Goodrich Actuation Systems Limited

Rohr, Inc.

Peter Bacon

Tony Jones

John Herbert Harvey

Maamar Benarous

Mark Hubberstey

Stephen Michael Roberts

Brett John Wharton

Neil Charles Davies

Steven Andrew Wylie

Norman John James

Joel H Frank

Paul Smith

David A Baer

Shunshen Richard Wang

David Roy Tucker

David Coleman

Bryant Lynoel McKleny

Adam John McLoughlin

Neil Davies

Lynoel Mckleny Bryant

Brett Wharton

Joel Hudson Frank

Shunsen Richard Wang

A system architecture for a backup thrust reverser actuation system control is provided. The system architecture includes an AC power supply of an aircraft, a power supply and a motor control adapted to control an electric motor (M) of a thrust reverser actuation system. The system architecture further includes a backup power supply adapted to provide power to the electric motor in the event that the power supply fails.

Back-up thrust reverser actuation system control

A system architecture for operation of aircraft flaps. The system architecture includes a first pair of motor drive units, the first pair comprising a first motor drive unit (MD) and a second motor drive unit (MD), and a second pair of motor drive units, the second pair comprising a third motor drive unit (MD) and a fourth motor drive unit (MD). The system further includes a first plurality of switches connected between the first motor drive unit (MD) and the second motor drive unit (MD), the first plurality of switches configured to operate a first electric motor and a second electric motor, and a second plurality of switches connected between the third motor drive unit (MD) and the fourth motor drive unit (MD), the second plurality of switches configured to operate a third electric motor and a fourth electric motor.

System architecture for operation of aircraft flaps

A solenoid comprises first and second coils connected to an electrical power supply circuit. In a first mode of operation the power supply circuit is arranged to provide a current flowing in opposite directions through the respective first and second coils, e.g. to produce a self-heating effect. In a second mode of operation the power supply circuit is arranged to provide a current flowing in the same direction through the respective first and second coils, e.g. to generate a magnetic force. In some embodiments, the power supply circuit includes a bridge rectifier or full wave rectifier connected to a bi-directional current driver.

Heating of solenoids

A hydraulic power drive unit (PDU) for a transmission system includes a hydraulic motor for converting hydraulic pressure into torque and rotation; a hydraulic brake system for applying a braking force to the hydraulic motor to prevent rotation of the hydraulic motor, wherein the hydraulic brake system is biased to apply the braking force to the hydraulic motor to prevent rotation of the hydraulic motor, and configured to remove the braking force in response to a supply of hydraulic fluid; and a hydraulic circuit for supplying a flow of hydraulic fluid to the hydraulic motor to pressurise and thereby operate the hydraulic motor and for supplying hydraulic fluid to the hydraulic brake system to pressurise the hydraulic brake system and thereby remove the braking force; wherein the hydraulic circuit comprises a brake supply line for supplying the hydraulic fluid to the hydraulic brake system.

Hydraulic power drive unit

A system for monitoring asymmetry between two components includes a comparator having a first input to receive a signal indicative of a position of a first component and a second input to receive a signal indicative of a position of a second component. The system also includes means for performing an integration of a plurality of output signals from the comparator indicative of the difference exceeding the threshold and means for outputting a command signal to actuate a brake in response to the integrating means determining that the number of times the difference exceeds the threshold is in excess of a given value.

Monitoring component asymmetry

The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag.

Variable area fan nozzle with bypass flow

An actuator arrangement comprises an actuator having a rotatable drive input, a motor, and a drive transmission arrangement for transmitting rotary drive from the motor to the rotatable drive input of the actuator, wherein the transmission arrangement includes a telescopic drive coupling.

Thrust reverser and VAFN arrangement

A distributed control system is provided where the controllers are split into two dissimilar groups and flight control responsibility is further allocated within each group such that one entire group plus one further controller can fail without compromising the pilot's ability to fly the aircraft.

Aircraft flight surface control system

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Wolverhampton, United Kingdom

Peter Bacon