Abstract: A connection arrangement for detachably connecting a first flexible tank and a second flexible tank in an aircraft includes a latching device, a first tubular connecting element attached to the first tank, and a second tubular connecting element attached to the second tank. The first and the second connecting elements are detachably connected to each other using the latching device. In a connected state of the connecting elements, fluid exchange can take place between the first and the second tanks via the first and the second connecting elements, the latching device is disposed inside one of the first and second flexible tanks and is actuatable from outside the respective flexible tank.

Abstract: The invention concerns a sound-proofing panel, in particular a rotorcraft structural or lining panel: the sound-proofing panel (1) comprises at least two opposite plates (2, 3, 5, 6) forming between them a closed internal space (4), and an aggregate (7) including at least solid elements (8) in contact and which fills entirely said internal space (4).

Abstract: An undercritical drive shaft and a method of producing the undercritical drive shaft from fiber composite material is disclosed. The drive shaft, which is produced of fiber composite material and is to be used as an undercritically operating shaft, has a high damage tolerance with respect to resistance to torsion and the manufacturing process requires lower expenditures. For the drive shaft, the fiber composite material consists of several successively individually wound-up webs of prepreg. For the method of producing the drive shaft from fiber composite material, as the fiber material, the web-shaped prepreg is wound onto the winding spindle and this prepreg is deaerated and simultaneously compressed by the winding-on of a thermoplastic woven band which is prestressed in a defined manner. The thermoplastic woven band is unwound again and additional prepreg layers are then wound up which are then deaerated and compressed in the same manner by a thermoplastic woven band.

Abstract: A pivoting power transmission unit is provided for transmitting rotational drive to a rotor configured to revolve about an axis of rotation and configured to be swivelled about a pivot axis substantially perpendicular to said rotation axis. The unit comprises a casing mounted between two parts of a support by two bearings co-axial with the pivot axis. Each bearing includes a stationary part attached to the support, swivelling part attached to the casing and a wear take-up ring disposed therebetween. The unit further comprises a device to take up axial play between the casing and the support. The device includes an annular piston, sliding axially in a chamber fed with fluid under pressure, and bearing against an axial end of the wear take-up ring.

Abstract: The blade includes a current part (1) having an aerodynamic profile enclosing a spar (7) and extending from blade tip (4) to a blade root (3) provided with a pitch sleeve (21), through which twisting arm (6) passes and protrudes beyond blade root (3), and comprising a first part of a bundle (5) of superimposed and elongated metal strips, current part (1) including a block (13) based on synthetic material molded in form in a single piece around spar (7), comprising a second part of bundle (5) extending in line with the first part forming the twisting arm (6) and cooperating with the anchoring devices (14, 17) of the block (13) based on synthetic material around the spar (7).

Abstract: A pitch control device for a blade of a tilting rotor of a convertible aircraft. The pitch control device is external to a rotor hub which is driven in rotation by a mast and connected to the latter by a mechanism for tilting the hub as a whole, each blade is connected to the hub by a coupling for retaining and hingeing the blade in pitch about its pitch change axis. The device includes a pitch change lever, integral in rotation with its blade root about its axis, a pitch control rod, a bellcrank pivoting about a pin on a drive plate integral in rotation with the mast, and to which the pitch control rod is hinged, the bellcrank being also hinged to a link rod connected to the pitch change lever.

Abstract: A test rig for testing a power transmission device, having an input shaft, an output shaft and a casing, may include a first assembly having a coupling shaft that is connected by a rigid and coaxial coupler to the output shaft of the power transmission device. A second assembly of the test rig is connected to the input shaft. The casing is mounted on a position-adjustable support, and a controllable adjusting device adjusts the position of the support. The adjusting device adjusts the position of the support so as to apply forces and moments acting along six degrees of freedom of the casing to the casing, and the support and the adjusting device bring the casing into a spatial position such that all the forces and moments likely to be generated on the output shaft are applied to the casing.

Abstract: According to the invention, this system comprises a main device (2) and an auxiliary backup device (3), which comprises: at least one reservoir (10) of lubricating and cooling liquid independent of the main device (2); at least one source (11) of pressurized gas; and at least one spray nozzle (17, 18) which is fed, on the one hand, with lubricating and cooling liquid at a pressure at most equal to 2 bar (2.10−5 pascal) from said reservoir (10) and, on the other hand, with pressurized gas from said source (11), said nozzle being able to spray a mist of lubricating and cooling liquid onto said mechanical assembly (1) so as temporarily to supplement the defective main device (2).

Abstract: A test bench for testing a power transmission device may include, a first assembly that can be connected to an output shaft of the power transmission device to be tested, a second assembly that can be connected to an input shaft of the power transmission device, and a transmission shaft that connects the first and second assemblies together. The second assembly includes a subassembly having a first module that is adjustable in position and orientation and able to be connected to the input shaft of the power transmission device. Additionally, the second assembly includes a second module that is coupled with the first module and provides a kinematic adaptation between the first module and the power transmission device.

Abstract: A device for the automatic control of a helicopter may include two objective algorithms associated with the collective axis, each of these algorithms automatically determining a command for operating the collective pitch of the blades of the main rotor of the helicopter. The device may also include two objective algorithms associated with pitching axis that function simultaneously and automatically determine a command for operating the tilting of the disk of the main rotor. A first selection device automatically selects the objective algorithm whose command is used for the collective axis, and a second selection made by the first selection device, the objective algorithm whose command is used for the pitching axis.

Abstract: An energy-absorbing connecting strut comprises a substantially straight rigid body with means of connection to two components which it links, and undergoing tensile/compressive stresses. The body comprising a buckling portion with a calibrated buckling load corresponding to a compressive load threshold, a hollowed portion housing a component absorbing energy by plastic deformation in compression, and a piston moving integrally with a rigid axial end part of the body. The body is configured so that under a compressive load greater than the compressive load threshold, the buckling portion deforms causing axial shortening of the connecting strut and movement of the piston with the rigid part, so that the piston crushes and plastically deforms the energy-absorbing component, limiting the load amplitude. The energy-absorbing strut may be used as a suspension strut of a main gearbox on the structure of a rotary wing aircraft.

Abstract: An apparatus for operating a controlled member on a rotary-wing aircraft is provided with at least one control intended to be subject to the action of a pilot of the rotary-wing aircraft and capable of moving a linkage, a device connected to the linkage for operating the controlled member as a function of movement of the linkage, a ram incorporated into the linkage which is capable of influencing the movement of the linkage as a function of control commands received, a trim device capable of acting on the control and on the linkage as a function of control commands received, a computer determining the control commands which are transmitted to the ram and to the trim device, and at least one sensor which is capable of measuring the values of a parameter that represents an action exerted by a pilot of the rotary-wing aircraft on an auxiliary control.

Abstract: The bearing is an angular contact ball bearing with two asymmetric rows of balls, with a one-piece outer race and an inner race having two matched inner half-races side by side and able to be axially preloaded against each other when the bearing is mounted on the shaft of a gear the set of teeth of which cantilevers out from the bearing which has its row of larger-diameter balls on the same side as the set of teeth. Preloading may be provided by a nut screwed onto the shaft and tightened up against one of the inner half-races until the latter bears against the other inner half-race. A lock nut may hold the nut in position. The gear with its set of teeth and its shaft, the bearing with its large-diameter balls on the same side as the set of teeth, and the preloading device constitute a modular assembly, premounted and preloaded prior to fixing to a housing using a flange belonging to the outer race.

Abstract: Structural assembly of part of an aircraft and aircraft, particularly a rotary-wing aircraft, comprising such a structural assembly. The structural assembly comprises an outer structure (3) equipped with a floor (4), a cladding assembly (5) comprising cladding panels (6) forming a self-supporting envelope (7) which is arranged inside (9) the outer structure (3) and mounted on the floor (4), and a connecting system (10) for connecting the self-supporting envelope (7) to the outer structure (3). The connecting system (10) comprises a number of connecting means (11) which, by rigid and permanent connections, fix the self-supporting envelope (7) to the outer structure (3) and perform this rigid and permanent fixing only between the floor (4) of the outer structure (3) and ends (12) of cladding panels (6) of the self-supporting envelope (7).

Abstract: An impact-absorbing, load-limiting connection device includes a first connection structure, a second connection structure, a guiding mechanism, and at least one impact-absorbing, load-limiting sacrificial element disposed between the first and second connection structure. At least one of the first and second connection structures is moveable with respect to the other in a predetermined direction of movement corresponding to an anticipated main impact direction. The guiding mechanism is configured to guide at least one of the first and second connection structures along the direction of movement and includes at least one transverse force-absorbing guide element configured to absorb a force in a direction transverse to the direction of movement.

Abstract: On the rotor, between each blade and the member for linking with the hub, an electrical connecting cable comprises a first section of which one part is held above that one of the two blade pins which is the pivot pin about which the blade can be folded by pivoting, once the other blade pin has been removed. This holding is provided by a cradle formed in a cable support connected to the pivot pin, and by a collar articulated to one edge of the cradle and which can be folded down into the closed position onto the opposite edge of the cradle, to which this collar can be connected detachably by at least one detachable retaining element. The section of cable is manually released from the collar and from the cradle before the removal of the removable pin, which precedes folding, so that this section of cable deforms naturally, following the pivoting of the blade.

Abstract: A method for avoiding a collision of a rotating rotor blade of a rotary-wing aircraft with a blade vortex, and a device for executing the method. An aerodynamic parameter of the rotor blade of a rotary-wing aircraft is controlled, (for example, variation of the angle of incidence of the blade or profile variation of the blade), using a signal processing device that includes at least one open-loop and/or closed-loop control device, in such a way that a collision of the rotor blade with blade vortices becomes avoidable. The frequency content from the signal of the sound-pressure sensors is rapidly and precisely found. The harmonics are progressively adapted. A lesser calculation requirement per step and increase accuracy, as compared with an FFT analysis, is provided.

Abstract: A device for determining in real time the behavior of a craft may include a first device for determining, from a current linear model modeling the behavior of the craft, a vector &lgr; illustrating an equilibrium state. A second device is connected to the first device for determining from vector &lgr; the values at equilibrium of parameters of the linear model. A third device is connected to the second device for calculating, from at least some of the parameter values, the dynamic component of the behavior of the craft. A fourth device is connected to the first and third devices for introducing the dynamic component into the linear model so as to obtain a new current linear model and to deduce the behavior of the craft therefrom.

Abstract: Device and process for regulating the power of the engines of a rotary wing multi-engine aircraft. The regulating device (1) comprises, in addition to main regulating systems (2, 6) associated with the engines (M1, M2) of the aircraft, auxiliary regulating systems (12, 13) associated with said engines (M1, M2) and means (10, 11) for determining the speeds of rotation of the engines (M1, M2). Each auxiliary regulating system (12, 13) is capable of automatically adjusting the flow rate of fuel in such a way as to slave the speed of rotation of the associated engine, when its main regulating system has failed, to the speed of rotation of the other engine of the aircraft.

Abstract: An structurally simplified actuation mechanism for swinging an aircraft door from a frame on an aircraft fuselage. The actuation mechanism includes a cantilever rotatably mounted to the frame and including a receiving region, a universal joint supported in the receiving region, and an actuation device disposed on the cantilever. The universal joint defines a vertical axis of rotation and is configured to receive a door fitting. The actuation device includes an output drive connected to the universal joint at the vertical axis of rotation.