Abstract: A method that recommends capturing a stream of images of the landing zone, using a first imaging system to calculate position information for the landing zone on the basis of at least one real image of the stream, using an autopilot system to determine a current position of the landing zone at the current calculation instant, using a second imaging system to verify the presence of a landing zone at the current position in the real image, and generating an alarm if the presence is not found.

Abstract: A cabin monument for an aircraft includes a floor panel, which forms a base surface of the cabin monument, and a surrounding sidewall which defines an interior space of the cabin monument. The surrounding sidewall is assembled from a first wall part and a second wall part which is coupled to this. Provision is made on at least one of the wall parts for a fixing section which is overlapped by the floor panel. Also described is an aircraft which features such a cabin monument.

Abstract: The invention relates to a gear assembly (10) for use in a space craft for control of a moveable component thereof. The assembly comprises a load gear (11) in engagement with a drive gear (12) and an auxiliary gear (13). The drive gear (12) is coupled to a drive motor (14) so as to drive the load gear (11) in a first rotational direction. The auxiliary gear (13) is coupled to a retardation device (15) that is configured to passively resist the load gear (11) from rotating in the first rotational direction.

Abstract: A flight attendant seat comprises a carrier device having a first surface, a seat element movably coupled to the carrier device, and a backrest element movably coupled to the carrier device and operatively coupled to the seat element. The seat is movable between an operative position, permitting the use of the seat by a flight attendant, and an inoperative position in which the seat element and the backrest element are positioned, relative to the carrier device, such that they do not protrude from the carrier device first surface. The seat may be positioned in such a way, relative to a passenger seat or a row of passenger seats, that the rear side of the backrest element faces towards the rear side of a backrest of the passenger seat or the rear side of a backrest of at least one passenger seat belonging to the row of passenger seats.

Abstract: A sensing orifice for an aircraft, an aircraft with such a sensing orifice and a method for assembling a sensing orifice for an aircraft are provided. The aircraft may be an airplane, a helicopter, a UAV, a drone or similar. The static sensing orifice includes a passage through an outer skin of the aircraft and a moisture protection body. The passage is designed to connect with a pressure line in the interior of the aircraft. The moisture protection body is gas-permeable and water-impermeable, and the moisture protection body is disposed such that the passage is gas-permeably and water-impermeably sealed. The method for assembling the static sensing orifice for the aircraft, includes the following steps: providing the passage through the outer skin of the aircraft for connecting to the pressure line in the interior of the aircraft, providing a gas-permeable and water-impermeable moisture protection body, and gas-permeable and water-impermeable sealing of the passage by the moisture protection body.

Abstract: The invention provides a pin assembly comprising a pin having a screw threaded portion, a nut having a screw threaded portion, wherein, preferably, the pin has a number of pin recesses and the nut has a splined portion having a number of splines, the assembly further comprising a sleeve having a splined portion having a number of splines and a number of sleeve recesses, and a cross-member for insertion through at least one pin recess, and at least one sleeve recess, such that once assembled, rotation of the nut about the pin axis is restricted by the combination of the mating of the sleeve splined portion with the splined portion of the nut and the insertion of the cross-member through the sleeve recess and pin recess. The invention also provides a fixing assembly, landing gear actuation mechanism, aircraft, method of manufacturing and a kit of parts.

Abstract: A system to detect a pressure difference between the interior of a cabin of an aircraft and the exterior of the aircraft. The system includes a window arrangement having a first windowpane with a first surface and an opposite second surface and is adapted to be mounted in an aircraft such that the first surface of the first windowpane faces the exterior of the aircraft and is subjected to ambient outside atmospheric pressure and the second surface faces the cabin interior, and a pressure sensor including a first pressure port. The first windowpane includes a first air passage opening extending between the first and second surfaces of the first windowpane, and the pressure sensor is sealingly connected to the first air passage opening such that the first pressure port of the pressure sensor is subjected to pressure acting on the first surface of the first windowpane.

Abstract: A method for merging measurements of a flight parameter of an aircraft, from measurements (y1, y2, y3, y4) of this parameter supplied respectively by a plurality of sensors (C1, C2, C3, C4), comprising: for each sensor (C1; C2; C3; C4), computing a deviation (T1; T2; T3; T4), proportional to the absolute value of a difference between a measurement (y1, y2, y3; y4) supplied by this sensor, and an estimation of the parameter computed from the measurements supplied by the other sensors; comparing each deviation to a corresponding threshold (Td1; Td2; Td3; Td4); based on the comparisons, determining the presence or not of an anomaly on one of the sensors with a determined total probability of false alarm; and merging measurements to provide a final estimation of the parameter ({circumflex over (x)}).

Abstract: In a rotary wing aircraft a bar (1) of composite matrix material has a longitudinal axis (8) perpendicular to a cross section with upper and lower surfaces (2, 3). At least one torsion box (17) comprises an upper and a lower layers (10, 21, 11, 22) respectively offset of a longitudinal axis (8) and of the upper and the lower surfaces (2, 3), said upper and lower layers (10, 21, 11, 22) being laterally joint, while cross sections are filled with the first group of fibers extending essentially parallel to the longitudinal axis (8).

Abstract: A link for coupling an aircraft lift device to a track that is deployable about an axis of rotation. The link includes a track member to be fixed relative to the track, a lift device member to be fixed relative to the lift device, and an intermediate member that couples the track member to the lift device member. The link is configured to allow for sliding movement of the lift device member relative to the track member such that the lift device is slidable along a linear path relative to the track in a direction of the axis of rotation of the track.

Abstract: A method for projecting information issued from a digital design model. Calibration is performed by acquiring characteristic data originating from a surface of interest and comparing the characteristic data with virtual data issued from the digital design model. A spatial position of a projecting device is determined. The projecting device comprises a video projector and at least two separate image-capturing devices. Depending on the spatial position, information issued from the digital design model is projected by the video projector onto the surface of interest.

Abstract: A method for obtaining a composite piece of n plies, at least one ply having a fiber volume greater than 58% in weight, the method comprising the steps of laying uncured prepreg plies and performing ultrasound compaction over each laid uncured laminate ply, wherein at least one of the uncured laminate plies has a fiber volume greater than 58% in weight. Finally, the composite laminate is cured. The step of performing ultrasound compaction comprises applying an ultrasonic compactor over each laid laminate ply.

Abstract: A half-duplex (HD), frequency division duplexing (FDD), method for wireless communication systems, implementing an uplink and downlink prioritization respectively for a HD-FDD type mobile communication terminal during a transition between a downlink (DL) sub-frame, labelled n, and an uplink (UL) sub-frame, labelled n+1, in order to avoid overlapping of said sub-frames. This method comprises a step of sending by a base station an allocation message, a step of receiving the allocation message by said terminal and a step of processing said allocation message by said terminal.

Abstract: A dome for a rotor of a rotorcraft, the dome comprising a cap extending radially from an axis of rotation in elevation towards a periphery and in azimuth over 360 degrees, the cap extending in thickness from a bottom face for facing a hub of the rotor towards a top face above the bottom face. At least one of the top and bottom faces is an undulating face that undulates at least in azimuth between the periphery and the axis of rotation in elevation, by including in azimuth along at least one internal circle a succession of bulges and of recesses.

Abstract: The start-up system comprises a control loop, which regulates in real time the opening of a valve of an air feed of a start-up turbine based on the current measured speed of rotation of a rotor of the turbomachine and a predetermined speed value, said start-up turbine being capable of turning the rotor of the turbomachine for the purpose of the start-up.

Abstract: A system for detecting low concentrations of specific chemical compounds in the air of an aircraft cabin. The system includes a cabin management system with a processing unit and a user interface and a plurality of sensors. Each sensor is connected to the processing unit of the cabin management system such that data can be transmitted from the sensor to the processing unit. Each sensor is adapted to determine a presence of a first chemical compound in the air of an aircraft cabin and transmit data indicative of the determined presence to the processing unit. The processing unit is adapted to process data indicative of the presence of the first chemical compound received from a sensor of the plurality of sensors and to signal the presence of the first chemical compound to a user via the user interface.

Abstract: A control device including at least one control member for measuring an acceleration of an aircraft, for generating an inflation order, and for transmitting the inflation order to an inflation member, the inflation member serving to inflate at least one inflatable safety bag, the control device, the inflation member and the inflatable bag being arranged together on a single seat of the aircraft. Such a control device includes at least one readying system connected to the at least one control member, the readying system comprising: at least a first sensor suitable for continuously measuring a first current acceleration of the aircraft relative to at least one axis; and at least one switch that is controllable as a function of the first current acceleration of the aircraft as measured by the first sensor.

Abstract: A polymerizable thermoset composition including a polymerizable organic cyanate ester resin and a polymerizable aryl ethynyl-terminated polyimide, a polymerized thermoset, a process for the production of the polymerized thermoset as well as the use of the polymerizable thermoset composition for the production of lightweight construction components, preferably carbon fiber composite materials (CFC), and a lightweight construction component, preferably carbon fiber composite material (CFC), containing the polymerized thermoset are described.

Abstract: A composite pyrotechnic product containing energetic charges in a plasticized binder includes a cured energetic polymer and at least one energetic plasticizer, wherein: the cured energetic polymer consists of a glycidyl azide polymer (GAP) having a number average molecular weight (Mn) lying in the range 700 g/mol to 3000 g/mol and cured via its hydroxyl terminal functions with at least one curing agent of polyisocyanate type; and the energetic charges present at a content in the range 50% to 70% by weight consisting, for at least 95% of their weight, of large crystals of ammonium dinitramide (ADN) and of small crystals of hexogen (RDX): the large crystals of ammonium dinitramide (ADN) being present at a content in the range 8% to 65% by weight; and the small crystals of hexogen (RDX) being present at a content in the range 5% to 55% by weight.

Abstract: A linear guide mechanism for a passenger seat includes a movable carriage and a guide rail. The linear guide mechanism further includes a guide unit for positioning the movable carriage on the guide rail. The guide unit includes at least one guide element and a fastening element. Moreover, the guide unit is substantially fixed to the movable carriage by the fastening element. The guide unit and the movable carriage are displaceably mounted on the guide rail.