Abstract: A channel profile extends above a door of an aircraft over the width of the door opening and is connected with the aircraft fuselage. When the door is open, the channel profile collects liquid (e.g. rain) flowing down from above the door, and diverts it next to the door opening. To reduce the air flow resistance arising during flight operation, with the door (2) in its closed position, the channel profile (3, 30) is retracted and enclosed behind the outer skin (6) or a flange of the door (2) in a dead space (11) between the upper edge of the door (2) and a frame (4) arranged above the door opening. When the door is opened, the channel profile extends into an outwardly protruding position on spring-loaded guides.

Abstract: A supporting arm of a passenger door of an aircraft, has a curved structure which forms hollow chambers and movably connects the passenger door to a frame on the fuselage. Receiving means one for the supporting arm for receiving connecting means which enable a movable connection on the one hand to the passenger door and a pivoting drive and on the other hand to the frame on the fuselage, so that the door is movable by means of the supporting arm on a linear-displacement path and a pivoting path. The structure of the supporting arm is formed from fiber composite, the structure-forming fiber composite being formed from individual structural elements. This fiber composite structure further improves the thermal insulation of the supporting arm and nevertheless achieves a further weight reduction of the supporting arm, while maintaining exacting structural safety requirements for the latter.

Abstract: A constant velocity drive mechanism of a rotary-wing aircraft rotor, comprises a torque splitting differential mechanism, comprising a driving disc integral in rotation with a rotor mast and connected to each of two driven discs either side of the driving disc, by a least one connecting pin hinged to each of the discs by one of three ball joint connections. Each of the driven discs is connected to a hub of the rotor by at least one of two driving devices, each of which is also hinged to the hub, so as to drive the hub in rotation about a geometrical axis which can be inclined in all directions about the axis of rotation of the mast.

Abstract: The regulating system (1) comprises in particular a metering valve (4) for metering the fuel fed to the engine (2), as a function of control commands, a device (8) for determining a pre-set value NTLcons corresponding to the pre-set value of the rotational output of the free turbine of the engine (2), and computation means (9, 10) which compute control commands making it possible to slave the output of the gas generator of the engine (2) to a pre-set value NGcons of the output of the gas generator, which depends on the rotational output NTL of the free turbine and said pre-set value NTLcons. Said device (8) comprises a means (21) for determining the position of a rudder bar of said helicopter, and an auxiliary computation means (22) which computes the pre-set value NTLcons as a function of said position of the rudder bar and of other external parameters, in particular the altitude.

Abstract: A tilting rotor of a convertible aircraft comprises, between the mast and the hub, a constant velocity drive mechanism and pivoting arrangement comprising two gimbals, each of which is driven by the mast and pivots about one respectively of two diametral axes by two diametrically opposite bearings. Each gimbal is also hinged to the hub by ball joint connections diametrically opposite and centred respectively in a radial plane passing through the axis of the mast and through the diametral axis about which the other gimbal pivots. The two resulting trains transmitting torque between the mast and the hub have substantially the same torsional rigidity, and one at least of the components of each torque transmission train exhibits a flexibility in deformation about the axis of rotation of the hub.

Abstract: To fold/unfold blades of a rotor, at least one variable-length linear actuator is removably attached to two blades locked in the flight position. A first blade is unlocked, and the actuator is actuated to vary its length and bear against the other blade which remains locked. This causes the first blade to pivot about its pivot axis and move to a folded position where it is again locked. The other blade is then unlocked and the actuator once again actuated but this time bearing against the first blade. In this way the other blade pivots into the folded position where it is again locked. The two locked folded blades may be connected to each other by a link rod. Rotors with three blades, four blades, five and six blades can be folded/unfolded with only two actuators.

Abstract: A device for lubricating a power gearbox having a variable orientation and a closed space has a lubricating unit that supplies lubricant to at least one element of the gearbox, which needs to be lubricated. A collecting reservoir collects lubricant from the closed space. A drain screw chamber, within the closed space, has a number of orifices disposed between different zones of the closed space and the drain screw chamber for passing lubricant there between. At least one rotary drain screw, which is produced in the form of an Archimedean screw, is disposed in the drain screw chamber to convey the lubricant from the drain screw chamber to the collecting reservoir. A drive unit drives the drain screw in rotation for conveying the lubricant. The orifices open respectively different zones of the closed space to the drain screw chamber such that the drain screw chamber can always collect lubricant from the different zones regardless of the orientation of the gearbox.

Abstract: Device and system for the automatic control of a helicopter. The automatic control device (6) comprises a vertical objective law (A) in respect of the pitching axis, which automatically determines a control command (UT1) for operating the tilting of the disk of main rotor of the helicopter, a speed limitation law (B) for limiting the airspeed of the helicopter with respect to at least one limit value, detection means (10) for automatically detecting whether the airspeed reaches the limit value, and toggling means (11) for, in order to select the objective law (A, B) whose control command (UT1, UT2) is used for the pitching axis, automatically toggling from the first law (A) to the second law (B), when the detection means (10) detect that the airspeed has reached the limit value.

Abstract: A system of pitch attitude symbols, which can be generated by a head-up display unit of an air vehicle, is provided. The system of pitch attitude symbols can be displayed by the head-up display as a virtual image in the direction of flight, behind the cockpit screen in a focal plane in front of the background. An unequivocal system of pitch attitude symbols is provided for the pilot, for a display area of an HUD, which display area is arranged below the natural horizon during neutral flight attitude of an air vehicle. Within the focal plane, the system of pitch attitude symbols comprises at least one pitch attitude representation area, arranged in perspective, which pitch attitude representation area can always be arranged parallel to the surface of the earth. The rear edge of the pitch attitude representation area is tiltably fixed in a rear edge axis and, depending on the pitch attitude of the air vehicle, the pitch attitude representation area can be tilted on the focal plane.

Abstract: An emergency opening cylinder of a passenger door of an airplane is provided. An existing emergency opening cylinder is adapted at the lowest expenditures and with an insignificant increase in weight with respect to its operating characteristic to the load situation of an emergency opening of the door against the force of gravity. A ventilation bore of the emergency opening cylinder leads into a collecting chamber which has an outlet valve controllable by a control.

Abstract: Transmission system for an aircraft, particularly a helicopter. The transmission system (1), of supercritical type, comprises at least one rotary transmission tube (4) which is such that at least one natural frequency of said transmission tube (4) is below its nominal rotational speed, and at least one active and controllable magnetic damper (5) capable of generating a magnetic force capable of acting on said transmission tube (4) and which damper is controlled in such a way as to generate a magnetic force making it possible to reduce the vibration of the transmission tube (4), at least when the speed of the transmission tube (4) is within a predetermined range of frequencies defined around said natural frequency.

Abstract: A drag damper for use on a rotary wing aircraft rotor comprises a body defining two variable volume chambers linked by a piston. The chambers are filled with fluid and are connected by a restriction port (35) and by a channel (32) of larger cross-section than the restriction port. A secondary piston slidable and pressure-tight piston is fitted in the channel and loaded by an elastic bias (34). The equivalent mass of this secondary piston (33) and of the fluid which it displaces, and the stiffness of the elastic bias (34) are such that the secondary piston is resonant in the channel (32) at the rotation frequency of the rotor, to filter the dynamic component at this frequency of stresses applied to the damper (20).

Abstract: A pivoting power transmission unit is provided for transmitting rotational drive from a power source to a rotor configured to revolve about a first axis and configured to swivel about a second axis perpendicular thereto. The transmission unit comprises: input pinion driven in rotation by the power source; two contra-rotating gearwheels which mesh with the input pinion and are co-axially mounted along the second axis; two cylindrical intermediate pinions, each joined to rotate co-axially with a respective one of the two gearwheels; and a further gearwheel in meshing engagement with the intermediate pinions. The further gearwheel drives in rotation an output shaft linked to the rotor.

Abstract: A valve arrangement is provided for a feed line to supply fuel from a tank to a combustion engine consisting of a valve housing with an inlet channel and outlet channel, and a valve with a movable valve head to seal the outlet channel from the inlet channel, whereby a feed pump is assigned to the feed line, and the valve head is in closed position when there is no feed pressure from the feed pump. The danger of feed line leakage for combustion engines that burn liquid fuel is eliminated using a coaxial second valve using no additional space to solve the problem. The other essentially coaxial valve within the main valve is in open position opposite the feed direction when the pressure at the outlet channel is greater than the feed pressure. The valve arrangement functions as a check valve when the combustion engine is running, and as an overpressure valve when it is off.

Abstract: A device for lubricating a step-up/down mechanical assembly with a lubricating fluid has a collection reservoir, a circuit for distributing lubricating fluid, and a device for creating relative movement. The collection reservoir collects the lubricating fluid from the step-up/down mechanical assembly and is fixed to a structure of the step-up/down mechanical assembly. The circuit for distributing lubricating fluid has a scoop with a first end that enters the collection reservoir and rotates with respect to the structure. The relative movement device provides a relative movement between the first end of the scoop and the collection reservoir such that the scoop rotates about an axis of rotation relative to the structure. As a result of this movement, the lubricating fluid in the collection reservoir flows through the distribution circuit and is conveyed to an element of the step-up/down assembly that is to be lubricated.

Abstract: A process for the production of a multi-branched bundle of electrical conductors having an electromagnetic shielding system includes partially surrounding a bundle of electrical conductors with a network of metal sheath elements. The metal sheath elements are interconnected to provide electrical continuity in the network and thereby form an electromagnetic shielding system for the bundle. A network of protective braid elements is braided either (i) between the bundle and the network of metal sheath elements, (ii) external to the network of metal sheath elements, or (iii) both (i) and (ii). The protective braid elements are filaments of a wear-resistant material that protect against frictional wear.

Abstract: An airplane door is swivellably disposed on a supporting arm, the supporting arm being swivellably disposed on an opening frame of a fuselage, and including a driving device for lifting and lowering the door and another driving device for swivelling the door and the supporting arm. During the movement of the lifting or lowering of the door, the transmission line of the driving device for the swivelling is uncoupled so that it is not unnecessarily mechanically stressed and a jamming of the transmission line therefore basically does not occur.

Abstract: A force transmitting linkage connects a piezoelectric actuator to a flap that is pivotably connected to a helicopter rotor blade. In a flap actuation control arrangement and method, a force transducer senses the force being transmitted through the linkage and generates a corresponding actual force signal, a flap position sensor senses the position of the flap and generates a corresponding actual flap position signal, a first controller receives a desired flap position signal and the actual flap position signal and responsively thereto generates a reference signal, and a second controller receives the reference signal and the actual force signal and responsively thereto generates a control signal that is provided to the piezoelectric actuator. This provides a real time flap actuation control with respect to highly dynamic forces as well as friction forces acting on the flap.

Abstract: A rotor blade arrangement includes a rotor blade with a hollow blade chamber therein, and a flap module removably arranged and secured in the blade chamber. The flap module includes a module housing received in the blade chamber, an actuator arranged in the housing, a flap pivotably arranged at an edge of the housing, and a power transmission linkage connecting the actuator to the flap. The module housing is inserted through an opening into the blade chamber, so that the flap protrudes and forms a continuation of the aerodynamic contour of the blade. The flap may be a trailing edge flap at the trailing edge or a leading edge nose flap at the leading edge of the blade. The flap module does not change the center of gravity of the blade. The entire flap module can be easily removed from the blade for adjustment, inspection, maintenance, repair or replacement.