Aerospatiale Societe Nationale Industrielle

Societe Nationale Industrielle Et Aerospatiale

Societe Nationale Industrielle Aerospatiale

Eurocopter France

Eurocopter

Societe Nationale Industrielle Et Aerospatiale Des Poudres Et Explosifs

Societe Nationale Ind. Aerospatiale

Jacques A Aubry

Jean J Mondet

Jean-Paul Merlet

Michel Deguise

Michel Bonfils

Michel R Bonfils

Daniel A Mauduit

Victor Y Yana

Rene L Coffy

Jean J Azeau

Andre Guillem

The blade includes at least one trailing edge swivelling air flow control flap, swivelling on the blade around an axis directed substantially along the span of the blade and the control flap, the swivelling of the control flap being controlled by an actuator gear mounted on the blade and including an actuator. The actuator includes a first rotating motor, the rotational speed of which corresponds to a frequency of swivelling of the control flap, and a second rotating motor which moves relative to each other two eccentrics mounted in series around the shaft of the first motor, the second motor rotating with one of the eccentrics, and a ring freely rotating around the eccentrics is driven in movements transmitted by a flexible arm transmission to the control flap. The frequency and amplitude controls of the swivelling of the air flow control flap are thus separated.

Rotor blade with swivelling air flow control flap

For braking a gyroplane rotor, a unit is proposed which comprises a disk brake equipped with a hydraulic actuator (26), which is integrated and has force amplification, as well as a mechanical transmission (54) connecting a control member such as a handle or lever (52) to the said actuator. The amplification effect is obtained by the section difference between a control piston (34) of the actuator directly connected to the mechanical transmission and a free piston (28) of the actuator by which the braking force is exerted.

Gyroplane rotor braking unit

The blade has its lower-surface and upper-surface skins of its shell, its front and rear filling bodies and its spar made of a composite material having the same thermoplastic matrix, preferably made of PEEK, reinforced preferably with carbon fibres. The spar is extended outside the shell by an integrated rooting part with linkage attachment, in a loop or laminate, in the same thermoplastic composite. The method consists in assembling the spar with the skins, after manufacturing these components in the form of prefabricated elementary pieces, by injecting under pressure a fluidized thermoplastic composite with short reinforcing fibres moulding the filling bodies.

Blade made of thermoplastic composite, in particular for ducted tail

A rotor head for a rotary wing aircraft having a plurality of rotor blades, such that each blade is coupled to the hub by an attachment assembly. The attachment assembly includes a thrust bearing device attached to the hub for allowing angular oscillations, and drag damping device coupled between the blade and the hub for damping movements of drag caused by rotation of the rotor head. The drag damping device has visco-elastic elements which are pivotable with respect to each other about a common axis. The damping device is also disposed to pivot in a flapping direction of the blade through a pivot joint.

Rotor head for rotary wing aircraft

A device for linking a blade to the hub comprising a laminate attachment at the end of the rooting part with torsion bars of the blade, the laminate attachment being in abutment against the pins for holding on the hub. The opposite blades of the rotor may be arranged angularly offset with respect to the other blades.

Blade-hub linkage device with a laminate attachment

The invention relates to a cylindrical elastomeric bearing with wide angular deflection comprising three cylindrical elements: a central element (1) and two lateral elements (2, 3) arranged either side of the central element (1). Each torsible cylindrical element is made up of a deformable elastomeric central part, relatively flexible angularly and relatively rigid radially, which is rigidly locked to an inner armature and to an outer armature; the outer armature (6) of the central element (1) and the inner armature (8, 11) of each lateral element (2, 3) are rigidly locked together so as to form a single part, the common armature (13). The inner armature (5) of the central element (1) is mounted on an inner sleeve (14) to which it is rigidly locked, and the outer armature (9, 12) of each lateral element (2, 3) is mounted in an outer sleeve (15) to which it is rigidly locked; inner sleeve (14) and outer sleeve (15) are coaxially arranged in such a way that the outer sleeve (15) and the inner sleeve (14) can rotate in relation to each other about their common axis with virtually no possibility of radial deflection.

Cylindrical elastomeric bearing with large angular deflection

A rotor head for a rotary wing aircraft rotor blades, such that each blade is coupled to the hub by an attachment assembly. The attachment assembly includes a thrust bearing attached to the hub for allowing angular oscillations, and drag damping device coupled between the blade and the hub for damping movements of drag caused by rotation of the rotor head. The drag damping device has hydro-elastic elements which are pivotable with respect to each other about a common axis. The damping device as also disposed to pivot in a flapping direction of the blade through a pivot joint.

The hydraulic damper has at least one restricted communication passage (47) between its two working chambers (8, 9) whose cross section is controlled by a viscous restriction valve (51) positioned via a control pressure of a fluid of a control damper with at least one secondary chamber (41, 42) delimited in a secondary cylinder (39) by a control piston (40), which cylinder and control piston are integrally attached, one to the main body (1), the other to the damping piston (4) of the damper, such that the pressure law of the control fluid positioning said valve (51) is linked to the relative displacements of the main body (1) and damping piston (4).

Hydraulic damper and elastic-return strut comprising such a damper

A joint is provided for connecting an end of a tube of composite material which is subject to relatively large axial stress to an annular metallic ferrule, and includes a composite tube composed of high strength fibers agglomerated by a polymerized synthetic resin having a wall and an annular metallic ferrule formed as a band. The ferrule has in cross-section the shape of a segment of a circle including a curved portion and a flat portion, the curved portion of the ferrule facing the composite tube. The ferrule is embedded in a receiving surface of the wall of the tube, and the flat portion of the ferrule is flush with adjacent regions of the receiving surface of the tube. An end member is included having an extending portion which engages the ferrule, and a complementary connecting device is disposed between the flat portion of the ferrule and the extending portion of the end member, for connecting the tube to the end member. The band and the complementary connecting arrangement together constitute an anchoring element for anchoring the tube of composite material to the end member.

Device for connecting the ends of a composite tube subjected to severe

An individual pitch control device for the blades (7) of a rotor of a rotor craft employing respective rotating linear jacks (29) for controlling the pitch of the rotor blades. The linear jacks are implanted in a rotating support (25) which is driven in rotation with the rotor. The jacks (29) include rods (31) which are connected via additional rods (33) to drive pitch control levers (24) for each respective blade. The jacks (29) are linear, electrohydraulic, dual-action jacks having at least one body, and are supplied by control servovalves (36) which are also mounted in a rotating reference system. The servovalves (36) are supplied from a hydraulic circuit in a fixed reference system positioned on the rotor craft, having at least one hydraulic collector (27) which is at least partially rotating.

Individual pitch control device for blades of rotors of rotor craft by

The resilient return strut is of the elastic-hydraulic type with incorporated linear damping by throttling a high-viscosity fluid, and comprises a damper (1) mounted between two return springs (2, 3) in elastomer-based sleeves (17, 18), undergoing a shearing action and sealing the chambers (34, 35) set off within the body of the damper (12) by a transverse wall (10) which marks off a permanent throttling passage around a central brace (23). Limiting valves equipped with spring-leaves (45) sealing the holes (40) bored in the wall (10) increase the throttling section. A compressed-air system (52), mounted in a spring (2), compensates for thermal expansion of the fluid. The device is used with helicopter rotors.

Resilient return strut of the elastic-hydraulic type with incorporated

In this elastic strut incorporating a hydromechanical resonator having a weight/spring system of the type providing a hydraulic amplification of the displacement of the beating weight (7), the weight mounted between two opposed return springs constitutes a double-sided hollow piston slidably mounted on two coaxial opposed cylinders (6) in a closed chamber filled with a liquid (10) in an inner tubular element (1) disposed in an outer tubular element (2) with which it defines, at each end, a chamber (18, 26) filled with liquid onto which opens one of the cylinders (6), the elements (1, 2) constituting the body of the strut being coaxially movable relative to each other and fixed together at each of their ends in a sealed and elastic manner by bearings composed of an elastomer material.

Elastic strut having an integrated hydromechanical resonator in

The invention relates to a control device for monocyclic pitch in a fixed reference system and multicyclic pitch in a rotating reference system, for the blades (7) of a rotor craft. In addition to conventional swashplates (27, 38), one (38) of which rotates (39) on the other (27) held in rotation by a nonrotating compass (28), but which slides axially (4) and oscillates (25) about the rotor mast (1), through the action of pilot control (30), it comprises multicyclic jacks (45) in a number equal to the blades (7), and each of which is implanted in the rotating plate (38) and directly drives a pitch control rod (44) of a corresponding blade (7). Each multicyclic jack (45) is a dual-action, hydraulic linear jack controlled by a servovalve (49) also implanted on the rotating plate (38).

Control device for monocyclic pitch in a fixed reference system and

A hydraulic device for the individual control of the pitch of a helicopter rotor blade by a rotary hydraulic jack, the stator vanes of which are integral with a sleeve fitted on the hub. The jack rotor carries rotor vanes movable relative to the stator vanes and delimiting with these chambers of variable volume fed by a servo-distributor controlled as a function of pilot signals and signals from a detector of the angular position of the blade about its pitch axis. The jack is integrated in a pitch bearing and in an elastic ball joint integrated in a rotary hydroelastic shock absorber with vanes for lamination of a viscous fluid. The shock-absorber rotor is connected rigidly in terms of rotation about the pitch axis to the rotor of the jack and is connected to the blade by a rigid cuff.

Hydraulic device for individual control of pitch of a rotor blade

Contact link for flight controls of aerodynes, especially helicopters. The link comprises a rod (2) mounted axially slideably over a limited stroke under tension and under compression in a body (1). A leaf spring (35) subjected to compressive buckling prestress is accommodated in a recess (27) of the rod (2) between two supports (36, 37) pushed against stops of the rod (2) and stops of the body (1). Under any axial tensile or compressive force higher than the prestress of the leaf spring (35), one of the supports (36, 37) is brought nearer to the other, so that the leaf spring (35) works by buckling, and its central part increases its deflection to an extent amplified in relation to the axial stroke of the rod in the body and shifts radially a movable contact member (55) actuating an electrical contactor (45) fastened in the recess (27) of the rod (2). The contact link is used for equipping flight controls for cutting in or cutting out an automatic pilot.

Growing community of inventors

Cabries, France

Jacques A Aubry