Abstract: A joint comprising: a structure; and a fastener passing through the structure. The cap has a body portion with an annular base terminating at an edge, the body portion forming an enclosure around an end of the fastener. The cap also has an annular flange which extends outwardly from the body portion and is set back from the edge of the base so as to define a pocket between the flange and the base. A sealant is provided in the pocket between the flange and the base, the sealant bonding the cap to the structure via a sealant/cap interface with the cap and a sealant/structure interface with the structure. The surface area of the sealant/cap interface is greater than the surface area of the sealant/structure interface.

Abstract: A preferred embodiment of the invention relates to a cyclone separator for a vacuum toilet system, with a casing; an input-side swirl generator, whose input openings impart a swirl to the inflowing fluid; a separating wall arranged in the casing, which encloses the fluid stream in the cyclone separator ring-like and whose interior cross section tapers downstream; and a collection tank in the casing for receiving and accumulating constituents separated out of the fluid. In addition, the invention relates to a wastewater tank and vacuum toilet system having such a cyclone separator.

Abstract: A flight control system for an aircraft, controlling a plurality of actuators adapted to actuate control surfaces of the aircraft, including: at least one communications bus; at least one computer situated in the avionics bay of the aircraft, and adapted to calculate flight commands and to transmit them over the bus in the form of command messages; and at least a first remote terminal connected to the bus, adapted to control a control surface actuator, and to acquire the state of the actuator from information provided by at least a first sensor, the first terminal receiving command messages from the computer and transmitting electrical orders to the actuator as a function of the command messages received in this way, and also transmitting messages to the computer, at its request, relating to the state of the actuator as a function of the information provided by the first sensor.

Abstract: Aircraft fuselage frame (9) in composite material with stabilized web whose omega-shaped cross section (11) in at least a first segment (31) is formed by one head (23), two webs (25, 25?), two feet (27, 27?) with a stiffening element (29) between the two webs (25, 25?). The invention also refers to a manufacturing procedure for the first segment (31) comprising steps to: a) provide an external element (41) with an omega-shaped cross section formed by one head (43), two webs (45, 45?) and two feet (47, 47?), and an internal element (51) with omega-shaped section formed by one head (53), two webs (55, 55?) and two feet (57, 57?), with their respective webs (45, 55; 45?, 45?) and feet (47, 57; 47?, 57?) oriented in parallel; b) join the internal element (51) to the external element (41).

Abstract: A high-lift system for an aircraft with a main wing and a slat that by way of an adjustment device is adjustable relative to the main wing to various adjustment states, with a gap resulting between the rear of the slat, which rear faces the main wing, and the main wing, where the size of the gap results from the adjustment state of the slat relative to the main wing, where in the interior of the slat an air guidance channel with at least one inlet and an outlet is formed, where the inlet is arranged at the rear, which faces the main wing, in order to influence the airflow in the gap.

Abstract: A method for manufacturing (partly) ring-shaped components, which include fiber-reinforced plastic, from fiber-composite semifinished products, involving the steps of: positioning a multitude of ring-shaped or partly ring-shaped mold pieces on a rotatable drum in such a manner that they include a reel-shaped mold with a ring-shaped channel for receiving the semifinished product, applying the semifinished product in the channel of the ring-shaped mold, rotating the drum in such a manner that as a result of the centrifugal forces the matrix material is pressed towards the outside and air contained in the channel moves inwards, and curing the semifinished product with the application of temperature to form a plastic ring, removing the plastic ring from the ring-shaped mold.

Abstract: A method of designing a structure, such as an airfoil section. A first set of candidate designs is generated in a first optimisation process, each candidate design comprising a set of M design variables associated with an M-dimensional design space. A subset of the first set of candidate designs is selected. The selected subset of candidate designs is analysed by proper orthogonal decomposition or principal component analysis to generate an N-dimensional design space defined by N design variables, N being less than M. A second set of one or more candidate designs is then generated in a second optimisation process, each candidate design comprising a set of N design variables associated with the N-dimensional design space.

Abstract: A method for detecting detachment of a reinforcing component that is attached to a body skin component of a vehicle body of a vehicle, the body skin component and the reinforcing component forming an electric capacitor together with an intermediate adhesive layer, said capacitor having a capacitance that changes if there is at least partial detachment of the body skin component from the reinforcing component, the capacitance of the capacitor or a change in the capacitance of the capacitor being measured in order to detect detachment of the reinforcing component.

Abstract: Composite material part (11) with stringer (31) on ramp, manufactured from a stack of fabrics, which comprises at least one zone (13) with two sectors (17, 19) having a greater thickness than that of the surrounding zones and with the stringer (31) situated on an edge (21) of said zone (13) in which: a) each group of fabrics (27, 27? . . . ; 29, 29?, . . . ) of said sectors (17, 19) has the dimensions to form on said edge (21) a ramp with an acceptable gradient 1/p so that the stringer (31) remains situated on the ramp; b) the stacking of the zone (13) is carried out firstly by placing the fabrics (27, 27?, . . . ) of the first sector (17) and on these the fabrics (29, 29?, . . . ) of the second sector (19) in such a way that in the coinciding section (35) of said edge (21) the gradient of the resulting ramp is 1/(p/2).

Abstract: A procedure and device optimize the quantity of fuel transferred on an aircraft during at least one in-flight fuel transfer. The optimization device includes a section that makes a prediction to determine a first quantity corresponding to the quantity of fuel remaining on board the aircraft at a first flight point in the flight plan of the aircraft, taking into account the current status of the aircraft and the current flying conditions. The device further includes a section that makes an estimation to determine a second quantity corresponding to the quantity of fuel enabling the aircraft to fly from the first flight point to a second flight point later in the flight plan. The device further includes a section that determines, from the first and second quantities, a third quantity corresponding to the quantity of fuel to be transferred at the first flight point. The device further includes a display that presents the third duly determined quantity to at least one pilot of the aircraft.

Abstract: A pressure bulkhead for a fuselage of an aircraft is configured for bounding a fuselage interior relative to an external environment. The pressure bulkhead includes a flat skin configured to span a cross-section of the fuselage and having a cavity disposed at a core region of the skin. The core region is radially bounded by a ring element. A plurality of radial stiffeners extend on the skin and provide stabilization of the skin. Each radial stiffener is fixed at an end to the ring element. A reinforcement element extends over the ring element.

Abstract: An aircraft control system in which a plurality of elementary control systems, corresponding to different aircraft functions, can share one or more sensors due to a common AFDX network. The transmission of commands is carried out via AFDX messages sent to network-subscribed actuators. Advantageously, the computers of the different elementary control systems installed in the avionics bay include generic computers hosting software specific to execution of respective functions thereof (IMA architecture).

Abstract: A nacelle, for an aircraft jet engine having a high bypass ratio, in which a jet engine having a longitudinal axis is mounted. The nacelle includes a wall that concentrically, and at least partially, surrounds the jet engine and together defines an annular duct. The nacelle further includes a displacement device that controllably displaces a portion of the nacelle wall in order to modify the section of the flow outlet passage and form at least one longitudinally extending opening. A device for forming a fluid barrier along the at least one longitudinally extending opening is provided to counteract the natural exhaust.

Abstract: A streamlined profile reducing the speed deficit in a wake, a pylon with such a profile, a propulsion assembly including such a pylon and an aircraft including this assembly. The profile has a device for suction of air from the boundary layer formed on this profile. This suctioned air is discharged with the aid of a nozzle the outlet of which is situated close to the trailing edge of the profile. Suction of the air and discharge thereof contribute to reducing the speed deficit downstream from the profile and therefore to reducing the turbulences in this zone.

Abstract: An mechanism for kinematic guidance of a body during its adjustment on a supporting structure. The body is moved between a refracted position and an extended position while performing a movement in a longitudinal direction in combination with a rotary movement. The mechanism includes first and second transmission levers for coupling to the supporting structure, a base connection lever to which these levers are coupled, third and fourth transmission levers coupled to the base connection lever, an adjusting lever coupled to the third and fourth transmission levers for attachment of the adjustable body, to adjust the body by a movement of the adjusting lever, and a coupling lever coupled to the first or second transmission lever and to the third or fourth transmission lever. During a movement of the adjusting lever, the first and second transmission levers each move opposite to the third and fourth transmission levers.

Abstract: Embodiments of the invention relate to an aerodynamic body with an extension in the spanwise direction, wing chord direction and wing thickness direction for coupling to a wing of an aircraft. This aerodynamic body can here be used for a leading edge flap or slat of an aircraft wing. To improve the flow characteristics, the rear side of the aerodynamic body is provided with a skin section that can be molded between a convex curvature and concave curvature.

Abstract: A high lift system is provided for an aircraft. The high lift system includes, but is not limited to a lift flap arranged on a wing and coupled to the wing so as to be movable relative to the wing, between a retracted position and at least one extended position. In the retracted position the lift flap rests against the wing, and in an extended position forms an air gap to the wing. The lift flap directed towards its trailing edge comprises at least one region of variable curvature, which region in an extended position of the lift flap extends towards the wing.

Abstract: An aircraft interior component system includes an aircraft interior component, a first structure holder fastened to an element of the aircraft structure, and a first component holder fastened to the aircraft interior component. The first component holder is fastened to the aircraft interior component in a first region thereof which faces an aircraft cabin ceiling when the aircraft interior component is mounted in an aircraft. The first structure holder and the first component holder attach the aircraft interior component in a suspended manner to the element, such that a mounting gap is present, at least in a second region of the aircraft interior component facing an aircraft cabin floor when the aircraft interior component is mounted in an aircraft, between a rear side of the aircraft interior component and an aircraft component opposite the rear side of the aircraft interior component.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: The invention pertains to a method and apparatus for verifying the consistency of the values given by an angle of attack probe of an aircraft. The method and apparatus verifies the proper operation of the angle of attack probe by using the aircraft's vertical load factor measurement provided by an accelerometer to estimate the angle of attack and then comparing the estimated angle of attach with the measure angle of attack.