Abstract: A rotor blade pitch control system (15) comprising a rotor blade (19a, 19b, 19c, 19d) rotatable about both a central axis (20) and a pitch axis (24a, 24b, 24c, 24d), a pitch drive rotor (32a, 32b, 32c, 32d) rotatable about the central axis independently of rotation of the rotor blade about the central axis, a pitch follower (40a, 40b, 40c, 40d) rotatable relative to the pitch drive rotor, the pitch drive rotor and the pitch follower having an eccentric axis (33a, 33b, 33c, 33d), a linkage (50a, 50b, 50c, 50d) between the pitch follower and the rotor blade configured such that the pitch follower rotates with rotation of the rotor blade about the central axis, the pitch drive rotor, the pitch follower and the linkage configured such that the pitch drive rotor may be driven to control an angular displacement of the pitch drive rotor relative to the pitch follower about the central axis and thereby control the pitch of the rotor blade about the pitch axis.

Abstract: A rotatable swashplate is rotatable relative to a stationary swashplate around a shaft and connects to a pitch control rod assembly. The rotatable swashplate includes an upper portion and a lower portion. The upper portion is extendable outside of a stationary swashplate and includes a plurality of lugs each configured to attach to a pitch control rod assembly, an innermost wall configured to receive a shaft, and a membrane. The lower portion is positionable within the stationary swashplate and has an outermost wall and at least one extension extending radially between the outermost wall and the innermost wall. The membrane extends radially over the at least one extension.

Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.

Abstract: A blade positioning system and method are provided to dynamically measure blade position during flight of a rotorcraft. In the context of a method, a blade of the rotorcraft is repeatedly illuminated by a light source during flight of the rotorcraft while the blade is rotating. The method also includes detecting radiation scattered from the blade in response to illumination of the blade. The method further includes determining at least one of a blade pitch angle, a blade flap angle, a blade leading position or a blade lagging position based upon the radiation that is scattered from the blade and detected. A rotorcraft is also provided that includes a chip-scale light detection and ranging (LIDAR) sensor configured to illuminate the plurality of blades while the blades are rotating in order to permit blade position to be measured or to illuminate terrain beneath the rotorcraft in order to provide an altitude measurement.

Abstract: A swashplate assembly of a rotary wing aircraft includes a first component, a second component arranged concentrically with the first component, and a bearing disposed between the first component and the second component. The bearing includes a spherical bearing and at least one bearing roller element and is operable to transmit torque between the first component and the second component.

Abstract: One embodiment includes a swashplate assembly for a rotary aircraft, including: a rotating ring configured to rotate with a drive shaft of the rotary aircraft; a non-rotating ring coupled to the rotating ring and rotationally decoupled from the rotating ring, wherein the non-rotating ring does not rotate with the rotating ring and drive shaft; an outer casing disposed around the gearbox; and an anti-drive mechanism to maintain the outer casing rotationally stationary relative to the gearbox, the anti-drive mechanism including a key and slot system between the gearbox and the outer casing.

Abstract: A rotor blade control system and methods therefor including a hub assembly pivotally attached to a rotor blade; a mast attached to the hub assembly; a swashplate assembly engaged with the mast and including a swashplate actuation mechanism pivotally coupled with the non-rotating ring at a plurality of coupling locations for moving the non-rotating ring and pivotally coupled with the base at a plurality of base locations, the swashplate actuation mechanism comprises a plurality of substantially triangular dual actuator assemblies that are independently and concurrently operable to move the respective coupling location so as to impart movement on the non-rotating ring. The swashplate actuation mechanism is configured to move the swashplate assembly about a longitudinal axis and a lateral axis in response to a cyclic input. The swashplate actuation mechanism is configured to move the swashplate assembly along the mast in response to a collective input.

Abstract: The present invention includes an apparatus and method for automatically adjusting the tracking of one or more blades comprising: a blade tracking adjustment mechanism connected to one or more blades of an aircraft; a blade tracking measurement system that measures the tracking of the one or more blades; and a computer that receives an output from the blade tracking measurement system with tracking information for each of the one or more blades; wherein the computer outputs instructions for the blade tracking adjustment mechanism to change a pitch of one or more of the blades to correct blade tracking.

Abstract: A first assembly can be configured to exert mechanical control forces on a second assembly through a tensioned and inelastic cable including steel. An electrical power source can be in electric communication with a first portion of the cable. An electrical power consumer can be in electric communication with a second portion of the cable. The cable can be a wire rope.

Abstract: An example of a hub for a tail rotor includes a body configured to couple to a mast of a rotor system, a trunnion disposed within the body, first and second shafts disposed on opposite sides of the trunnion, first and second end plates secured to the body, and first and second end bearings, the first end bearing disposed between the first shaft and the first end plate and the second end bearing disposed between the second shaft and the second end plate.

Abstract: A rotorcraft includes a flight control computer (FCC), a first rotor system, and a second rotor system. The first rotor system includes a first swashplate coupled to a first rotor and a first multiple actuators configured to move the first swashplate. The second rotor system includes a second swashplate coupled to a second rotor and a second multiple actuators configured to move the second swashplate. The rotorcraft also includes a first communications channel coupled between the FCC, a first actuator of the first multiple actuators, and a second actuator of the second multiple actuators. The rotorcraft also includes a second communications channel coupled between the FCC and a third actuator of the first multiple actuators.

Abstract: A quill shaft which translates rotational energy between a gear and a drive shaft having a drive shaft spline includes a first leg having an inner spline which meshes with the drive shaft spline and a second leg concentric with the first leg and radially offset and separated from the first leg by a gap. The second leg includes an outer spline which meshes with the gear. The first leg is connected to the second leg at one end to allow for change to a gap size during while translating the rotational energy between the gear and a drive shaft.

Abstract: A method for equalizing rolling moments at high advance ratios is disclosed including impelling an aircraft in a forward direction at an airspeed by means of a thrust source and rotating a rotor of the aircraft at an angular velocity with respect to the airspeed effective to cause a positive total lift on each blade due to air flow over the blades in the retreating direction when the blade is moving in the retreating direction. The rotor includes an even number of blades placed at equal angular intervals around the rotor hub. One or both of cyclic pitch and rotor angle of attack are adjusted such that a rolling moment of the retreating blade due to reverse air flow is between 0.3 and 0.7 times a rolling moment on the advancing blade due to lift.

Abstract: A control system for controlling at least collective pitch of rotor blades, of a multi-blade rotor with a rotor shaft in a rotary-wing aircraft, the control system comprising a non-rotating sliding sleeve that is mountable to the rotor shaft such that the non-rotating sliding sleeve is axially displaceable coaxially to an associated rotor axis on the rotor shaft, at least one actuator arm that is pivotally mounted to the non-rotating sliding sleeve and adapted for axially displacing the non-rotating sliding sleeve that is mounted to the rotor shaft upon activation, and at least one hinge support that is adapted for a hinged support of the at least one actuator arm.

Abstract: A folding yoke comprising a bilateral center yoke pivotally connected to separate foldable yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: An actuator includes a plurality of linear motors. A carriage is operatively connected to each linear motor to be driven by each of the linear motors. An output forcer rod is operatively connected to at least one of the linear motors to be driven by at least one of the linear motors. A position sensor is operatively connected to the output forcer rod to measure motion of the output forcer rod. A fly-by-wire system includes a plurality of electromechanical actuators. Each electromechanical actuator includes a plurality of linear motors. A flight control computer is operatively connected to the linear motors of each of the electromechanical actuators. The fly-by-wire system includes a plurality of hydraulic systems. Each hydraulic system is operatively coupled to a respective one of the electromechanical actuators.

Abstract: A rotary system and method to control feathering movement of a rotor blade. The system having a yoke arm configured to rotate a rotor blade. A first bearing and a second bearing are utilized to secure the rotor blade to the yoke arm and are configured to restrict longitudinal and transverse movement, while allowing feathering movement of the rotor blade relative to yoke arm.

Abstract: The present invention provides a system for engaging a fluid flow. The system comprising one or more foil members operationally connected to a feedback control loop system. In one embodiment, the foil member is a hydrofoil member or an airfoil member. The foil members are configured for one or more degrees of freedom of oscillatory movement within the fluid flow. The feedback control loop system comprises a sensor system, actuator system, and a controller system. The feedback control loop system configured for actuating the foil members and thereby optimizing the operation of the foil members to attain one or more optimization objectives. In operation, the foil members are situated in the fluid flow and are manipulated to attain one or more optimization objectives.

Abstract: A rotary system and method to control feathering and centrifugal forces of a rotor blade during flight. The rotary system having a hub assembly, which includes a hollow yoke arm to receive a spindle section of the rotor blade. A tension-torsion strap extends through the hollow yoke arm and couples the rotor blade and the hub assembly. The method includes allowing the spindle section of the rotor blade to pivot within the hollow yoke arm and controlling rotational and centrifugal movement of the rotor blade with the tension-torsion strap.

Abstract: A set of swashplates having a non-rotary swashplate and a rotary swashplate. The set includes drive means constraining the rotary swashplate and the rotor mast in rotation about the axis of rotation. The drive means are provided with a drive arm driving the rotary swashplate in rotation about the axis of rotation by plane connection means including a fork, the drive arm extending in elevation from a first end to a second end that is fastened to the rotor mast, the first portion being held captive laterally between two lateral branches of the fork, the fork being hinged to the rotary swashplate by movement means giving the rotary swashplate a degree of freedom to move in rotation about a radial direction of the rotary swashplate relative to the fork.

Abstract: One example of a rotorcraft blade control system includes a mechanical linkage to connect to a rotorcraft blade including a feather axis and a pneumatic muscle connected to the mechanical linkage. The system also includes a movement member connected to the mechanical linkage, the pneumatic muscle and the movement member to move the mechanical linkage to control movement of the rotorcraft blade on the feather axis. The pneumatic muscle can be a first pneumatic muscle and the movement member can be a second pneumatic muscle or a bias spring.

Abstract: A swashplate apparatus is provided and includes a first swashplate including outer and inner bodies and an intermediate portion defining a major groove between the outer and inner bodies, a second swashplate disposable in the major groove to be rotatable relative to the first swashplate, the second swashplate including an interior facing surface radially separated from the inner body to define a minor groove and defining a recess in which the rod end is disposable, a connector disposable in the recess to pivotably couple the rod end to the second swashplate and a plate element disposable in the minor groove and affixable to the interior facing surface of the second swashplate and the connector.

Abstract: A method and apparatus for reducing flapping loads imposed on a rotor are disclosed. The method may include flying a rotorcraft comprising an airframe, a rotor, a mast extending to connect the rotor to the airframe, a tilt mechanism, at least one sensor, and a computer system. The computer system may obtain in real time, from the at least one sensor, data characterizing at least one flapping load experienced by the rotor during the flying. Using the data, the computer system may issue at least one command to the tilt mechanism. In response to the command, the tilt mechanism may reorient the mast with respect to the airframe. This reorienting may lower the flapping load experienced by the rotor.

Abstract: A rotorcraft rotor comprises a blade having a pitch axis, a primary pitch horn for the blade, and a secondary horn opposite the primary pitch horn with respect to the pitch axis.

Abstract: A method for equalizing rolling moments at high advance ratios is disclosed including impelling an aircraft in a forward direction at an airspeed by means of a thrust source and rotating a rotor of the aircraft at an angular velocity with respect to the airspeed effective to cause a positive total lift on each blade due to air flow over the blades in the retreating direction when the blade is moving in the retreating direction. The rotor includes an even number of blades placed at equal angular intervals around the rotor hub. One or both of cyclic pitch and rotor angle of attack are adjusted such that a rolling moment of the retreating blade due to reverse air flow is between 0.3 and 0.7 times a rolling moment on the advancing blade due to lift.

Abstract: A blade-pitch control system for controlling a pitch angle of blades on a rotor has an input swashplate assembly having non-rotating and rotating portions, the rotating portion being operably connected to blade grips. A feedback swashplate assembly has non-rotating and rotating portions, the rotating portion being connected to the yoke for movement with the yoke during flapping of the yoke. Linear actuators connect the non-rotating portion of the input swashplate assembly to the non-rotating portion of the feedback swashplate assembly. Motion of the yoke during flapping causes a corresponding motion of the feedback swashplate assembly and input swashplate assembly for providing selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the grips.

Abstract: The present invention provides a method of driving a main rotor (2) of a rotorcraft (1) in rotation. A regulation setpoint (C) for a power plant (3) used for driving the main rotor (2) at a variable speed of rotation is generated by a control unit (4) and is transmitted to a regulator unit (5) for regulating the operation of the power plant (3). The value of an initial setpoint (NRini) is generated progressively and continuously depending on variation in the current value of the density (D) of the ambient air outside the rotorcraft (1). The value of the initial setpoint (NRini) is potentially corrected depending on predefined flight conditions of the rotorcraft (1). Prior to being transmitted to the regulator unit (5), the value of the regulation setpoint (C) is preferably limited to a range of acceptable speeds for driving the main rotor (2) in rotation.

Abstract: According to one embodiment, a rotor system includes an anti-rotation sleeve featuring an outer recess portion and a tilt sleeve positioned about the anti-rotation sleeve and having an opening therethrough. A first swashplate ring is positioned about the tilt sleeve and features an inner recess portion. An anti-rotation mechanism is disposed through the opening and at least partially in the outer recess portion and the inner recess portion. The anti-rotation mechanism is operable to prevent the first swashplate ring from rotating about the anti-rotation sleeve. A second swashplate ring is positioned about the first swashplate ring and rotatable about the anti-rotation sleeve.

Abstract: An aircraft with aerofoils including a main wing and a control flap that includes an adjustment flap. The aircraft includes an actuator for the control flap, as well as a sensor device for acquiring the position of the control flap, an arrangement of flow-influencing devices for influencing the fluid that flows over a segment of the main wing, and flow-state sensor devices for measuring the flow state. The aircraft includes a flight control device connected to the sensor device for acquiring the position of the control flap and to the flow-state sensor devices, and connected to the actuator and flow-influencing devices for transmitting actuating commands, and a flight-state sensor device connected to the flight control device for transmitting flight states. The flight control device includes a function that selects the flow-influencing devices that are operated for optimizing local lift coefficients on the aerofoil, depending on the flight state.

Abstract: A rotor assembly includes a rotor shaft rotatable about a rotor axis and a plurality of rotor blades operably connected to the rotor shaft. A rotor control assembly has a plurality of substantially concentric control tubes extending through the rotor shaft. Each control tube of the plurality of control tubes is operably connected to a rotor blade of the plurality of rotor blades such that movement of one or more of the control tubes of the plurality of control tubes along the rotor axis effects a pitch change in one or more rotor blades of the plurality of rotor blades. A method of controlling pitch of a plurality of rotor blades of a rotor assembly includes locating a plurality of concentric control tubes inside of a rotor shaft of the rotor assembly capable of changing a pitch of one or more of the rotor blades.

Abstract: According to one embodiment, a rotor system, comprise a mating element, a sleeve, a first swashplate ring, a locking element, and a second swashplate ring. The mating element having a first plurality of grooves a first plurality of ridges. The sleeve is positioned inside the mating element such that the sleeve prevents rotation of the mating element about the sleeve while allowing the mating element to translate along the sleeve. The sleeve has a second plurality of grooves mating with the first plurality of ridges and a second plurality of ridges mating with the first plurality of grooves. The first swashplate ring is positioned around the mating element, and the locking element prevents. the first swashplate ring from rotating about the sleeve. The second swashplate ring is rotatable about the sleeve.

Abstract: A blade-pitch control system has a swashplate configured for continuous rotation with an associated rotor and mast, and at least one link connects the swashplate to each blade of the rotor. The swashplate provides for collective control of the pitch angle of the blades through selective rotation of the swashplate about a swashplate axis while the swashplate is rotating with the rotor and mast. The system can be configured to provide for cyclic control of the pitch angle of the blades through planar translation of the swashplate or through tilting of the swashplate about axes generally perpendicular to the swashplate axis.

Abstract: An individual blade control system (IBCS) for a rotor system having a rotor hub is provided including a plurality of blade cuffs mounted to the rotor hub. Each blade cuff is configured to receive a rotor blade and rotate about a blade axis. A plurality of electrical actuators is mounted to the rotor hub adjacent at least one of the plurality of blade cuffs. Each electrical actuator is configured to rotate about an actuator axis. The plurality of blade axes and the plurality of actuator axes are arranged in a plane. Each electrical actuator is coupled to an adjacent blade cuff such that rotation of one of the plurality of electrical actuators causes a proportional rotation of one of the blade cuffs.

Abstract: A set (10) of cyclic swashplates (11, 12) for controlling the pitch of blades (4) of a main rotor (1) of a rotorcraft. The set includes a non-rotary swashplate (12) retained against rotation about an axis of rotation (AX) and a rotary swashplate (11) suitable for rotating about the axis of rotation (AX). The set (10) also includes drive means (100) with a drive arm (101) and an annular linear connection means (200) secured to the rotary swashplate (11). A first end (110) of the drive arm (101) is connected to the rotary swashplate (11) by the annular linear connection means (200). A second end (120) of the drive arm (101) is connected to a rotor mast (2) by slideway connection means (300) of the drive means (100).

Abstract: A direct orientation vector rotor (DOVER) for use on rotary wing aircraft includes a gear set for multidirectional rotor orientation based on the spherical coordinate system; an inclination mechanism, wherein the rotor is moved from the 0° horizontal position to an inclined position; a rotational turret, wherein the rotor is moved along the azimuth and wherein the inclination mechanism is housed; and a motion-adapted gear lubrication housing.

Abstract: A rotor system for a rotorcraft includes a rotor hub having a plurality of rotor blade pairs mechanically coupled to a rotor mast. A pitch link assembly is mechanically coupled to each rotor blade pair for controlling the pitch angle of each rotor blade pair in tandem. Each rotor blade pair has an upper rotor blade and a lower rotor blade. The plurality of rotor blade pairs rotor in a single direction and about a single axis of rotation.

Abstract: A rotor system for a rotorcraft having at least one rotor blade pair operably associated with a differential pitch assembly operably for controlling a pitch angle of an upper rotor blade and the lower rotor blade in the rotor blade pair. Operation of the differential pitch assembly changes the pitch of the upper rotor blade more severely than the pitch of the lower rotor blade. As such, the rotor system is configured to provide optimum pitch of the upper and lower rotor blades during a helicopter mode and an airplane mode.

Abstract: The main rotor control system includes a rise/fall swashplate assembly that is coupled to three triplex actuators. The swashplate assembly is configured to provide full collective and cyclic pitch controls. Each triplex actuator includes three piston/cylinder assemblies in parallel. Selective actuation of each triplex actuator is controlled by a fly-by-wire system in conjunction with three flight control computers and three hydraulic power packs. Integrated three function valves can be associated with an individual manifold for each piston/cylinder assembly of each triplex actuator, the integrated three function valve be configured to insure safe operation of the triplex actuator during a failure of a certain piston/cylinder assembly.

Abstract: The present invention relates to a transmission structure of a main propeller clamping seat and a swashplate of a remote-controlled helicopter. The main propeller clamping seat includes a pair of connection blocks at two ends thereof. The swashplate includes a pair of link rods which are connected with the pair of connection blocks of the main propeller clamping seat. The pair of link rods each has a pivot axle and an axle bolt. The axle bolt is inserted through the pivot axle and connected to the relative connection block. Through the link rods and the pivot axles, the main propeller clamping seat and the swashplate are direct driven to control the main propeller clamping seat and the angle of the wings quickly and precisely.

Abstract: A rotor system for a rotorcraft having at least one rotor blade pair operably associated with a differential pitch assembly operably for controlling a pitch angle of an upper rotor blade and the lower rotor blade in the rotor blade pair. Operation of the differential pitch assembly changes the pitch of the upper rotor blade more severely than the pitch of the lower rotor blade. As such, the rotor system is configured to provide optimum pitch of the upper and lower rotor blades during a helicopter mode and an airplane mode.

Abstract: According to one embodiment, a rotor system, comprise a mating element, a sleeve, a first swashplate ring, a locking element, and a second swashplate ring. The mating element having a first plurality of grooves a first plurality of ridges. The sleeve is positioned inside the mating element such that the sleeve prevents rotation of the mating element about the sleeve while allowing the mating element to translate along the sleeve. The sleeve has a second plurality of grooves mating with the first plurality of ridges and a second plurality of ridges mating with the first plurality of grooves. The first swashplate ring is positioned around the mating element, and the locking element prevents. the first swashplate ring from rotating about the sleeve. The second swashplate ring is rotatable about the sleeve.

Abstract: A heater with 360° rotation of a heated air stream is provided. The device includes a housing, a motor, an impeller, a heating element, an air stream deflector and a rotational engine. More specifically, the device is directed toward a portable space heater having an outward radial projection of a heated air stream in combination with 360° rotational movement for reducing air temperature stratification and uneven heating problems in a room.

Abstract: The present invention relates to a bellcrank (40) for a flight-attitude-changing linkage (27, 25A, 28A) of the variable gain type. The linkage (27, 25A, 28A) connects a manual flight control device of a rotary wing aircraft (1), e.g. a hybrid helicopter, to at least one airfoil of said aircraft (1) suitable for causing a change in flight attitude. Said bellcrank (40) includes first and second sliders (50, 52). Said first slider (50) is connected to a movable portion (57, 61) of a setpoint flight-attitude-changing linkage (24) that delivers a setpoint, with movements of said linkage causing the gain of said variable-gain linkage (27, 25A, 28A) to be adjusted, which gain is proportional to the position of said movable portion (57, 61).

Abstract: An assisted control system for controlling the attitude of a rotorcraft comprises a flight control device; at least one control member configured to act on an aerodynamic element of the rotorcraft; a mechanical connection connecting the flight control device to the at least one control member, the mechanical connection including at least one connecting rod moveable in translation, a crank device pivotably disposed about a stationary support shaft passing through the crank device, and a motor including a drive rotor and a stator configured to facilitate a pivoting movement of the crank device about the stationary support; a motor control device configured to control a rotation of the drive rotor relative to the stator; and at least one sensor configured to measure information representative of an operation performed by the flight control device under pilot control and to deliver a signal to the motor control device.

Abstract: A rotor control system including a collective control rod positioned internal to a rotor shaft, the rotor shaft for imparting torque to rotor blades; and a cyclic control rod positioned internal to and concentric with the collective control rod.

Abstract: A set (10) of cyclic swashplates (11, 12) for controlling the pitch of blades (4) of a main rotor (1) of a rotorcraft. The set includes a non-rotary swashplate (12) retained against rotation about an axis of rotation (AX) and a rotary swashplate (11) suitable for rotating about the axis of rotation (AX). The set (10) also includes drive means (100) with a drive arm (101) and an annular linear connection means (200) secured to the rotary swashplate (11). A first end (110) of the drive arm (101) is connected to the rotary swashplate (11) by the annular linear connection means (200). A second end (120) of the drive arm (101) is connected to a rotor mast (2) by slideway connection means (300) of the drive means (100).

Abstract: An assisted control system for controlling the attitude of a rotorcraft comprises a flight control device; at least one control member configured to act on an aerodynamic element of the rotorcraft; a mechanical connection connecting the flight control device to the at least one control member, the mechanical connection including at least one connecting rod moveable in translation, a crank device pivotably disposed about a stationary support shaft passing through the crank device, and a motor including a drive rotor and a stator configured to facilitate a pivoting movement of the crank device about the stationary support; a motor control device configured to control a rotation of the drive rotor relative to the stator; and at least one sensor configured to measure information representative of an operation performed by the flight control device under pilot control and to deliver a signal to the motor control device.

Abstract: An upper rotor control system is contained within an upper rotor shaft and upper hub assembly of a contra-rotating rigid rotor system. A collective servo assembly includes a hydraulic actuator that provides collective pitch to all blades through axial extension/retraction of the control rod relative the upper rotor shaft for collective pitch control of the rotor blades. The collective servo assembly includes a spherical bearing for attachment of the control rod to aircraft structure. An X-Y positioner assembly includes a bearing arrangement which allows the shaft to rotate, while the X-Y positioner assembly remains non-rotational therein. The X-Y positioner assembly includes a multitude of hydraulic actuators, orthogonally positioned, to tilt the control rod about the spherical bearing off the axis of rotation of the upper rotor shaft for cyclic pitch control of the rotor blades.

Abstract: An improved swashplate assembly of the main rotor of an AH-64 Apache helicopter includes a stationary swashplate and a rotating swashplate and a ball bearing between the swashplates, the ball bearing having an outer ring, an inner ring, two sets of balls between the inner ring and the outer ring, and a wire loop cage between the inner ring and the outer ring. The improvement includes that the inner ring, the outer ring and the balls are formed from an M50 alloy.

Abstract: A cyclic swashplate device for controlling rotorcraft blade pitch is disclosed for application to rotorcraft swashplates, in particular, in helicopters. A cyclic swashplate device controls the rotorcraft blade pitch. The device (10?), with rotating (10?) and non-rotating (14?) cyclic swashplates is designed in such a way that at least one of the two disks includes a modular link fitting assembly (46, 42) ensuring the links with the disk (12?, 14?) and the pitch connecting rods (6) and/or at least one driving device or with the pilot control devices (17) and/or at least one retaining device. Interconnecting fittings are attached rigidly and separately to an annular device, such as one of the rings (31?, 30?) of a bearing (21?) on the corresponding disk (14?, 12?).