Abstract: The present invention relates to an afterglow coating comprising a clear varnish and a photoluminescent pigment, wherein the pigment comprises a white luminous color in which the clear varnish is distributed. The present invention furthermore relates to methods for producing these coatings and to their use for coating surfaces in the cabin of aircraft.

Abstract: An aircraft cockpit comprises a head-up display device comprising a projector and a screen, the screen being placed facing a pilot along a theoretical line of sight of the pilot. The projector is fixed to a side wall of the cockpit, the screen forming a non-zero angle of inclination relative to a plane perpendicular to the theoretical line of sight of the pilot.

Abstract: A boomerang link for aircraft engine mounts, including a first orifice and a second orifice both designed to connect the boomerang link to an aircraft pylon, and a third orifice designed to connect the boomerang link to an aircraft engine. The third orifice is offset relative to a plane passing simultaneously through an axis of the first orifice and through an axis of the second orifice. When the boomerang link is seen in section in any plane orthogonal to the axes, a straight line segment extending from the axis of the second orifice to an axis of the third orifice crosses a region external to the boomerang link. This conformation confers on the boomerang link a flexibility enabling it to filter transverse vibrations between an engine and an aircraft pylon.

Abstract: Lavatories on-board a vehicle, and in particular to a lavatory unit for use by persons with reduced mobility on-board a vehicle are described. The lavatory unit includes a lavatory housing structure enclosing a lavatory interior space, a door opening in the lavatory housing structure, a toilet assembly inside the lavatory interior space, and a transition seating support for a user. The transition seating support provides a first transfer position and a second transfer position. In the first transfer position, in an open door state the transition seating support is directly accessible for a person sitting in a wheelchair that is located at least partly outside the lavatory unit such that the person can transfer to the transition seating support and vice versa, and in the second transfer position, a person sitting on the transition seating support can transfer to the toilet assembly and vice versa.

Abstract: The invention relates to an angle measurement probe on board an aircraft, which comprises a fin, which can move in rotation about an axis, at least one first optical encoder and one second optical encoder, each comprising at least one disk, each disk being fixed at right angles to the central axis and being provided with at least two circular tracks, each track being provided with alternate opaque and transparent zones, means for processing the output signal from each encoder.

Abstract: A method and an arrangement to determine an incidence of loading of an aircraft structure. A true reality of at least one aircraft structural section is superposed with the virtual reality of the aircraft structural section, and any deviation is established by means of a comparison of the two realities; this deviation is evaluated with reference to its consequences in terms of the structural mechanics involved.

Abstract: The display device comprises display means which highlight on a screen, preferably of PFD type, the information useful to the pilot relating to at least one flight parameter, especially while reducing the corresponding scale on said screen.

Abstract: A cargo container for accommodating transport goods and for being arranged in a cargo compartment of a means of transport is provided. The cargo container includes a housing that can be closed so that it is airtight, and an internal coating. The internal coating is incombustible and is arranged on an inner surface of the housing. Thus, the cargo container makes it possible to limit propagation of a fire to the internal space of the housing.

Abstract: An aircraft cabin partition monument comprising a partition wall element and a stowage compartment. The stowage compartment includes a cover plate element and at least one sidewall element. The stowage compartment is convertible between a state of rest, wherein the cover plate and the sidewall element extend substantially parallel to the partition wall element, and a state of operation, wherein the cover plate element and the sidewall element extend relative to the partition wall element such that the cover plate element and the sidewall element define a stowage space arranged adjacent to the partition wall element.

Abstract: A system for air conditioning at least one partial region of an aircraft comprises an air providing device for providing air to be supplied to a region of the aircraft to be ventilated at a desired temperature and pressure. A supply air duct is connected at a first end to the air providing device. A second end of the supply air duct is connected to an air inlet which opens near the floor into the aircraft region to be ventilated. A control device is set up to ensure that the air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at such a speed that the air is distributed near the floor in the aircraft region to be ventilated and rises at heat sources present in the aircraft region to be ventilated, and that the air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at such a temperature that a desired ambient temperature is set in the aircraft region to be ventilated.

Abstract: A method for detecting erroneous air data on an aircraft includes determining a current air parameter and a current altitude pressure parameter which collectively define a current point of control for the aircraft. The method also includes verifying whether the current point of control is situated in a characteristic envelope indicating operating limits for the aircraft. When the current point of control is outside the characteristic envelope, then a detection piece of information identifying at least one of the parameters as an erroneous parameter is emitted, which causes that erroneous parameter to be invalidated and an alarm signal to be sent to the crew. Therefore, an erroneous air data parameter is readily addressed and discarded using the method and associated device.

Abstract: A piece of furniture for an aircraft, including a plurality of carriages a first section forming an interface of use for a user with which at least one carriage may be taken and/or deposited in the piece of furniture and a second section allowing the said carriages to be circulated along at least first and second main directions substantially perpendicular to each other, at least in a plane of the aircraft for storing and/or delivering to the user at least one carriage, the first section and/or the second section including an arrangement for distributing at least one carriage from the second section towards the first section and vice versa.

Abstract: The invention relates to a compressor/turbine arrangement for use in an air conditioning unit of an aircraft air conditioning system comprising a process air supply line which is designed to supply process air generated by a process air source to a compressor. A detection device is designed to detect a characteristic signal for the temperature of the process air flowing through the process air supply line. A turbine is designed to drive the compressor. A cooling device is disposed in a process air line connecting the compressor to the turbine and is designed to cool the process air coming out of the compressor and flowing through the process air line in the direction of the turbine. Downstream of the cooling device a connecting line branches off from the process air line and opens into the process air supply line. A control device is designed to control a process air flow through the connecting line in dependence on the signal detected by the detection device.

Abstract: A seal is interposed between two surfaces of an aircraft propulsion assembly. The seal includes at least two layers each comprising a plurality of strands made of a heat-resistant material, the strands of a first layer being oriented in a first orientation and the strands of a second layer being oriented in a second orientation different than the first orientation.

Abstract: A drilling template for use in the field of producing aircraft or spacecraft or parts thereof has a first template part and a second template part. The first template part and the second template part are in each case provided here with means for fixing positions of bores to be produced. The drilling template has coupling means, by which the first template part and the second template part can be coupled to one another in such a way that the coupled template parts are movable relative to one another.

Abstract: An aircraft lifting surface with a torsion box of a composite material including an upper skin, a lower skin, a front spar, a rear spar, one or more intermediate spars and transverse ribs arranged between the rear spar and an adjacent intermediate spar and/or between the front spar and the adjacent intermediate spar.

Abstract: An aircraft comprising a front beam having stiffeners and a front lower fuselage section having stiffeners, each stiffener comprising a core and at least one bearing surface. Each stiffener of the front beam is connected to a stiffener of the lower fuselage section by at least one batten which abuts against the bearing surfaces of the stiffeners. A sealed wall is arranged in a transverse plane which corresponds approximately to the connection plane between the front beam and the front lower fuselage section. The sealed wall includes cut-outs in order to allow the stiffeners and the battens to pass.

Abstract: A method and a device for the execution of the method for the reproduction of an impact event of a projectile, with any ratio of energy and impulse, wherein a feed rate of an impress element is controlled by taking account of an alteration in velocity that is proportional to the quotient of a resistance force and a freely selected projective mass.

Abstract: An interface device for attaching mobile equipment (1) to an aircraft structure (5) comprises at least an attachment arm (6) and is subject to traction along a main axis of said equipment. The interface device comprises at least one fitting (2) secured to the structure (5), the fitting (2) and the attachment arm (6) having attachment means that coordinate together to offset the tensile stress and that comprise: means to hook a first end of the arm (7) to a first end of the fitting (8), a locking device (9) that coordinates with the hooking means to lock the first end of the arm (7) to said first end of the fitting (8), attachment means to attach a second end of the arm (10) to a second end of the fitting (11).