Abstract: A coaxial rotary coupling (11) includes a hollow inner tube (4) and a hollow outer tube (7), with inner and outer splines (12 and 13) in mutual engagement. The coupling (11) further includes: approach elements for longitudinally approaching the inner and outer tubes (4, 7) together with elements presenting a wedge arrangement for causing the inner and outer tubes (4, 7) to turn (23) relative to each other in opposite directions so as to limit tangential assembly slack; a soleplate (16) of the driven tube (7); and a flange (17); the driving tubes (4) having complementary splines (12, 13, 18) together with dogs including force-transformation ramps (31) that are distributed peripherally within the coupling (11).

Abstract: The invention relates to a stop armature of an armature system of an aircraft door with a fuselage stop armature (10) and a door stop armature (12, 79), with a stop screw (30; 40; 60) in one of the two stop armatures (10, 12 or 79), which can be pressurized by the other stop armature (10) in the longitudinal direction of the screw (30; 40; 60; 80) on a locating face (34; 52; 70; 88). It is further developed by virtue of the fact that the screw (30; 40; 60; 80) encompasses a screw head (32; 42; 69) with a ball (36; 50; 68; 85) held therein that can rotate around its midpoint (M) as the fulcrum. The invention also relates to a stop screw for a stop armature and the use of a ball thrust screw as the stop screw.

Abstract: A blade (1) provided with a fitting (2) for fastening to a hub and with an airfoil element (10) having a spar (20) extending spanwise from an attachment zone (21) towards a distal zone (22), said attachment zone (21) surrounding a centrifugal force transmission bushing (31) that is connected to said fitting (2) by a through pin (3). The blade comprises a twisting force transmission member (40) provided with a first half-shell (41) and with a second half-shell (42) that together surround said attachment zone (21), each half-shell (41, 42) having a perforated first portion (43?, 43?) giving visual access to said bushing (31) when said airfoil element is removed from the fitting, and a second portion (44?, 44?) co-operating with a torsion box (50) surrounding said distal zone (22), said transmission member (40) being secured to said fitting in rotation about a torsion axis (AX) of the blade (1).

Abstract: A modular adapter plate system (1) for the installation of mission equipment in vehicles with floor panels (30), particularly for the installation of mission equipment in aircrafts such as helicopters, each plate (2-8) of said system comprising a pair of parallel seat/cargo tracks (9, 10) interconnected by stiff beam elements (11-15) and lateral flanges (16, 40) for releasable fixation to the floor panels (30) and lateral flanges (18, 19, 41, 42) for releasable interconnection. The invention is also related to a vehicle with said modular adapter plate system (1).

Abstract: Damper device for damping relative movements of two elements of a mechanical system. The damper device comprises a damping chamber filled with a hydraulic fluid, a rod (4) having a piston (3) movable in the damping chamber so as to define two hydraulic compartments (1, 2), at least one calibrated orifice (10) provided in the piston (3) for throttling the hydraulic fluid flowing from one hydraulic compartment (1, 2) to another hydraulic compartment, at least one compression peak-limiting valve (11) and a traction peak-limiting valve (12), throttling the hydraulic fluid flowing from one hydraulic compartment (1, 2) to another hydraulic compartment. The damper has additional hydraulic means that are active in compression and in traction when the piston (3) reaches the end of its stroke, so as to constitute a progressive hydraulic abutment damping the end-of-stroke jolts.

Abstract: A blade (1) for a tail anti-torque device of a helicopter, said device comprising a ducted rotor (13). The blade (1) has an assembly of sections, a leading edge (2) and a trailing edge (3); a stacking line (4) of the profiles extending at a distance lying in the range 25% to 50% of the chord (C). The stacking line (4) presents a shape that is curved having successively from the root (5) to the end (6) of the blade a back sweep, a forward sweep, and a last back sweep; and a chord (C) that becomes larger going towards the end (6) of the blade (1) over at least the end profile (1a).

Abstract: A protective device (10) for protecting an occupant (7) of a vehicle (1), said protective device comprising an airbag (11) and inflation means (12) for inflating said airbag (11), the inflation means (12) being connected to the airbag (11) via a feed pipe (13) for feeding inflation fluid for the purpose of inflating the airbag (11) under predetermined conditions. This protective device further comprises expulsion means (20) for expelling said fluid, which expulsion means cooperate with at least one water detection means (15) so as to act when water is detected to remove said fluid resulting from inflation of the airbag (11), said airbag (11) being provided with a peripheral elastic strap (50) for optimizing the deflation of said airbag (11) when said expulsion means (20) allow said fluid to be removed from the airbag (11).

Abstract: A fastener device (10) provided with attachment means (20) for attaching an external load (5) and with fastener means (30) provided with a support beam (40) and with anchor means (50) for anchoring said support beam (40). A first mechanical coupling (60) connects said support beam (40) to the anchor means (50) so as to enable the support beam (40) to pivot about a first pivot axis (AX1). In addition, coupling means (70) are hinged to the support beam (40) so as to make pivoting possible about a second pivot axis (AX2), the attachment means (20) being hinged to the coupling means (70) to make pivoting possible about a third pivot axis (AX3). This fastener device (10) includes automatic folding means (100).

Abstract: An aircraft door assembly of an aircraft, having a fuselage with a door opening and a door frame, encompassing an aircraft door fittable in the door frame. The door includes a door structure having an outer skin and is liftable from a locked closed position into a unlocked closed position, pivotable into an open position located outside the door frame and outside the fuselage, pivotable from the open position back into the unlocked closed position, and lowerable into the locked closed position such that in the locked closed position, a door gap is present between the door frame and a door edge. The gap defines a space for lifting and lowering the door. The door also includes, on its outer side and on a door edge region, a door gap covering element that extends over the door gap onto the outer side of the aircraft fuselage and covers the door gap, when the door is in the locked closed position.

Abstract: Described is a blade (10) extending longitudinally from a root (11) of the blade (10) to a free end (12) of the blade (10), the blade (10) being provided with an incorporated resonator (20) for reducing the drag movements (F1, F2) of the blade (10), the resonator (20) being provided with a closed tank (30) that is partially filled with a liquid (50). Furthermore, the resonator (20) includes a central tube (40) immersed inside the tank (30), the tank (30) and the central tube (40) being arranged in a longitudinal direction (Y) of the blade (10), the central tube (40) having first and second ends (41, 42) that communicate with the tank (30) so that the liquid (50) can move from the tank (30) into the central tube (40), and vice versa.

Abstract: A method of inspecting the integrity of an avionics system (1) installed in an aircraft, by inspecting the integrity in terms of electrical installation and data acquisition and transmission, wherein the method includes: using an Ethernet network (4) connecting the avionics system (1) to an inspection computer (3); using the computer (3) to generate first inspection signals transmitted to the component and/or to acquire second inspection signals coming from the component; using data read and write elements of a controller of the avionics system (1) to generate reference data relating to the component and transmitted to the inspection computer (3) via the Ethernet network (4); and displaying the reference data and the inspection signals and where appropriate recording the reference data and the inspection signals.

Abstract: A method and system for predictive maintenance of electronic equipment on board an aircraft (1). To produce a prognosis, the following are provided: a step (48) of modeling the equipment (3) with a model (53) for damage by an external aggression; a step (49) of simulating the damage up to failure; a learning step (64); a step (65) of classifying calculated and normalized values; and a fusion step (61) giving the real prognosis of the time to maintenance in units of time. The invention applies in particular to a rotary wing aircraft (1), e.g. a helicopter drone.

Abstract: A rotary device associated with drive means. The rotary device comprises a shaft and/or a hub and balancing means for balancing its rotational motion. The balancing means has a hollow chamber surrounding the hub and a solid/fluidic material with thixotropic properties, which fills partly the hollow chamber.

Abstract: An aerodynamic profile includes a main profile body defining a profile depth direction and being shear-flexible in the profile depth direction, a tension-stiff and compression-stiff upper covering skin, a tension-stiff and compression-stiff lower covering skin, wherein the upper and lower covering skins envelope the main profile body, a bearingless and hingeless rear profile deformation region disposed at a rear edge region, and at least one actuator disposed in the main profile body. The at least one actuator is configured to initiate a flexural motion of the main profile body resulting in a curvature of the upper and lower covering skins and to deform the rear profile deformation region and so as to yield a flap deflection directed opposite to a direction of the flexural motion.

Abstract: An aircraft (1) having an airframe (4) extending from a rear end (4?) to a front end (4?), a rotary wing (2), and a tail rotor (10). The aircraft (1) also includes a power plant (20) driving said rotary wing (2) via a main power gearbox (30) secured to a mast (31) of said rotary wing (2), said power plant (20) driving said tail rotor (10) via a tail power gearbox (40). The aircraft possesses pivot means (43) for causing the tail rotor (10) to swivel in a reversible manner from a stationary first position (POS1) towards a second position (POS2). The aircraft also includes tilt means (50) for tilting said mast (31) in a reversible manner.

Abstract: A method and a device for contactless determination of forces and/or moments acting on a hollow cylindrical body (12), in which via a light source (20; 38; 40), light radiation is produced within the hollow cylindrical body (12); measurement signals are recorded by an optoelectronic sensor (22; 34); the measurement signals recorded by the optoelectronic sensor (22; 34) are supplied to the signal processing unit (26); the signal processing unit (26) detects and outputs changes of the measurement signals relative to an initial state determined beforehand by calibration, corresponding to the initial undeformed state of the hollow cylindrical body (12); and when a mechanical deformation of the hollow cylindrical body (12) is present, according to a calibration function or a calculation rule, the signal processing unit (26) outputs an output signal that describes the forces and/or moments that are causing the mechanical deformation of the hollow cylindrical body (12).

Abstract: A fiber cable for helicopter rescue winches includes a plurality of load-bearing synthetic-fiber strands braided with one another, at least one electrically conductive insert, and a wear indicator providing a visual check of a state of the fiber cable, where the load-bearing synthetic-fiber strands are encased in a radial direction by a friction-reducing stable fiber layer, an inner cable jacket, and outer cable jacket.

Abstract: An anchoring element (2) intended to be fixed on at least one external anchor point (4) of an aircraft's fuselage, comprising a fixing area (5) for ensuring the fixing of the anchoring element (2) on the external anchor point (4) and said anchoring element (2) comprising an anchor means for the connection to attaching means, characterized in that the fixing area (5) comprises means for fixing the anchoring element (2) also to a additional external anchor point (6) of the aircraft's fuselage and said fixing area (5) comprising an extension area (7) on which is located the anchor means.

Abstract: A method of presenting attitude and heading information of a vehicle on a display to a viewer inside the given vehicle, comprising the steps of: using a 2D display, using data provided by an inertial reference system, using a computer and graphical software for treating the data and defining graphical elements, depicting the graphical elements in 3D on the 2D display, and presenting the attitude and heading information on the 2D display by associating them to at least one graphical element.

Abstract: A smoke simulator system (1) for an aircraft simulator cockpit said system (1) comprising a water tank (2), an ultrasonic generator (3), said ultrasonic generator (3) being inside said water tank (2), supply means (7) to said water tank (2) and outlet means (8) from said water tank (2) for smoke. The invention relates as well to a method to operate such a smoke simulator system (1) for an aircraft simulator cockpit.