A powered nose aircraft wheel system (130) for an aircraft (12) includes landing gear (104) that extends from the aircraft (12). A wheel axel (136) is coupled to the landing gear (104). A wheel (134) is coupled to the wheel axel (136). A wheel motor (106) is coupled to the wheel axel (136) and the wheel (134). A controller (120) is coupled to the wheel motor (106) and rotates the wheel (134). A method of taxiing an aircraft (12) includes permitting the wheel (134) of the aircraft (12) to freely spin during the landing of the aircraft (12). Power is transferred from an auxiliary power unit (73) of the aircraft (12) to the wheel motor (106). The wheel (134) is rotated via the wheel motor (106). The aircraft (12) is steered and the speed of the wheel (134) is controlled via one or more controllers selected from an onboard controller (18, 118, 120) and an offboard controller (45, 58, 59).

Powered nose aircraft wheel system

An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

Aircraft landing gear

The invention relates to a powered wheel system for an aircraft, comprising at least one undercarriage with several rotatably held wheels, with the powered wheel system comprising two or more motors of which in each case at least one motor is coupled to at least one of the wheels, and comprising at least one control device that is coupled to the motors. A control device is equipped to control operation of the motors independently of each other as far as their respective rotary speeds and direction of rotation are concerned, so that the system is able, among other things, to effect taxiing; by means of rotary speed differentials on different motors to be able to steer the aircraft; prior to landing to bring the wheel circumference speeds to landing speed; and to boost the undercarriage brakes of the aircraft. Furthermore, by means of an improvement of the system according to the invention, the rotary speeds of the wheels may be determined with precision. The invention furthermore relates to a method for driving wheels of an aircraft.

Integrated multifunctional powered wheel system for aircraft

An aircraft braking system includes a brake disk stack (22) that has at least one brake rotor (26) rotatable with an aircraft wheel (16) and at least one brake stator (24). at least one actuator (36) movable in response in a braking command to compress the brake disk stack (22) and slow the wheel (16). at least one actuator motor (32) operably connected to the at least one actuator (36) for moving the at least one actuator (36), a generator (40,82,100) having a generator rotor (42) and a generator stator (44), the generator (40,82,100) being operably connectable to the aircraft wheel (16) such that said generator rotor (42) rotates when the wheel (16) rotates, and a controller (50) electrically connected to the generator (40,82,100) and the at least one actuator motor (32). Also a method of generating electrical power from an aircraft wheel (16), to power the actuator (36) of the wheel brake is provided.

Aircraft electric brake and generator therefor

A kinetic energy system which transfers the kinetic landing into recoverable electric energy for an aircraft. The system incorporates at least one wheel supporting the aircraft for landing and takeoff coupled with a dynamic functioning motor/generator mounted to and operated by rotation of the wheel to create electrical energy from kinetic energy. An induction shoe structurally connected to the aircraft and electrically connected to the motor/generator, which shoe draws the converted energy from the generator which supplies the load created by the inductively coupled induction shoe to the an ancillary load provided by the resistive heat sink on by the capacitor storage bank. This provides the generator circuit for conversion of the rotational energy of the wheel to electrical energy and creates braking drag. In exemplary embodiments, the system employs an energy storage system acting as the load to store electrical potential energy created by the generator. Additionally, the generator is employable as a motor, receiving energy from the storage system for traction power to the associated aircraft wheel. An induction grid or a surface mounted conductive layer mounted into or onto a runway is employed for transferring energy to and from the motor/generator.

Aircraft kinetic landing energy conversion system

Aircraft landing gear comprised of a wheel hub motor/generator disks stack, includes alternating rotor and stator disks mounted with respect to the wheel support and wheel. The invention can provide motive force to the wheel when electrical power is applied, e.g. prior to touch-down, thus decreasing the difference in relative velocities of the tire radial velocity with that of the relative velocity of the runway and reducing the sliding friction wear of the tire. After touchdown the wheel hub motor/generator may be used as a generator thus applying a regenerative braking force and/or a motorized braking action to the wheel. The energy generated upon landing maybe dissipated through a resistor and/or stored for later use in providing a source for motive power to the aircraft wheels for taxiing and ground maneuvers of the aircraft. Methods and apparatuses for nose gear steering and ABS braking using the disclosed invention are described.

Landing gear method and apparatus for braking and maneuvering

Method and apparatus for braking and maneuvering

FIELD: transport. ^ SUBSTANCE: invention relates to aircraft alightning gear unit. In the first and the second version the unit contains front chassis support and main chassis support. The front chassis support or the main chassis support contains nonrotating main segment, wheel, stator, rotor, processor, electric device. The stator and the rotor are made capable to generate axial magnetic flux. The processor is connected with the stator and the rotor and is executed with possibility to connect stator-rotor sets to electric device and to disconnect them from electric device. The electric device contains electric energy storage device and/or electric energy dissipation device. In the second version, the unit includes rotor with disk. Rotor disk is made capable to move in parallel to the axis of rotation. Constant magnet of rotor disk applies clamping force to corresponding stator disk to provide parking brake function. In the third version, stator and rotor are executed in such a way that interaction of their axial magnet fluxes causes conversion of total wheel rotation energy into electric energy and then into thermal energy via eddy currents generation in the stator and/or the rotor. Electric motor/generator contains rotor and stator. Rotor element is connected with alighting gear wheel to rotate together with the wheel. Stator element is connected with axis or tube shaft to rest without rotation. The method consists in applying electric current to stator, generating axial magnetic flux and implementing aircraft wheel motorised braking. ^ EFFECT: increase in aircraft stability. ^ 62 cl, 3 dwg

Method and device for braking and manoeuvring

Aircraft landing gear comprised of a wheel hub motor/generator disks stack, includes alternating rotor and stator disks mounted with respect to the wheel support and wheel. The wheel hub motor/generator can provide motive force to the wheel when electrical power is applied, which may be applied prior to touch-down thus decreasing the difference in relative velocities of the tire radial velocity with that of the relative velocity of the runway thus greatly reducing the sliding friction wear of said tire. After touchdown the wheel hub motor/generator may be used as a generator thus applying a regenerative braking force and/or a motorized braking action to the wheel. The energy generated upon landing maybe dissipated through a resistor and/or stored for later use in providing a source for motive power to the aircraft wheels for the purpose of taxiing and ground maneuvers of said aircraft.

Steven Sullivan

Papers

Landing gear method and apparatus for braking and maneuvering

Method and apparatus for braking and maneuvering

Method and device for braking and manoeuvring

Landing gear assembly for aircraft