Abstract: A fluid temperature control installation for a rotorcraft, the installation comprising a system for cooling a main transmission (3) and a system for temperature control of the ambient air (32) of a cabin (16). A heat exchanger (8) is fitted with a bladeless ventilator (9). A source air stream (11) generated by an accessory compressor (5) driven by the main transmission (3) passes through the heat exchanger (8) where it takes heat. The source air stream (11) is distributed selectively to the bladeless ventilator (9) to generate a cooling air stream (13) passing through the heat exchanger (8), and/or is distributed to the cabin (16) after passing through the heat exchanger (8) in order to heat the ambient air (32) of the cabin.

Abstract: The present invention relates to fire-protection storage means (10) having a fire-protection bag (20) suitable for being fastened to a partition (9) of a hold (5) of a vehicle (1). Said fire-protection bag (20) is provided with airtight closure means (30), the fire-protection bag (20) having a vacuum pump (40) and extinguisher means (50) for extinguishing a fire that occurs in the interior (INT) of said fire-protection bag (20).

Abstract: A system and a method for controlling a rotorcraft (1) in yaw (Y). The control system comprises a plurality of drive channels that operate an anti-torque rotor (4) of the rotorcraft (1). A first drive channel makes use of a rudder bar (13) including a set of pedals operated by the human pilot of the rotorcraft in order to control the anti-torque rotor (4). A second drive channel includes an autopilot. A third drive channel includes objective-type flight control means comprising a movable control member (12) that is operated by the human pilot and that continuously issues control signals (11) relating to a state of progression that the rotorcraft (1) is to achieve. Use of the second drive channel and of the third drive channel depends on inhibit means (19) for inhibiting operation thereof, which means are activatable by detector means (37) for detecting operation of the rudder bar (13).

Abstract: A method of preparing a test for an electronic system including a plurality of pieces of equipment interconnected by at least one communications link, in which method, in order to perform the test, use is made of a test bench appropriate for the electronic system under test, which test bench is connected to the system and controlled in application of a command sequence established from at least one informal functional specification; while preparing the test, the informal functional specification, the command sequence, and a link identifying the informal functional specification from which the command sequence was established are all recorded so that after execution of the command sequence and after the test results have been recorded, it is possible to read the link and identify unambiguously the informal functional specification that corresponds to the test results obtained.

Abstract: A blade (20) of a rotor (5), the blade (20) having a suction side (21) and a pressure side (22) extending transversely from a leading edge (23) towards a trailing edge (24) and extending spanwise from a root section (31) towards a free end section (41). The blade (40) comprises, going from the root section (31) towards said free end section (41): a root zone (30); followed by rounded zone (35); said rounded zone (35) presenting rounded pressure and suction sides (22?, 21?) departing from said main plane (P1) in a direction (Z) parallel to the axis of rotation (AXROT) of said blade.

Abstract: A storage tank (25) of a storage system. The storage tank (25) includes a container (30) and a dynamic ventilation line (35) incorporated therein, said dynamic ventilation line (35) being provided with an air-no-fuel valve (45) that shuts off in the presence of fuel, the air-no-fuel valve (45) communicating with an internal space (INT) of the container (30) via an upstream pipe (40) placed inside the container (30), a downstream pipe (50) secured to a wall (31) of the container (30) extending from the air-no-fuel valve (45) and opening out into a dynamic air intake (53) communicating with the outside air (200), said storage tank having at least one communication orifice (300) for communicating with other tanks.

Abstract: A skin-stiffener transition assembly (1) with a skin (4) and two L-shaped fiber-reinforced fabric preforms (2, 3) for a flange and a composite gusset filler (5) integrated between said skin (4) and said two L-shaped fiber-reinforced fabric preforms (2, 3). The skin (4) comprises two separate skin layers (7, 8) and the flange comprises a flange layer (6), each of said skin layers (7, 8) and said flange layer (6) being provided with cut outs (9, 10) along one side. Said skin layers (7, 8) and the flange layer (6) are attached to the composite gusset filler (5) with at least one of its cut-outs (9, 10) to one side of the essentially polygonal cross section of the composite gusset filler (5) and with at least one of its adjacent cut-outs (9, 10) to another side of the essentially polygonal cross section of the composite gusset filler (5).

Abstract: A pitching stabilization means (10) having at least one stationary stabilization surface (20) extending in a thickness direction from a bottom face (21) to a top face (22) and in a transverse direction from a leading edge (23) towards a trailing edge (24). The stabilization surface (20) has at least one slot (30) passing through said thickness of the stabilization surface (20) from said top face (22) to said bottom face (21), said slot (30) being arranged within the stabilization surface (20) between said leading edge (23) and said trailing edge (24) so as to allow a flow of air coming from a rotor to pass from said top face (22) towards said bottom face (21).

Abstract: An aerodynamic blade attachment (1) for a bearingless rotor, particularly a main rotor, of a helicopter, comprising: an airfoil blade (2) having a tip end and a root end and having a pitch axis from said tip end to said root end; a flexbeam (3); a control cuff (4, 22) enclosing and extending along said flexbeam (3) and a separable junction arrangement between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Said junction arrangement is mechanical between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Removable fasteners (5, 6) connect said root end of said airfoil blade (2) and said control cuff (4) with said flexbeam (3). Said junction arrangement comprises fairing means (10, 27, 28, 31, 32 and 39) encompass the removable fasteners (5, 6) and said flexbeam (3).

Abstract: A method of forming a rotorcraft blade is provided. A first support shaft (8) is secured to a rigid attachment filler (1) of the blade that is reversibly fastened to a mandrel (20). Fibers are placed around the assembly comprising said attachment filler (1) and said mandrel (20) in order to fabricate a spar of said blade, said spar (40) then including a succession of fiber layers (31, 32, 33) that hold said attachment filler (1) captive at the root (51) of said blade. Said first shaft (8) is removed after the spar has polymerized.

Abstract: The invention provides a control mechanism for controlling flight of an aircraft, the control mechanism comprising a cyclic control stick (1) that is mounted to tilt (B1, B2) on a carrier structure (4) and that is in engagement with remote mechanical transmission members (2, 3). The stick (1) is arranged as a telescopic member provided with locking means (20) for locking it in a normal-use retracted position, and is equipped with deployment means (21). Unlocking of the locking means (20) and use of the deployment means (21) depend on an assistance device (17) associated with the stick (1) being in a defective state. In the event of such a defective state being detected, the stick (1) is suitable for being deployed so as to increase the comfort of the pilot while manipulating it.

Abstract: A ball joint device (1) having an outer cage (2) and a spherical ball (3), anti-friction means (5) being interposed between the outer cage (2) and the spherical ball (3). The ball joint device (1) comprises wear detection means (10) co-operating with the anti-friction means (5) between the outer cage (2) and the spherical ball (3), the wear detection means (10) having a first color that is distinct from a second color of said anti-friction means (5) in order to indicate wear visually by means of a change in color.

Abstract: An electrical power supply device (10) comprising a pole (11), said pole (11) having a non-rotary casing (15) and a rotary casing (12) provided with fastener means (14) for fastening to a mast. The pole (11) includes a non-rotary converter (20) fastened to the non-rotary casing (15) and generating AC at a frequency higher than one kilohertz. The pole also includes a rotary transformer (25), said rotary transformer (25) having a primary member (26) secured to the non-rotary casing (15) and a secondary member (27) secured to the rotary casing (12), the primary member (26) being connected to the non-rotary converter (20) to receive said AC, and the secondary member (27) being suitable for electrically powering equipment (100) of a rotor (2).

Abstract: The present invention relates to a method of reducing the vibration of a lift and propulsion rotor (5) of a rotorcraft (1), the rotor having a plurality of airfoil assemblies (10) that perform rotary movement around a drive axis (AX) of the rotor (5), each airfoil assembly (10) comprising a blade (20) extending longitudinally from a root (22) suitable for being fastened to hinge means (4) of a hub (6) of said rotor (5) to a free end (21), a first distance (D1) extending between said free end (21) and said hinge means (4). In the method, said first distance (D1) is caused to vary cyclically so that the projection (TR) of the center of gravity (Cg) of a blade (20) on a horizontal plane (P) perpendicular to said drive axis (AX) and containing said hinge means (4) describes a circle.

Abstract: A method of controlling and regulating a rotorcraft presenting a speed of advance that is high and stabilized, the rotorcraft including at least a main lift rotor (10), at least one variable pitch propulsion propeller (6), and at least one power plant for driving the main rotor(s) (10) and at least one propeller (6), said method consisting in using a first loop for regulating pitch or attitude, and a second loop for regulating speed by means of a control over the mean pitch of the propulsion propeller(s) (6), wherein the method further consists in controlling the deflection angle of a horizontal tailplane (30, 25, 35) by using a third loop for controlling and regulating said deflection angle of the horizontal tailplane (30, 25, 35) in order to minimize the total power consumed by the main rotor (10) and the propulsive propeller(s) (6), for a given speed and attitude.

Abstract: The invention provides a mechanism for attenuating torque pulsations between an engine (2) and a rotor (1) of a rotorcraft. Torsion means (5) are interposed between the driving and driven shafts and comprise a torsion shaft (6) axially engaged with the drive shaft (3) and the driven shaft (4) an inlet shaft (9) and an outlet shaft (10) respectively engaged with the drive and driven shafts (3, 4) a lever system (7) that extends radially relative to the torsion shaft (6) and that has the inlet and outlet shafts (9, 10) hinged thereto via points (11, 12) that are spaced apart; and a mass (8) carried by said lever arm (7) at its free end (13) radially farthest away from the axis along which the torsion shaft (6) extends.

Abstract: A regulator device (10) for regulating a turbine engine (3). The regulator device (10) includes mechanical power take-off means (100) for taking off power mechanically from a gas generator (4), and an engine computer (20) controlling said engine (3) to comply with at least a first limitation (LimTET, LimT45) of a temperature (TET, T45) of the gas within the engine, and with a second limitation (LimNg) of a speed of rotation (Ng) of the gas generator (4). The engine computer (20) determines whether the speed of rotation (Ng) of the gas generator has reached said second limitation (LimNg), and whether said temperature (TET, T45) has reached said first limitation (LimTET, LimT45). An avionics computer (30) causes the mechanical power take-off means (100) to operate if the speed of rotation (Ng) of the gas generator (4) has reached said second limitation (LimNg), and if said temperature (TET, T45) has not reached said first limitation (LimTET, LimT45).

Abstract: A device for monitoring the sealing state of a casing (2) of a transmission box (1) of a rotorcraft. An open airflow circuit (7) fitted with a suction generator member (10) is connected to a vent (5) of the casing (2). Regulator means (12) maintain stable suction in the airflow circuit (7) relative to a setpoint threshold (S), the regulator means being controlled in response to a pressure gauge (13) for measuring the suction generated inside the airflow circuit (7). The device is used on the ground to detect a source of leakage in the casing (2) and in flight to retain lubricant inside the casing (2) in the event of there being a source of leakage.

Abstract: A method essentially comprising a step of storing each plot mesh. Each plot mesh receiving plots sent thereto by detector means and retaining in memory at least the altitude of the highest plot and the number of plots neighboring said highest plot in said mesh. The altitude and the number of plots neighboring are updated each time a new plot is sent to the plot mesh. A step of rejecting plot meshes is presenting a number of neighboring plots that is less than a predetermined rejection threshold value. The rejection threshold value is a function of the position of the mesh relative to the detector means. A step is preparing the local terrain elevation database from the plot meshes (M(i,j)) that are not rejected.

Abstract: A fluid flow network for feeding fuel to at least one engine (2) of a power plant driving rotation of at least one rotary wing (1) of a rotorcraft. The fluid flow network includes a suction pump (3) for sucking fuel from a feeder tank (5) via a transfer circuit (4). The feeder tank (5) is fed with fuel from a main tank (9) by a transfer circuit (10) including a transfer pump (12). The transfer pump (12) is also a pump for priming the suction pump (3) by means of a feed ejector (15) provided on the feed circuit (4) and immersed in the feeder tank (5).