Abstract: An aeroplane includes an escape opening passing through an external skin and an internal bulkhead. The escape opening is closed off by an external escape hatch having an external opening controller. The aeroplane further includes an internal escape hatch that closes off said escape opening flush with the internal bulkhead, and kept closed by at least one catch movable between a locked state and unlocked state, a first opening controller that controls the passage from the locked state to the unlocked state of the catch being accessible from inside the aeroplane, and a second opening controller that controls the passage from the locked state to the unlocked state of the catch being positioned such that the actuation of the external opening controller of the external escape hatch or the passage of the external escape hatch from the closed position to the open position causes the second opening controller to be actuated.

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: Method and device for aiding the guidance of an aircraft having to comply with at least one time constraint. The device can determine and present on a screen of the flight deck an offset in distance (?D) between the aircraft (AC) and a reference aircraft (Aref) which is defined to fly along the flight plan (TV) at an optimal speed to comply with the time constraint.

Abstract: An electrically actuated braking system for an aircraft. The system includes: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a motor controller for generating a drive signal for the EMAbrake; a braking control unit (BCU) for generating a braking force command signal for the EMAC during a normal mode of operation; and an emergency braking control unit (eBCU) for generating a braking force command signal for the EMAC during an emergency operating mode. The eBCU is disposed together with the EMAC in a common line replaceable unit (LRU).

Abstract: The device for automatic management of an actuator controlled by a servo-valve, includes a sensor for measuring the actual value of a parameter at the output of the actuator for a given control command, a computation unit for computing a theoretical value of said parameter, by applying the control command to a nominal performance model which models the operation of the actuator exhibiting nominal performance, a computation unit for computing the difference between the measured actual value of the parameter and the computed theoretical value of said parameter, a control unit for computing an adapted gain as a function of this difference, and a link for applying the adapted gain to the servo-valve for it to use it as gain value, so as to allow the actuator to restore nominal performance.

Abstract: A system for controlling an aircraft control parameter including a control interface including a mobile element configured to move on a travel, of which at least two portions are separated by a neutral position; a return element bringing the mobile element back to the neutral position when it is not actuated; and an interaction element, and a control unit configured to memorize an item of information corresponding to a first position of the mobile element at an instant of activation of the interaction element; and generate a setpoint of the aircraft control parameter, as a function of a control associated with the first position of the mobile element for which said information has been memorized; or a current position of the mobile element, when this current position is situated on the same portion of travel as the first position and is more remote than the latter from the neutral position.

Abstract: A wing for of aircraft has a wing tip shape that has a profile that extends in the direction of the span of the wing, and across the direction of the span of the wing extends from the wing leading edge to the wing trailing edge. The profile is delimited by a first skin and a second skin, with a winglet, arranged on the wing end. The winglet is substantially planar, and has a transition region arranged between the wing and the winglet, that extends from a connection on the wing to a connection on the winglet. The curvature of the local dihedral can increase in the transition region from a low level or a level of zero at or near the wing intersection in the outboard direction.

Abstract: A device for separating two zones of a passenger cabin including a frame element and an area element which is fastened to said frame element and includes, at least in certain sections, a flexible stretch material. The separating device is detachably fastenable in such a way to a passenger seat installed in the passenger cabin, that the area element extends substantially in one plane with a backrest of the passenger seat and that the section of the area element which includes of a flexible material is transferrable from a non-tensioned physical state into a flexibly stretched physical state in the event of the backrest of the passenger seat being adjusted from an upright position into a reclined position.

Abstract: A screw for an electrically contacting connection includes a screw head and a thread having a thread profile with a first thread flank facing the screw head and a second thread flank facing away from the screw head. The first thread flank is continuously curved from a radially inner bottom region to a radially outer run-out region in such a way that first angles between the center axis and local tangents, which lie on the first thread flank and intersect the center axis of the screw, increase radially outward along this direction. The second thread flank and the center axis include a second angle, which lies below the maximum first angle, in the opposite direction of the first angle. The run-out region continuously connects the first thread flank and the second thread flank to one another and is completely rounded.

Abstract: An assembly device between two sections of a double-skinned fuel pipe of an aircraft has a clamp for assembling the internal pipes, a coupling device for assembling the external pipes, a fitting extending between the ends of the external pipes of the first and second sections, with a shape complementary to the shape of an internal portion of the coupling device, and such that its section through any cutting plane perpendicular to the longitudinal axis common to the coupling device and the external pipes contains the smallest surface delimited by: a line corresponding to the intersection of the internal surface of the coupling device with this cutting plane and a straight line cutting said line at two points, this straight line being tangential to the orthogonal projection in this cutting plane, of the internal surface of the external pipes of the first or of the second section.

Abstract: A communication module includes a communication module, having an inductive energy transfer unit, a transfer driver coupled to the inductive energy transfer unit and configured to generate driver signals for operating the inductive energy transfer unit, a charging processor coupled to the transfer driver and configured to control the inductive energy transfer unit to operate in an inductive power charging operation mode, and a communication processor coupled to the transfer driver and configured to control the inductive energy transfer unit to operate in a near field communication (NFC), operation mode.

Abstract: The invention relates to a wingtip extension comprising a leading edge and a trailing edge, which wingtip extension is affixable to an outer end of a wing, wherein the leading edge, at least in some sections, is essentially straight, and the straight section of the leading edge comprises a leading-edge sweep angle that exceeds the leading-edge sweep angle of the wing, and the local depth of the wingtip extension gradually decreases between a connecting region for connection to the wing and the outer end of the wingtip extension. By means of a wingtip extension according to the invention, in a delta wing a vortex burst region is positioned just behind the wingtip, as a result of which vortex burst region the cores of wingtip vortices burst and eventually become unstable, so that as a result of this the wake vortices of the aircraft can be reduced. The invention furthermore relates to a wing, comprising wingtip extensions according to the invention, as well as to an aircraft comprising such a wing.

Abstract: A method of mounting at least one pressure port in a skin of an aircraft, where the port is made with a hollow tube implanted in the skin, optimizes conditions whereby each of the tubes is made flush with the skin so that static or dynamic pressure measurements are accurate and reliable. The method includes a step of leveling each of the tubes and a step of painting the skin. To achieve satisfactory leveling conditions for the tubes on each occasion, the leveling step is independent of the layer of paint deposited on the skin.

Abstract: A method for producing a part made of a composite material, including a skin and at least one stiffener made of strips, which are in turn made of one or more plies of fibers impregnated with a non-polymerized resin. The method includes the steps of: producing a preform of the part by pulling the strips through a die for shaping and positioning the skin and the stiffeners, a polymerization core being provided between a first strip and a second strip prior to the passage thereof through the die; and pressing the resulting preform in a hot press for a duration dt while applying a pressure P and at a temperature T for polymerizing the resin of the strips in the hot press over a pressing length L that is shorter than the length of the panel.

Abstract: A fuselage structure includes a pressure bulkhead and a frame being arranged behind the pressure bulkhead. The fuselage structure includes a first beam element with a first cantilever and a second cantilever, while the first beam element extends in a vertical direction of the fuselage structure. The first cantilever and the second cantilever protrude from the first beam element in a first direction toward the frame. The first direction of both cantilevers is inclined at a first angle with respect to a longitudinal direction of the fuselage structure. An aircraft with a fuselage structure and a method for manufacturing a fuselage structure are also described.

Abstract: An aeroplane includes an external skin and an internal bulkhead delimiting a cabin, and an escape opening passing through the external skin and the internal bulkhead. The escape opening is closed off by an external escape hatch disposed flush with the external skin. The aeroplane also includes an internal escape hatch that closes off the escape opening disposed flush with the internal bulkhead, and pressure regulating means capable of automatically triggering an opening of the internal escape hatch or a part of the internal escape hatch when a pressure differential on both sides of the internal escape hatch exceeds a determined value.

Abstract: A drop test device includes a suspension frame, a delay roller which is placed and mounted on the suspension frame, and at least one suspension cable, a first end of which is connected in a stationary manner to an attachment point on the outer surface of the delay roller and a second end of which includes a mounting which can be releasably or fixedly connected to a drop object.

Abstract: A drive unit includes a combustion chamber for combusting a fuel/air mixture, and a fuel cell device, wherein the fuel cell device includes at least one fuel cell, which in each case includes an anode that is couplable to a fuel line, a cathode that is couplable to an air source, and a fluid outlet and is arranged upstream of the combustion chamber. The combustion chamber further includes a combustion chamber inlet for supplying the fuel/air mixture, and a combustion chamber outlet for discharging exhaust gas, and the combustion chamber inlet is connected to the fluid outlet of the fuel cell device. In this way a hybrid drive unit can be provided which apart from mechanical power also generates electrical power at high efficiency.

Abstract: A method for manufacturing a composite material part comprising a web and at least one flange. In a laying up stage, a plurality of plies of different orientations, including 0° oriented plies, are laid up to obtain a flat laminate with edges comprising an outer contour and an inner contour, the flat laminate also comprising at least one section with a radius of curvature of less than 10 m. A forming stage comprises forming a fold along a folding line on the flat laminate to create a flange forming an angle with the web, and applying a stress tension to the 0° oriented plies located at least partially between the folding line and the outer contour of the flat laminate, in the at least one section, to avoid the appearance of wrinkles.

Abstract: A system for monitoring a fiber-reinforced composite component in production or in service. The system includes a composite component having reinforcing fibers which are encompassed by a matrix material; at least one optical fiber arranged to extend in a continuous path over a monitoring area of the composite component for contact with the matrix material; a signal generator configured to transmit an optical signal along the at least one optical fiber; and a detector device configured to detect scattering, and in particular backscattering, of the optical signal transmitted along the at least one optical fiber.