Rolls-royce Corporation

Peter Malkin

Brian E Simmers

Philip M Sargent

David Reginald Trainer

Stephen Mark Husband

Alexander Charles Smith

Paul Robert Miller

Geraint Wyn Jewell

Alexander C Smith

Philip Michael Sargent

Brian Edward Simmers

A termination unit for a superconductor network. Including a primary system that includes a first superconductor cable. Also a first superconducting coil and a first auxiliary magnetizing coil, each coil wound around the first superconductor cable. Also a terminal including a first leg, the first leg including an aperture configured to receive the first superconductor cable. The first leg defining a clearance about the first superconductor cable at ambient temperature and arranged to firmly clamp onto the first superconductor cable at a cryogenic temperature. The termination unit including a cooling system arranged to enclose and cool the primary system to cryogenic temperatures.

Termination unit

An aircraft electrical actuator arrangement includes a plurality of actuators and a master power converter to convert power from the electrical power distribution network for supply to each actuator. The actuators include an environmental control system actuator, an aileron actuator, a flap actuator, a slat actuator, a landing gear actuator, a thrust reverser actuator, a brake actuator and a taxiing actuator. A controller is coupled to the master power converter and is arranged to allow the supply of power from the master power converter to the environmental control system actuator during a first mode of operation of the aircraft. The controller is arranged to allow the supply of electrical power from the master power converter to at least one of the aileron, the flap, the slat, the landing gear, the thrust reverser, the brake actuator or the taxiing actuator during a second mode of operation of the aircraft.

Aircraft electrical actuator arrangement

Apparatus indicated generally atis incorporated within an aircraft. The apparatusincludes an electric motor, a first drive trainand a second drive train. The first drive trainprovides drive from the electric motorfor one or more of the wheels, allowing the electric motorto propel the aircraft when taxiing. The second drive trainprovides drive from the electric motorfor an aircraft system which is operational at least when the aircraft is in flight. In this example, the electric motoris illustrated using the second drive trainfor driving a compressorof the ECS, the compressorbeing responsible for cabin pressurization during flight. A clutchallows the drive trainto be connected or disconnected from the electric motor, thereby connecting or disconnecting the drive from the electric motorto the wheels. The clutchis controlled to disconnect the first drive trainwhen the aircraft is in flight. Thus, when the aircraft is in flight, the full output of the motoris available for driving the compressor; when the aircraft is on the ground, the compressoris not required or is less demanding, and surplus output of the motorcan be used for driving the wheels

Apparatus for taxiing an aircraft

A fault current limiter comprising: an input node; an output node; a variable impedance element coupled between the input node and the output node; a closed loop cryocooler circuit, comprising a first cryocooler for cooling the variable impedance element and a second cryocooler, thermally coupled to the first cryocooler, for cooling the first coolant, wherein the variable impedance element comprises Magnesium Diboride.

Fault current limiter

A fault current limiter comprising: an input node; an output node; a variable impedance element coupled between the input node and the output node; a multi-cycle refrigeration system, comprising a first coolant cycle for cooling the variable impedance element and a second coolant cycle, thermally coupled to the first coolant cycle, for cooling the first coolant, wherein the variable impedance element comprises Magnesium Diboride.

Growing community of inventors

Hexham, United Kingdom

Peter Malkin