Moog Gmbh

John Kopp

Christopher Mazurkiewicz

Matthew Schleife

Thomas P Neal

A rotor blade pitch control system () comprising a rotor blade () rotatable about both a central axis () and a pitch axis (), a pitch drive rotor () rotatable about the central axis independently of rotation of the rotor blade about the central axis, a pitch follower () rotatable relative to the pitch drive rotor, the pitch drive rotor and the pitch follower having an eccentric axis (), a linkage () 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.

Rotary-wing aircraft individual rotor blade pitch control system

A vibration suppression unit for an aircraft comprising a vibration control frame adapted to be mounted to the aircraft and to rotate about a central axis, a first motor configured to rotate the vibration control frame about the central axis, a second motor configured to rotate a first and second center of mass about a first and second axis or rotation, a third motor configured to adjust a variable distance between the first and second centers of mass and the first and second axis of rotation, respectively, and a controller for receiving input signals and outputting command signals to the first, second and third motors.

Variable rotary mass vibration suppression system

A vibration suppression unit for an aircraft comprising a mass having a center of mass, a first rotor, a second rotor, a first coupling between the first rotor and the mass, a second coupling between the second rotor and the mass, the first and second couplings having first and second coupling centers offset perpendicularly from a central axis of rotation by different radial distances and offset in axially from the center of mass with respect to the central axis by different axial distances, the first and second coupling centers having a selectively variable displacement angle defined by the angle between lines extending between the central axis of rotation and the first coupling center and the second coupling center, respectively, wherein the first rotor and the second rotor are controllable to produce a vibration control force vector having a controllable magnitude and frequency about the central axis.

Variable rotary pendulous mass vibration suppression system

A vibration suppression unit for an aircraft comprising a mass assembly having a center of mass and a frequency rotor having a frequency center axis offset from a central axis of rotation and driven to rotate about the central axis, a vibration control amplitude rotor rotationally coupled to the mass assembly and having an amplitude center axis offset from the central axis driven independently of the frequency rotor to rotate about the central axis, the amplitude center axis and the frequency center axis having a selectively variable displacement angle defined by an inclusive angle between a line extending between the central axis and the amplitude center axis and a line extending between the central axis and the frequency center axis, wherein the amplitude rotor and the frequency rotor are controllable to produce a vibration control force vector having a controllable magnitude and frequency about the central axis of rotation.

Variable rotary radially supported mass vibration suppression system

An actuator system comprising a shared link arranged to pivot about a first axis relative to a reference structure, a controlled element arranged to pivot about a second axis relative to the reference structure, a first member arranged to pivot about a third axis relative to the shared link and a fourth axis relative to the controlled member, a first actuator arranged to control a first variable distance between the third axis and fourth axis, a second member arranged to pivot about a fifth axis relative to the shared link and a sixth axis relative to the controlled element, a second actuator arranged to control a second variable distance between the fifth axis and the sixth axis, the system configured such that a change in the first variable distance causes rotation of the controlled element about the second axis when the second variable distance is constant and vice versa.

Multiple actuator and linkage system

A servovalve comprising a motor, a motor bias mechanism, a first stage valve having a first position, a second stage valve movable with movement of the first valve, a reference member in fluid communication with the second valve, a transfer link acting between the first valve and the reference member, an eccentric drive acting between the motor and transfer link, wherein movement of the motor causes the transfer link to move the first valve, movement of the first valve causes the second valve member to move, movement of the second valve applies on the reference member a pressure differential from a load, the pressure differential on the reference member causes movement of the reference member, and movement of the reference member causes the transfer link to move the first valve back to the first position.

Closed center pressure flow control valve

An actuator assembly comprising an output member rotatable about an output axis, first and second actuators each having an axis of rotation, a drive motor and a hold motor, first and second linkages between each of the first and second actuators and the output member, wherein a torque produced by a drive motor is summed through the linkages at the output member when the respective hold motor is restrained from rotating, and wherein the respective hold motor may be selectively released so that it rotates with a failure of the respective drive motor, and wherein one of the first or second actuators may be driven to selectively rotate the output member with a failure of the drive motor of the other of the first or second actuators. The assembly may comprise a third actuator linked to the output member in the same manner as the first and second actuators.

Summing and fault tolerant rotary actuator assembly

A servovalve () comprising a motor (), a motor bias mechanism (), a first stage valve member () adapted to be moved from a first position to a first off-null position, a second stage member () adapted to be moved from a first position to a second position with movement of the first valve member (), a transfer link () acting between the first () and second () valve members, an eccentric drive member () acting between the motor () and the transfer link (), the transfer link () and drive member () configured such that selective movement of the motor () causes the transfer link () to move the first valve member (), movement of the first valve member () causes the second valve member () to move, and movement of the second valve member () causes the transfer link () to move the first valve member () from the first off-null position back to the null position.

Two-stage closed center electro-hydraulic valve

An actuator system comprising a shared link () arranged to pivot about a first axis () relative to a reference structure, a controlled element () arranged to pivot about a second axis () relative to the reference structure, a first member () arranged to pivot about a third axis () relative to the shard link and a fourth axis () relative to the controlled member, a first actuator arranged to control a first variable distance (LI) between the third axis and fourth axis, a second member () arranged to pivot about a fifth axis () relative to the shared link and a sixth axis () relative to the controlled element, a second actuator () arranged to control a second variable distance between the fifth axis and the sixth axis, the system configured such that a change in the first variable distance causes rotation of the controlled element about the second axis when the second variable distance is constant and vice versa.

An actuator synchronization system comprising a control valve in fluid communication with a plurality of actuators; each of the actuators comprising an input member moveable by the control valve, a main valve moveable from a null to an off-null position, an output member moveable from a first to a second output position, and a feedback linkage and a drive link configured such that selective movement of the input member causes movement of the valve from the null to the off-null position and movement of the output member to the second output position causes movement of the valve member from the off-null to the null position; and a mechanical connector between each of the input members or drive links of the actuators configured such that rotational motion of each of the respective drive links is synchronized.

Engine nozzle synchronization system

The improved servovalve broadly () includes: a body () having an axis of elongation (y-y), a portion of the body defining a cylinder () having an axis (x-x) substantially perpendicular to the body axis; a valve member () movably mounted in the cylinder, and adapted to be moved off-null in either direction along the cylinder axis to selectively meter the flows of fluid between a plurality of ports defined between the spool and cylinder; a rotor () mounted on the body for rotation about the body axis; a motor () acting between the body and rotor, and selectively operable to cause the rotor to rotate in a desired angular direction relative to the body; and a quill-like transfer member () acting between the rotor and valve spool.

Integrated structure electro-hydraulic valve

An actuator system having a controlled element configured for rotary movement about a first axis relative to a reference structure; a linkage system between the element and reference structure; a first actuator and a second actuator configured to power a first degree of freedom and an independent second degree of freedom of the linkage system, respectively; the linkage system having a first link configured for rotary movement about a second axis not coincident to the first axis and second link configured for rotary movement about a third axis; the linkage system configured such that a first angle of rotation may be driven independently of a second angle of rotation between said first link and said reference structure; wherein one of the first or second actuators is configured and arranged to drive rotation of the element about the first axis when the other is operatively locked.

Rotary actuator

A valve () comprising a motor () having an output shaft () orientated about a motor axis (), a hydraulic valve having a drive spool () configured to move from a first position to a second position, a mechanical linkage () between the output shaft () and the drive spool () having a sleeve () mechanically coupled to the output shaft (), a pole shaft () configured for sliding engagement in a direction generally perpendicular to the motor axis, a link () connected to the pole shaft () by a pivot joint (), a drive shaft () coupled to the link () and rotatable about a drive axis, the drive shaft () having an end portion to engage and apply a force to the spool (), and a spring () to provide a bias between the pole shaft () and the sleeve (), such that a distance between the motor axis and the pivot joint multiplied by a distance between the drive axis and the applied force is less than a distance between the drive axis and the pivot joint.

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West Seneca, NY, United States of America

John Kopp