Abstract: A storage compartment configuration and an aircraft having a storage compartment configuration according to the invention are proposed. The storage compartment configuration has a storage compartment having a storage space and a suspension. The storage space is designed to receive pieces of luggage. The suspension is used for the attaching the storage compartment to a load-bearing structure of the aircraft. The suspension is designed in such a manner that the storage compartment can be pivoted essentially around a geometrical center point of the storage space.

Abstract: A method for stiffening a skin field of an aircraft fuselage includes providing a skin field for an aircraft fuselage, manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners and connecting the stiffening structure to the skin field. The manufacturing can include the use of a tool mold having a plurality of longitudinal recesses configured to form longitudinal stiffeners and a plurality of sunken areas disposed between the longitudinal recess. The sunken areas are configured for forming respective mounts that are configured for connection to circumferential stiffeners.

Abstract: Disclosed is a taper bolt connection including a taper bolt received in a taper bush, a fastening nut and a washer, the taper bush having a continuous longitudinal slot, and the taper bush being capable of being spread open uniformly in the radial direction by means of a fastening nut screwable onto the taper bolt. Since the taper bolt and/or the taper bush have/has, at least in regions, an at least Teflon-containing coating, tribochemical processes between the taper bush wedge surface and the taper bolt wedge surface are largely avoided, so that the taper bolt connection can be released again without great effort even after a long period of connection. Furthermore disclosed is the use of the taper bolt connection for connecting a rudder unit to a carrying structure of a fuselage cell of an aircraft.

Abstract: An apparatus is provided for adjusting and locking a movable control surface, which includes, but is not limited to a rotatably held spindle, an adjustment body, a linear guide, a drive unit, a linear positioning encoder and a control unit. The adjustment body with the linear guide is slidably guided along a first movement axis, and the spindle is connected to the adjustment body for moving the adjustment body along the movement axis. The adjustment body is configured to connect to a control surface mount, and the linear positioning encoder and the drive unit are connected to the control unit. The latter is designed to adjust a predetermined actuating position of the adjustment body by rotation of the spindle with the drive unit and by comparing an actual position, detected by the linear positioning encoder, of the adjustment body with the predetermined actuating position.

Abstract: The present invention relates to a production method for a workpiece (15) composed of a fibre-composite material, having the following steps: at least one support means (3) is provided. A main material (6) composed of a pre-impregnated fibre semi-finished product and/or of a secondary material (7) are/is applied to the at least one support means (3) in order to form at least two blank-mould areas (1, 10), in such a manner that at least one of the at least two blank-mould areas (1, 10) has the main material, and at least one of the blank-mould areas (1, 10) has the secondary material. The blank-mould areas (1, 10) are pressure-bonded to one another to form a workpiece blank (14) such that the at least one support means (3) is provided on a surface of the workpiece blank (14). The at least one support means (3) and the secondary material (7) are removed from the workpiece blank (14) in order to form the workpiece (15).

Abstract: A method is provided for destroying a blind fastener joining at least two parts. The blind fastener includes, but is not limited to a body situated in the holes provided in the joined parts, with a head at each end thereof, and portions of which protrude above the level of the holes. The method also includes, but is not limited to withdrawing the accessible head of the fastener, and creating a hole that passes through the fastener. An insertion device is configured to restrain the remainder of the fastener in the hole, which has an elongated body having a diameter smaller than or equal to that of the hole and an expandable head at one end thereof The insertion device for restraining the remainder of the fastener being immobilised or capable of only limited movement relative to the joined parts, and expelling the remainder of the fastener from the holes.

Abstract: The invention relates to an aircraft comprising: a drainage system for condensation water formed in the aircraft between an upper zone thereof where the condensation water is formed and a lower zone where it is collected, a thermal insulation blanket (16) having two opposite faces, a first face (16a) of which is arranged facing the fuselage. The drainage system includes a drainage duct (18, 24) which extends into the upper zone along the second opposite face (16b) of the insulation blanket and which is connected to a pass-through device (30; 40) for the blanket placed beneath the upper zone. In this way, the drained condensation water passes through the blanket through the pass-through device and then is drained to the lower zone, between the first face of the blanket and the fuselage.

Abstract: The invention relates to a device for producing a reinforced foam material and for receiving a textile semifinished product in a hook. To this end, the device has a first subunit having a transport device and a second subunit having a receiving device. The transport device is designed to convey the textile semifinished product into the receiving device, and the first subunit and the second subunit are designed such that the textile semifinished product can be presented in defined length by a relative movement of the first subunit relative to the second subunit. Furthermore, the receiving device of the second subunit is set up such that the textile semifinished product can be placed in the hooks by a relative movement of the receiving device relative to the hook.

Abstract: A method and a system for monitoring an actuator equipped with a no-back device or no-back brake, particularly an adjustable horizontal trim actuator provided in aircraft, the method including the steps of: determining a value representative of mechanical work produced by the actuator and comparing the determined value with ranges of values so as to detect a dysfunctioning of the said no-back device. If the actuator is a screw/nut type with a hydraulic motor, the value representative of the mechanical work is determined from an algebraic velocity of the motor and an algebraic differential of hydraulic pressure at terminals of the motor. A negative value corresponding to negative mechanical work then identifies a failure of the no-back device.

Abstract: An air outlet valve for use in an aircraft is adapted during normal operation of the aircraft as a component of a cabin pressure control system for adjusting a desired pressure level in an aircraft cabin to remove air from an interior of the aircraft into the environment around the aircraft. The air outlet valve is further adapted during emergency ventilation operation of the aircraft as a component of a system for emergency ventilation of the aircraft cabin to introduce air from the environment around the aircraft into the interior of the aircraft. The air outlet valve comprises a nose-side valve flap, which is pivotable about an axis and is adapted to open or close a nose-side portion of an air outlet valve aperture, and a tail-side valve flap, which is pivotable about an axis and is adapted to open or close a tail-side portion of the air outlet valve aperture.

Abstract: A device for interior covering of an aircraft cabin, intended to be fastened to a structure of an aircraft and to extend along a skin of the aircraft, the device comprising a covering panel. The covering panel bears at least one system, possibly through a system support. It advantageously comprises at least one air circulation pipe fastened to an exterior face of the covering panel, each air pipe having an upstream end equipped with a connection device.

Abstract: An aircraft air conditioning system includes a main air conditioning device which taps air off a turbine engine, and an auxiliary unit with a compressor that taps ambient air and conditions it to send to a distributing device in place of a main device, when the aircraft is in cruising flight or close to cruising flight.

Abstract: A method and device aids in monitoring at least one turbine engine in an aircraft. The method includes determining a value illustrating a thermomechanical state of the turbine engine, and comparing the determined value with at least one threshold. The method also includes displaying in the cockpit of the aircraft, at least one indication related to the operation of the turbine engine, according to this comparison. As a result, conditions that could result in mechanical degradation or failure of the turbine engine are identified for a crew of the aircraft.

Abstract: An aircraft nose structure includes a fuselage, a floor for a pressurized space and a nose landing gear bay arranged under the floor, on the opposite side to the space. The bay includes walls that form a pressure barrier, of which there are two lateral panels mechanically secured to the floor by load-reacting members, an upper panel adjacent to the floor and extending between the lateral panels, and a rear panel extending between the upper panel and the fuselage.

Abstract: A method for detecting and locating by reflectometry electrical faults in a metal structure includes injecting a probe signal into an electrical propagation line held at a substantially constant distance from the structure. The propagation line is connected at one end to the metal structure and at another end to a signal generator. The method further includes detecting a reflected signal in return from the injected signal. In addition, the method includes comparing the reflected signal with a reference signature of an undisrupted reflected signal.

Abstract: A method of manufacturing a composite element. A stack of plies is assembled on a lay-up table, each ply comprising a plurality of reinforcement elements such as dry-fibers. A first part of the stack of plies is bound to form a partially bound stack of plies, a second part of the stack of plies remaining unbound. The partially bound stack of plies is press-formed in a mold cavity between a pair of mold tools to form a shaped pre-form, plies in the second part of the stack sliding against each other during the press-forming. A liquid matrix material is injected into the shaped pre-form in the mold cavity and subsequently cured.

Abstract: This invention provides a method for producing a structural component, particularly in the aerospace sector. An unhardened prepreg fabric is formed from a composite fiber material, hardenable at a first hardening temperature, into a predetermined shape. The unhardened prepreg fabric is then connected to at least one hardening part of a composite fiber material partially hardened at a second hardening temperature for holding the unhardened prepreg fabric in the predetermined shape, wherein the second hardening temperature is lower than the first hardening temperature. In a further method step the unhardened prepreg fabric connected to the at least one holding part is hardened at the first hardening temperature to form the structural component.

Abstract: A wing of an aircraft has a pressure-side flow surface and a suction-side flow surface relative to an assumed main direction of attack and comprises a flow fence disposed on a flow surface, wherein the flow fence extends in the main wing chordwise direction and between a location of the pressure-side flow surface and a location of the suction side flow surface.

Abstract: A device and a method for manufacturing a fiber-reinforced fuselage shell for an aircraft, which fuselage shell for the purpose of reinforcement comprises several stringers that are spaced apart from each other, wherein the device includes a base frame comprising several supporting walls of different lengths for forming a curved mounting surface for the fuselage shell to be manufactured, wherein several actuators that extend radially outwards and that are longitudinally adjustable are affixed to the mounting surface, at the distal ends of which actuators in each case mold channels for receiving the stringers are attached, which mold channels are interconnected by means of flexible intermediate elements and/or further mold channels for forming a vacuum-tight closed mold surface.

Abstract: The invention provides a stiffening element, in particular for a shell component of an aircraft or spacecraft, which has a stiffening profile part and a foot part. The stiffening profile part is in this case composed of a lightweight metal material, and the foot part is composed of a material which is highly resistant to corrosion. A method is also provided for production of a stiffening element, in particular for a shell component of an aircraft or spacecraft. A stiffening profile semi-finished product is first of all produced from a lightweight metal material, and a foot part is produced from a material which is highly resistant to corrosion. The foot part and the stiffening profile semi-finished product are then integrally connected. The stiffening profile semi-finished product together with the foot part is then subjected to machining to form an intended shape for the stiffening element.