Abstract: An energy absorbing structural unit is attached outside the fuselage belly of an aircraft having at least two decks arranged one over another. At least the lower deck, of which the floor is adjacent to the fuselage belly, includes passenger cabin compartments and/or service facilities. The energy absorbing structure is an energy absorbing structural unit (5) that is attached outside of the existing aircraft fuselage (2) approximately vertically below the passenger cabin compartment (9) and/or service facilities provided on the lower deck of the aircraft. The energy absorbing structural unit absorbs impact energy arising in a crash or emergency landing of the aircraft. Because impact energy is absorbed by the external structural unit rather than or in addition to the structure of the aircraft fuselage and air frame, it is possible to provide lower deck passenger cabin space that may be continuously occupied by passengers and crew even during the take-off and landing phases of a flight.

Abstract: An aerodynamic structure having an aerodynamic surface for an aircraft, has at least two spars, several ribs made up of rib elements, and two shells made up of a plurality of shell elements. The ribs extend in the direction of the profile depth of the structure and the longitudinal extension of the spars and shells corresponds approximately to the span width of the structure. The shells and ribs are subdivided in the direction of the profile depth with an approximately equal division, to form at least two structural components open along one length side and closed by a spar along the opposite length side. Each component (21, 22) has two shell elements (24, 25; 34, 35, etc.

Abstract: An apparatus for generating or recovering energy on board an aircraft effectively utilizes the cabin exhaust air stream, which has a high thermal energy and a differential pressure, before it is discharged into the environment outside the aircraft. In this manner, the total efficiency of the aircraft is improved. The apparatus essentially includes an energy conversion unit (8) connected to the cabin exhaust air duct (2) to generate or recover energy from the exhaust air stream (5). Bleed or tap air (11) from the engine (10) is provided from a bleed air port (10A) through a cabin supply air duct or tap air duct (3) to an air conditioning plant (12) for final preparation of cabin supply air. A heat exchanger (4) is arranged between the cabin exhaust air duct (2) and the tap air duct (3), upstream of the energy conversion unit (8) in the cabin exhaust air duct (2).

Abstract: In an air conditioning system for the passenger cabin of an aircraft, the conditioned air is essentially provided by an air conditioning plant and is introduced into the passenger cabin through several individual air distribution systems (5 to 10) which are each associated with a respective air introduction section (A1 to A6). The length of the passenger cabin is to be divided into several air conditioning zones, for example three air conditioning zones, wherein the number of air introduction sections (A1 to A6) is a multiple of the number of air conditioning zones (2 to 4). A zone temperature sensor (18 to 20) and an associated separate temperature regulation system is provided for each air conditioning zone. A zone control unit (41) is connected to all of the temperature controls of the separate air distribution systems (5 to 10), whereby the zone control (41) selectively associates or couples each air distribution system (5 to 10) with a determined air conditioning zone (2 to 4 ).

Abstract: A method for avoiding cold welding of blind rivets, especially for the production of rivet connections between load carrying components in aircraft construction uses a not yet cured, curable adhesive to perform three functions, namely as a lubricant during setting of the blind rivet when the adhesive is not yet cured, to prevent cold welding between the shaft and the sleeve of the rivet, and as a seal and bond when the adhesive has cured. The blind rivet has a shaft or mandrel with a thickened end and a pulling end. The shaft has a conical section tapering from the thickened end to the pulling end. Grooves run around at least the conical section. The rivet mandrel or shaft is axially received in a rivet sleeve with a settable head. The not yet cured adhesive is provided in the grooves, especially along the conical section of the blind rivet. After the rivet has been set the adhesive hardens in the seam or gap to form the seal and bond.

Abstract: An aircraft body or fuselage is divided by a main deck (3) to form an upper deck and a lower deck. The lower deck has its own floor (5). A connecting device or several such devices, for example stairs and/or elevators, interconnect the upper deck with the lower deck in positions to facilitate central access to a plurality of lower deck facilities. Supply facilities and sanitary facilities are arranged on the lower deck to provide additional seating space on the upper deck. The lower deck may also hold resting areas, such as a lounge that may be equipped with beds, such as convertible beds. A food distribution station is arranged on the upper deck in vertical alignment with a galley on the lower deck. All the facilities of a group of facilities on the lower deck are centrally accessible.

Abstract: A smoke detector device for signalling a smoke detection in a space in an aircraft such as a cabin, a toilet, or a cargo hold of an aircraft, is mounted in a recessed position in a hole in a wall or ceiling of the aircraft. The device has at least one smoke detector enclosed in a housing (3) that also holds a smoke guide ring forming a funnel collar (7) for guiding smoke from a smoke collecting entrance (9) into a detector inlet opening (11) facing toward the space. The funnel collar (7) has a bottom (10) extending essentially on one level with the smoke inlet opening (11) of the smoke detector. The funnel collar tapers from the smoke collecting entrance (9) of the smoke guide rim to the smoke detector inlet opening (11) to form a smoke trap wherein a smoke stream toward the smoke detector is guided and accelerated. The smoke guide rim itself may function as a mounting for one or more smoke detectors, whereby a separate housing is obviated.

Abstract: A drilling tool is adapted for incorporation into a riveting robot. For this purpose, the drilling tool with its spindle head is mounted on a slide that is motor driven for displacement in the Z-direction of an XYZ coordinate system. The slide in turn is mounted on a console provided with a flange to be secured or docked to the riveting robot. The console is rotatable about its longitudinal axis that extends perpendicularly to the drill spindle axis and intersects the latter approximately in the center of the spindle axis. The drill spindle is rotatably mounted in a spindle head and carries a drive wheel approximately in the center between the spindle ends. The drive wheel is meshing or cooperating with a power transmission train from a motor that is also secured to the slide and moves up and down with the slide and thus with the spindle head. Another motor drives the up and down movement of the spindle head. This type of arrangement permits positioning the drill bit in difficult locations.

Abstract: An aircraft structure, such as a wing, is made of fiber composite material and includes a shell structural component also made of fiber composite material. The structural component has at least one access opening closeable by a cover. The shell structural component has a first area containing the access opening closeable by the cover. In the longitudinal direction of the wing the first area is predominantly flexible while a second area surrounding the first area is predominantly stiff, whereby these areas take up different longitudinally effective forces, relative to the length of the wing. Both areas are capable of transferring shear forces in the same manner.

Abstract: An overhead luggage compartment system for a passenger aircraft is equipped with luggage compartments formed as shells that can be adjusted in their tilted position and in their elevated position for easy access. In the closed position the shells are fully recessed into the ceiling structure of the aircraft cabin. Such a structure does not require any separate covers or lids for the luggage compartments. Additionally, a power drive lifts, lowers, and tilts the compartment shells. In the lowered position the shells are fully accessible even for short people. In the upper, recessed position the shells are closed and locked.

Abstract: An effective grounding of electrical equipment, electrical cables, housings, and the like, is accomplished by connector lugs that are initially formed as an integral part, for example, of a connecting sleeve that surrounds a protective casing or an envelope of a cable in a crimping manner. The lugs are only bent out of the sleeve or housing portion or the like when needed. A grounding conductor is then secured to the lug, for example, by a screw connection or by a plug-in connection or the like. The present 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.

Abstract: A pallet that is initially not completely aligned with a support structure, such as support rails in the floor of an aircraft, is properly aligned by the function of an aligning and coupling device which has two sections interconnected by a coupling member, such as a screw bolt that can be tightened. One section is connected to the support and the other section is connected to the pallet. Relative movement at least in a radial direction of the components of one section permit an adjustment. The relative movement is preferably permitted in the radial and axial direction. The continued tightening of the two sections to each other provide the required alignment.

Abstract: The spreading of a fire outside of an aircraft body into the cabin through the windows is retarded by a fire retardant slide member that is movable into a window covering position guided by guide rails or the like. Both, the sliding member and the guide rails are made of fire retarding material such as thermosetting material, preferably glass fiber reinforced thermosetting materials. A thermoplastic locking element that holds the sliding cover member in a recessed position releases the cover member when the locking element melts at elevated temperatures to cover the window automatically, e.g. with the aid of gravity or with the aid of one or more biasing springs.

Abstract: A large surface area work piece, such as a piece of sheet metal to be three-dimensionally deformed is held by a suction cup member which in turn is pivotally supported by a bearing disk and by a support that holds the bearing disk as a pivot socket. Two cooperating slide bearing surfaces are formed between the support and the bearing disk and two further cooperating slide bearing surfaces are formed between the bearing disk and the suction cup member. As a result, the angular adjustment movement of the suction cup member is substantially increased with the aid of the bearing disk. In operation, the applied suction or reduced pressure holds the components and the work piece in place. Venting or a slight excess pressure is applied to release the work piece. A flexible loop holds the three components together when suction is not applied.

Abstract: A stair and stairwell construction for interconnecting two different decks, especially in an aircraft, includes stair treads, stringers, and a stairwell enclosure or housing. At least one of the just enumerated components is constructed to be positionable or tiltable relative to the planes defined by the decks. One of these components is positionable into an open position, thereby providing a passageway, or into a closed position thereby blocking the passageway. In both positions, this positionable component is lockable.

Abstract: An aircraft cabin divider is so constructed that its installation can easily be handled by one person taking advantage of the force of gravity. For this purpose the divider has a frame with a first plug-in section that cooperates with a second socket section in the cabin structure, for example, the cabin floor or the cabin seating structure. The plug-in and socket sections cooperate so that an automatic lock-in is accomplished or so that a slight turn will provide the required interlocking. At least two couplings each including a plug-in section and a socket section are provided.

Abstract: Electrical conductors of a wiring system in an aircraft are mounted on a guide and support frame of modular structure. The frame is mounted on a structural air frame of the air-craft. Frames of different sizes may be assembled of tubular components and interlocking elements that have stubs that fit into open ends of the tubular components. The interlocking elements and the tubular components are made of electrically insulating materials such as thermoplastic materials. The stubs have wedge-shaped pockets or notches for holding an adhesive.

Abstract: An overhead luggage compartment for a passenger conveyance is secured to a fixed overhead structure by a single guide lever at each end of the movable trough that can be tilted up or down. Each guide lever has one end journalled to the fixed overhead structure and one end journalled to a respective side wall of the trough. Two gear sectors (6, 7) mesh with a common gear wheel journalled to the guide lever between the gear sectors which have a gear center coinciding with the journal axes of the journals that secure the guide lever. One gear segment is rigidly secured to the overhead structure. The other gear segment is rigidly secured to the trough sidewall. The gears control the up and down motion of the trough. A biasing spring and a shock absorber are also provided.

Abstract: An overload clutch limits the transmittable torque moment by permitting an override when a certain compression force is exceeded. For this purpose a drive shaft meshes with a disk provided with a number of holes in which balls are received. The disk has an axial thickness smaller than the diameter of the balls so that the balls can be uniformly exposed to a compression force exerted by a compression spring through a disk or bushing bearing on the balls. The balls cooperate with an entraining cam disk. As long as the torque to be transmitted is smaller than the compression force, the balls engage cam ribs on the entraining disk and transmit the torque. When the input torque exceeds the compression force, the balls override the cam ribs.

Abstract: Elongated components such as electrical wiring, electrical cables, piping, rods, ropes, and steel cables are mounted in place, for example, in an aircraft body, by a mounting device that has at least two mounting sections. At least one, preferably both mounting sections are provided with component holding channels. When the two mounting sections are held together they form a block in which the components are held in the respective through-going channels. The mounting block is locked to a support, such as a wall member. The closing and thus the connection of the two mounting sections to each other and the clamping of the elongated components in the channels as well as the locking of the device to the support is accomplished by a mechanism that performs all three functions. In one embodiment the mechanism includes a connecting bolt holding at one end an expander dowel and on its threaded other end a clamping nut, whereby the expander dowel is expanded by a pulling action.