Rolls-royce Corporation

Goodrich Actuation Systems Limited

Dowty Boulton Paul Limited

Antony Morgan

Andrew Swift

Andrew Robert Hawksworth

James Holding

John Herbert Harvey

Michael Paul Somerfield

Jonathan E Holt

Paul Simms

Brian Farley

Arthur Derek Mountney

Timothy Robert Matthews

Robert E Wilson

A method for driving a tilt rotor between vertical and horizontal using a variable displacement motor controlled in response to a swash angle of the motor measured in a feedback loop. The loop includes an algorithm configured to monitor change in swash angle as the motor speed reduces and the actual tilt position of the rotor pylon approaches the second position and, based on the change and actual tilt position, to limit change in swash angle to be within a predetermined range as a percentage of the operating load.

Tilt rotor control

A thrust reverser is described that comprises a new type of locking means for locking an actuator in position so that maintenance can be performed on the machine. The locking means comprises a removable locking device for preventing movement of an actuator. The locking means may also function in one configuration as an end cap. An actuator is also described comprising a removable torque limiting device for limiting torque of the actuator.

Locking system and torque limiter for an electrically actuated thrust reverser

A system for driving a tilt rotor between vertical and horizontal using a variable displacement motor controlled in response to a swash angle of the motor measured in a feedback loop.

An apparatus for a thrust reverser actuation system ('TRAS'), the apparatus comprising: an input shaft; a first component located concentrically around the input shaft; a second component located concentrically around the first component; a first ballscrew mechanism between the input shaft and the first component, and configured such that rotational movement of the input shaft causes a translational movement of the first component via the first ballscrew mechanism; and a second ballscrew mechanism between the first component and the second component, and configured such that rotational movement of the first component causes a translational movement of the second component via the second ballscrew mechanism.

Telescopic ballscrew actuator

A thrust reverser actuation system includes a first cowl actuation system for translating a first cowl of a thrust reverser and a second, separate cowl actuation system for translating a second cowl of the thrust reverser. The system also includes a device operatively connected between the first cowl actuation system and the second cowl actuation system, and configured to transmit drive from one of the first and second cowl actuation systems to the other of the first and second cowl actuation systems in the event of a failure of the other of the first and second cowl actuation systems.

Thrust reverser actuation system

An actuator system for controlling a movable surface has a main shaft connected between a power drive unit and the movable surface to transmit a command from the power drive unit to move the movable surface. If a failure in the main shaft is detected a failure control device connects a secondary shaft from the movable surface to the power drive unit e.g. by releasing a solenoid which releases gears so as to permit differential rotations between an outer ring and a sun gear of a planetary gear system, within prescribed limits. When these limits are exceeded, the solenoid brake is de-energised braking the planetary gear outer ring and tying the gears through an epicycle ratio corresponding to the ratio of gears connecting the main and secondary shafts. The gear system acts as a low mass asymmetry brake that allows post-failure operation of the surface control.

Actuator system

An apparatus for a thrust reverser actuation system ('TRAS'), the apparatus comprising: an input shaft; a first component located concentrically around the input shaft; a second component located concentrically around the first component; a first balls crew mechanism between the input shaft and the first component, and configured such that rotational movement of the input shaft causes a translational movement of the first component via the first ballscrew mechanism; and a second ballscrew mechanism between the first component and the second component, and configured such that rotational movement of the first component causes a translational movement of the second component via the second ballscrew mechanism.

A nacelle for a gas turbine engine, comprising a thrust reverser movable between a stowed position and a deployed position, and a locking system configured to selectively prevent movement of the thrust reverser from the stowed position, the locking system comprising a locking mechanism and an actuator configured to actuate the locking mechanism, wherein the locking mechanism is positioned aft of a blade-off zone defined across the nacelle and the actuator is positioned fore of, or at least partially within, the blade-off zone.

Thrust reverser tertiary locking system

There is provided an actuator for an aircraft thrust reverser, comprising a first member, a second member movable relative to the first member, a third member movable relative to the first member and the second member, and a lock system configured to selectively lock the second member to the third member in a first stage of actuation, and the first member to the second member in a second, separate stage of actuation.

Actuator for use in aircraft

An actuator comprises a ball nut and a lock housing arranged radially outwardly of the ball nut and overlapping a proximal end of the ball nut when the ball nut is in a stowed position. The lock housing comprises a sleeve in which is located an aperture, and a locking element is retained within the aperture and can move in a radial direction through the aperture. When the ball nut is in the stowed position, the locking element engages with a locking projection on the ball nut, to retain the ball nut in the stowed position.

Actuator

An actuator comprises a rotatable nut arranged to be driven for rotation by a motor, an axially translatable shaft cooperable with the nut and arranged such that rotation of the nut drives the shaft for axial movement, and a steering rack coupled to the shaft by a coupling arrangement so as to be driven for axial movement by the shaft, wherein the coupling accommodates limited relative lateral movement between the shaft and the steering rack.

A pitch change apparatus is provided for a propeller assembly having a row of propeller blades which rotate around an axis of the assembly. The apparatus has a unison ring which is coaxial with the propeller assembly. The unison ring is movable to drive respective mechanisms for varying the pitch of the blades. The apparatus further has a plurality of pitch lock assemblies circumferentially distributed around the unison ring. Each pitch lock assembly has a free state which allows movement of the unison ring and a locked state which prevents or limits movement of the unison ring and thus prevents or limits variation of the pitch of the blades. The pitch lock assembly moves from the free to the locked state when the assembly receives a signal to lock the blades.

Propeller assembly pitch change apparatus

An engine arrangement has a gear assembly that drives a first propeller assembly. The gear assembly is driven by a power drive shaft that joins to the gear assembly at a first side. The engine arrangement has a static conduit that extends along a longitudinal internal cavity of the power drive shaft. The conduit penetrates the gear assembly such that a portion of the conduit projects from an opposing second side of the gear assembly. The engine arrangement has one or more first fluid supply lines routed along the static conduit between a hydraulic pressure power source and the first hydraulic actuator. A first hydraulic rotating coupling is mounted to the projecting portion of the static conduit. The first fluid supply lines fluidly communicate with the first hydraulic actuator via the first rotating coupling.

Engine arrangement

A back-up featherer is provided for an engine arrangement having a main hydraulic actuator which operates a pitch change mechanism to angularly displace propellers of a propeller assembly of the engine arrangement, the pitch change mechanism and main hydraulic actuator rotating with the propeller assembly. The back-up featherer has one or more back-up hydraulic actuators located on a static structure of the engine arrangement. The back-up featherer further has one or more load application members which are located on the static structure of the engine arrangement and which are movable by the back-up hydraulic actuators. When moved by the back-up hydraulic actuators, the load application members bear against an engagement portion of the pitch change mechanism across a rotating interface formed therebetween to apply a load to the pitch change mechanism which results in angular displacement of the propellers.

Growing community of inventors

Wolverhampton, United Kingdom

Antony Morgan