Abstract: A trailing edge wedge for an aircraft wing is attached to a bottom downwardly facing wing surface along the trailing edge of the wing so that an inner edge wedge surface is fully covered by the bottom wing surface. When the edge wedge is secured to a bottom surface of a wing, the wedge tip faces in the flight direction. The inner edge wedge surface and an opposite outer edge wedge surface enclose a wedge angle within the range of about 5° to about 20°. The edge wedge compensates for asymmetric aircraft characteristics due to unavoidable manufacturing tolerances.

Abstract: A shell component for an aircraft fuselage includes a fuselage skin panel, a plurality of stringers extending in an aircraft lengthwise direction, and a plurality of frames extending crosswise relative to the stringers. The stringers and the frames are respectively welded onto the skin panel with the addition of a weld filler material. Each frame includes a frame root portion and a frame profile portion connected to each other. The frame root portion has cut-out notches receiving the stringers passing therethrough. The frame root portion is welded to the skin panel at the areas between the cut-out notches, and may be welded to the respective stringer in each cut-out notch. The stringers and frames are fabricated from webs and flanges, whereby a premanufactured grid of flanges may be used. The result is a very strong, yet simple shell component structure, that may be manufactured with a simple welding process, at a low cost and with low effort.

Abstract: An arrangement of an airfoil, such as a main wing of an aircraft, includes a close-mounted engine on a short pylon connected to the airfoil, an inboard slat arranged inboard from the engine pylon along the leading edge of the airfoil, and an auxiliary high lift device. An open cut-out space is formed between the outboard edge of the inboard slat, the engine pylon, and the leading edge of the airfoil when the inboard slat is extended. The auxiliary high lift device is configured and arranged to be extendable into an extended position in which it aerodynamically covers or closes the cut-out space. The auxiliary high lift device is a movable high lift component that can be retracted into a retracted position in which it is recessed and integrated into the outer contour of the engine nacelle and/or the pylon. Thereby, the structural arrangement and mechanisms necessary for extending and retracting the auxiliary high lift device are simplified, and the weight and costs are reduced.

Abstract: A mobile access bridge provides access to the doors and the exterior surface of an aircraft fuselage in the final stages of construction, assembly, and outfitting. The access bridge includes catwalks preferably arranged at several levels, in pairs on opposite sides of the aircraft. The bridge further includes bridge supports that each have an arched inverted U-shape. The bridge supports are connected to and carry the catwalks, and respectively arch over the top of the aircraft fuselage. The bridge may be made up of a number of bridge segments that are coupled together as needed by coupling units. The entire bridge or each individual bridge segment is lifted at a lifting fixture by an overhead crane or lifting cable, is then moved into position, and then lowered onto the aircraft fuselage.

Abstract: A subsonic aircraft having backswept lifting wings is equipped with individually rotatable winglets at the wing tips thereof, in order to reduce drag during cruise flight, to minimize the dangers posed by wing tip vortices to following aircraft during take-off and landing, and to minimize the total wingspan during ground operations, with respective different positions of the winglets. A streamline-shaped rotation body made up of at least two individually rotatably supported rotation segments is mounted on the wing tip of each lifting wing. A respective winglet is mounted on each respective rotation segment. Each rotation segment with its associated winglet is individually rotatable about a rotation axis of the rotation body extending substantially parallel to the aircraft lengthwise axis. Thereby, each winglet is individually pivotable to any selected pivot angle relative to a horizontal plane extending through the rotation axis.

Abstract: A connection bolt arrangement typically used for connecting two structural members to each other, for example in aircraft construction, includes a conically tapered connection bolt that is force-locked or frictionally engaged in an expansion sleeve so as to cause a radial outward expansion of the sleeve and thereby tightly hold the structural components. An apparatus for releasing such a connection bolt arrangement includes two levers that are pivotably connected to each other, a stamping actuator arranged between respective first ends of the two levers, a pulling extraction device mounted at the second end of the first lever, and a pushing block mounted at the second end of the second lever. The actuating force applied by the actuator is transmitted through the levers and applied to the connection bolt and to the expansion sleeve in opposite directions so as to tend to push the bolt out of the sleeve.

Abstract: Three-dimensional large scale bodies such as jumbo aircraft fuselages (14) are assembled in body sections around a central longitudinal assembly core (1) which itself is mounted at its ends and accessible all around along its length. Robots carrying tools for holding, transporting and precisely positioning preassembled wall shell sections, are movable along the central core (1). First, at least one floor grid (2 or 3) is releasably mounted to the core. Then, side wall shell sections (4, 5) are secured to the floor grids. Then, top and bottom wall shell sections (10, 8) are secured to the side wall shell sections (4, 5) to form a body section (BS) of the large scale body (14). Neighboring body sections are secured to each other along cross-seams. Upon completion, the floor grids are released from the core (1) and the core is removed preferably withdrawn longitudinally from the assembled large component or body.

Abstract: Luggage storing bins in an aircraft passenger cabin are suspended from rigid mounting brackets by cooperating first and second securing elements forming part of the carriers and of bin end walls. The securing elements, such as holes, cooperate with connector members such as threaded bolts and nuts, whereby the bins can be secured to the respective bracket in different elevational positions to vary a cabin layout in accordance with airline requirements. Gaps between the cabin ceiling cover panels and the bins are covered by overlaps and/or additional moldings to accommodate different elevational bin positions.

Abstract: An aircraft air-conditioning system provides ventilation, air-conditioning and fire protection for a below-deck stairwell and cargo hold that may be equipped with passenger sleeping compartment containers. An air mixing unit mixes fresh air and recycled air to supply mixed air through a first supply air main line (31) and a supply air unit (21) into the freight hold (4), and through a second supply air main line (32) into the stairwell (5). A trimming air unit (7A) provides hot bleed air from the aircraft engines into the mixed air supplied through the first and second supply air main lines (31, 32). An exhaust air line (11) extracts exhaust air from the freight hold (4), while an exhaust air supplemental line (15) extracts exhaust air from the stairwell (5), both of which are connected to an exhaust air main line with an exhaust air ventilator (16) that blows the exhaust air overboard. A bypass line (8) provides bypass air if needed for the demands of the ventilator (16).

Abstract: A method for fabricating a stringer-stiffened shell structure using fiber composite materials involves the following steps. A fiber reinforced skin member having a specified surface curvature is laid onto a correspondingly curved mold surface of a shell mold. Stringer core blanks are cut from a cured plate of fiber composite material, whereby each blank has a narrow edge with a curvature matching the curvature of the skin member. These stiff pre-cut blanks are arranged extending along and vertically protruding from the skin member, with the narrow edges of the blanks lying in contact along the skin surface. An auxiliary frame is placed around the perimeter of the shell mold, and the ends of the stringer core blanks are received in slots in the frame to hold the blanks in proper positions.

Abstract: The below-deck space of an aircraft may be selectively configured as a freight hold or alternatively as a passenger sleeping cabin space by arranging a sleeping cabin container therein. An air conditioning system for this below-deck space provides air in a supply air main line (31), which branches off to at least one supply air delivery line (19). A first flange (23) is provided at the end of the supply air delivery line (19), and a seal collar (25) seals the end relative to the freight hold wall (29). When a sleeping cabin container is to be arranged in the below-deck space, a flap door (24) is pivoted into an open position, and the flange (28) at the end of a ventilation duct (27) of the sleeping cabin is connected directly to the flange (23).

Abstract: A system for air-conditioning the cabin of a passenger aircraft using externally provided fresh air as well as bleed air tapped from the engine of the aircraft includes at least one heat exchanger (4, 5), a blower (7), a compressor (8), an expansion turbine (9), a condenser (11), a reheater (10), a first high pressure water separator (13), and a second low pressure water separator (12). The several components are connected to each other by air lines such as air ducts, with control valves interposed therein. Two separate air-flow paths representing two different sub-systems are formed. A first air-flow path uses the high pressure water separator while a second air-flow path uses the low pressure water separator. These two air-flow paths or sub-systems can be operated separately and independently of each other by appropriately switching respective shut-off valves.

Abstract: An air inlet provides air to an air consuming system of an aircraft, such as an auxiliary power unit, which consumes ram air during flight and which sucks in ambient outside air during ground operations of the aircraft. The inlet opening is flush with the outer surface of the fuselage skin. An air channel extends from the opening and is recessed into the fuselage. An air inlet lip bounds the downstream edge of the inlet opening. To prevent the formation of an airflow separation bubble in the air channel when air is sucked into the inlet during ground operations of the aircraft, an air guide element is arranged adjacent to the nose of the air inlet lip. In one embodiment the air guide element is an aerodynamically profiled auxiliary slat fixed in front of the nose of the air inlet lip to form an air guide gap therebetween.

Abstract: An aircraft, preferably a large capacity passenger aircraft with two passenger decks, has a double-T tail assembly arranged on its tail section. The double-T tail assembly includes a double fin and rudder assembly and a tailplane and elevator assembly, and provides a significant increase in the usable passenger cabin space in the tail section of the aircraft. The double fin and rudder assembly has a U-shaped structure and comprises two upright stabilizer fins connected to each other by a horizontal torsion box that fixedly extends crosswise through the fuselage tail section within the floor of a cabin deck. The tailplane and elevator assembly is pivotably mounted on the upper tips of the two upright stabilizer fins in a double-T arrangement.

Abstract: A storage compartment is combined with an air flow channel (5) between a passenger seat and an aircraft side wall in an aircraft cabin. The storage compartment is constructed of five walls forming a box (3) inserted into the air channel that extends longitudinally along the aircraft side wall and along the cabin floor. The box (3) is upwardly closed by a hinged cover (16) forming a tray (17). The aircraft side wall (2) has at least one air filter element (10) facing into the channel. One or more dado panels (7) with air flow passages (6) enclose the channel toward the cabin. A cabin floor (4) closes the channel (5) downwardly. One or more decompression flaps (15) in the floor (4) normally close the channel (5). Under normal operating conditions air flow into and out of the cabin passes around the box through the channel (5) and the filter element (10).

Abstract: A patient transport arrangement is provided in the passenger cabin of an aircraft and includes a patient stretcher, medical supplies and equipment, and a compartment that is variably and adaptably useable as a restroom compartment and as a medical care compartment. The compartment is arranged adjacent to the doorway clearance area in front of the cabin door of the aircraft. The adaptable compartment includes a foldable wall element so that the stretcher can extend at least partially into the compartment during take-off, landing and ground operations of the aircraft while leaving the doorway clearance area unobstructed, and so that the stretcher can be repositioned out of the compartment and into the doorway clearance area during cruise flight so as to allow the compartment to be used as a passenger restroom during the flight. This arrangement makes efficient use of space within the passenger cabin that would otherwise be unused during various phases of flight.

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 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.