between the two panes and sealed by the window seal. A condensation inducing tube is connected by a hose to an adapter tube, which passes through the window seal into the window interspace. The condensation inducing tube is connected in a direct thermally conducting manner to the outer fuselage skin of the aircraft. An open end of the condensation inducing tube is arranged to receive pressurized air from the aircraft cabin interior. As the air flows through the condensation inducing tube, any condensable moisture in the air condenses out on the interior walls of the tube, so that only dry air flows into the window interspace.

Abstract: Boundary layer air on the skin structure of an aircraft is sucked off through suction holes in the aircraft skin structure by a least one ejector pump. The ejector pump is operated by at least one of several air flow sources. One source is the excess pressure in the passenger cabin at higher altitudes. The other air flow source is tap air from at least one aircraft engine. If necessary, one or the other or both air supply sources may be utilized to operate the ejector pump or pumps.

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: A reading lamp system for passengers especially in an aircraft is equipped with at least one central light source preferably including a cool light lamp, the light of which is supplied through light guides such as fiber optical conductors, to individual reading lamps having a housing to which the respective light guide is connected. A liquid crystal film is positioned in the lamp housing between the light exit of the respective light guide and a lens that provides a light output from the reading lamp housing. The liquid crystal film is controllable in its light transparency by a passenger through a switch, whereby the passenger can make the liquid crystal film opaque to switch off the reading lamp or transparent to switch on the lamp. A dimmer may also be arranged to provide intermediate light level illuminations.

Abstract: An apparatus for cleaning hydraulic fluid includes a centrifugal fluid-spinning disk arranged in a housing, of which an upper portion forms a vapor chamber and a lower portion forms a fluid collecting basin. A vacuum pump is connected to the housing through an oil mist separator, such that water vapor is vacuumed away and hydraulic fluid collects in the oil mist separator to then be pumped away. The apparatus further includes preferably a single container that contains both the contaminated hydraulic fluid that is to be cleaned and the cleaned hydraulic fluid. A flexible inlet line and a flexible outlet line with respective hydraulic quick connectors are provided to connect the apparatus and particularly the oil container to a hydraulic system of an aircraft, for example. A high pressure pump connected to the outlet line pumps the cleaned hydraulic fluid into the aircraft hydraulic system and a pressure maintaining valve in the inlet line maintains the system pressure.

Abstract: A luggage compartment system especially for a passenger cabin of an aircraft is equipped with shells or bins (2) that are suspended from a support structure forming part of the aircraft body, by a four-bar or four-link system, the journals or pivots of which are substantially positioned in or above a reference plane defined by a top wall of the bin so that none of the links nor any of the journals take up space between end walls of longitudinally aligned bins. One journal may even be positioned below the reference plane, but not axially outside the end walls of the bin. Thus, additional space for luggage is gained.

Abstract: A method and apparatus for welding sectional members onto a large-format aluminum structural component using laser beams is especially applicable for welding stringers onto cylindrically or spherically pre-curved fuselage skin components in the construction of aircraft. The apparatus includes an adjustable support arrangement for supporting the large-format structural component, a roller guide and clamping system by which the sectional member, after it has been prepositioned, is guided by a computer numeric control (CNC) system and fixed onto the structural component, and a laser guide system that simultaneously directs two laser beams from two opposite sides of the sectional member onto a weld point along a joint seam between the sectional member and the structural component. The method and apparatus are applicable and readily adaptable with high flexibility to a great variety of geometries of the components to be welded, because the laser guide system is not coupled to the roller guide and clamping system.

Abstract: An apparatus for the heat treatment of aluminum and aluminum alloy components in the aircraft manufacturing industry is precisely controlled in accordance with manufacturing regulations that must be satisfied if the components are to meet regulation quality standards for use in manufacturing an aircraft. For this purpose, the apparatus has a compact arrangement of four stations cooperating with a transport system that moves the components to be treated sequentially through the stations including an annealing station, a quenching station, a cleaning station, and a drying station arranged in that order in the transport direction. The transport system and the stations are controlled by a central processing unit for providing the required control signals, including closed loop controls and monitoring of all parameters that are necessary for a fault-free precisely repeatable heat treatment of the aluminum and aluminum alloy components.

Abstract: A combustion chamber for a gas turbine using hydrogen as fuel, is equipped with an evaporator for liquid hydrogen which converts the hydrogen into its gaseous form that is fed directly or for instance via an external control valve into the combustor. The evaporator covers and protects at least a portion of the inner and/or outer wall that encloses the combustion chamber, whereby the evaporator also cools the combustion chamber while converting the liquid hydrogen to gaseous hydrogen.

Abstract: A luggage compartment system for a passenger cabin, especially for commercial airliners, is equipped with compartment units each formed by at least two compartments interconnected or coupled through a coupling, guide and drive mechanism (13) for moving the compartments of a unit from a closed upper position to an open lower position and vice versa. Each unit has a large compartment and a small compartment, the latter is intended for smaller luggage items, including fragile items, while the larger compartment is intended for large luggage including suitcases. In the closed position the two compartments of a unit are arranged next to each other in a direction extending crosswise to a longitudinal central vertical plane (10) through the aircraft cabin. The compartments have for their bottom contoured panels that are integrated into the ceiling of the cabin in the closed compartment position.

Abstract: A connector element is provided for variably laying and protecting insulated electrical conductors or cables for interconnecting the electrotechnical devices and lightning protective systems in aircraft and spacecraft. The connector element (29) includes a protective corrugated hose (25) connected to a screw-on component (1) by a collar nut (3) screwed onto the screw-on component (1). The collar nut (3) engages a flange (26A) on an end of the hose (25) and clamps it against the screw-on component (1). Insulated electrical conductors or cables (8) are guided through the hose (25), which is conductively connected to the aircraft structure. The hose (25) serves to protect, hold, and guide the electrical cables (8) in a desired configuration. The corrugated hose (25) includes a compressed portion (25A) with a small corrugation spacing, whereby the hose (25) is bendable into a desired configuration, yet is form-retaining and flexurally stiff to maintain the bent configuration.

Abstract: An arrangement for dividing an aircraft cabin that extends perpendicular to the longitudinal direction of the cabin, includes a divider wall that is guided in a position adjustable manner in guide tracks that are arranged stationarily fixed along the aircraft cabin. The divider wall includes a plurality of individual divider elements. Each divider element is held slidably by corresponding support members in at least one guide track. Each guide track is arranged in the area of joints between cabin interior components. With this arrangement, running grooves, scratches, and lubricant smears on visible furnishings or fitting in the interior of the aircraft cabin can be avoided. The cost and effort for cleaning and maintaining the aircraft cabin are thus significantly reduced. The arrangement does not restrict the open or clear cross section of the cabin, particularly in the head room area, thereby reducing a source of danger to passengers.

Abstract: A clamp for securing a protection hose to an electrical connector is formed as a cuff with a longitudinal gap. The cuff has an inherent bias which normally tends to close the gap. The cuff is provided with tool insertion elements for widening the gap to insert the protection hose into the cuff. When a tool is released the inherent bias generates force components so directed that the cuff will clamp the hose between the connector and the cuff. The tool insertion elements may also be used for electrically grounding the cuff made of electrically conducting material.

Abstract: A snap fastener for securing two structural components to each other has a fastener section with a head and stem with at least one axial slot (6, 7) in the stem opposite the head to form snap-on members (3A, 3B, . . . ) spaced by the slot (6, 7) in the stem (S). A washer fits over the snap-on members around the stem when the snap-on members are pressed toward each other. The locking members have shoulders (4) that engage the washer and form the snap-on connection. A locking bail (12) fits with a central portion into the slot so that the snap-on members cannot be pressed together anymore, thereby preventing the unlocking. The locking bail has at least one locking hook (15 or 16) that engages the washer so that the central portion (13) of the locking bail (12) cannot escape out of the slot. The locking hook can be intentionally disengaged against its elasticity for removing the snap fastener.

Abstract: In an emergency oxygen supply system of an aircraft equipped with a pressurized cabin, breathable gas is supplied by a gas generator (1) for generating an oxygen-enriched gas either from the ambient air, or from air tapped from the engine, or from fresh water. The generator may also generate practically pure oxygen. A mixed gas is produced in a mixing unit (14) from the breathable gas and oxygen as needed especially in short duration transition periods to meet official regulations. The oxygen partial pressure in the mixed gas is varied or controlled depending on the cabin pressure. The breathable gas is fed in a constant mass flow through an on-board distribution network to the breathing masks connected to the network. Selectable masks for the crew may receive pure oxygen while most other masks for the passengers receive mixed gas having an adequate oxygen content.