Aircraft landing gear arrangement
An aircraft landing gear arrangement ( 1, 101 ) on an aircraft, the arrangement including a wheel ( 2, 22 ), a brake ( 6 ) operable to inhibit rotation of the wheel, one or more fan blades ( 7 a, 7 b ) rotatable to cool the brake, and a brushless DC motor ( 8 ) operable to rotate the one or more fan blades.
1 . An aircraft landing gear arrangement comprising:
a wheel;
a brake operable to inhibit rotation of said wheel;
one or more fan blades rotatable to cool the brake;
a brushless DC motor operable to rotate the one or more fan blades;
a thermoelectric device configured to convert thermal energy from the brake into electrical energy and configured to provide the electrical energy to the brushless DC motor, and
a cover mountable on the wheel, the cover defining a cover volume within which is the brushless DC motor;
wherein the thermoelectric device is within the cover volume.
2 . The aircraft landing gear arrangement according to claim 1 , further comprising a thermoelectrical device configured to convert thermal energy generated by the brake into electrical energy.
3 . The aircraft landing gear arrangement according to claim 2 , in which the brake comprises a brake stator, a brake rotor and an actuator configured to urge the brake rotor and brake stator into contact with one another, thereby engaging the brake, and in which the thermoelectric device is on the brake stator or brake rotor.
4 . The aircraft landing gear arrangement according to claim 2 , further comprising an axle on which the wheel is mounted, and the thermoelectric device is on the axle.
5 . The aircraft landing gear arrangement according to claim 1 , further comprising a kinetic energy convertor configured to convert kinetic energy from the wheel into electrical energy.
6 . The aircraft landing gear arrangement according to claim 5 , in which the one or more fan blades are lockable in a non-operating condition during a kinetic energy conversion mode in which kinetic energy is converted into electrical energy by the kinetic energy convertor.
7 . The aircraft landing gear arrangement according to claim 1 , in which the brushless DC motor comprises a stator and a rotor, the rotor is coupled to the one or more fan blades, wherein rotation of the rotor rotates the one or more fan blades.
8 . The aircraft landing gear arrangement according to claim 1 , in which the brushless DC motor comprises a stator, a rotor and a casing fixed to the rotor, wherein the one or more fan blades is coupled to the casing so that rotation of the casing rotates the one or more fan blades.
9 . The aircraft landing gear arrangement according to claim 1 , in which the cover comprises one or more wall portions and a lid portion, the one or more wall portions and the lid portion defining the cover volume.
10 . The aircraft landing gear arrangement according to claim 1 , further comprising one or more sensors configured to determine a sensed parameter, the brushless DC motor is configured to be:
operable dependent on the sensed parameter, and/or
operable dependent on a phase of flight of an aircraft, and/or
operable dependent on a predicted flight plan of an aircraft which includes the aircraft landing gear arrangement.
11 . The aircraft landing gear arrangement according to claim 1 , in which the brushless DC motor is operable in a first, enhanced cooling mode and a second, reduced cooling mode.
12 . The aircraft landing gear arrangement according to claim 11 , further comprising:
an alternative aircraft DC power source or a rectified AC power source,
wherein, during the first, enhanced cooling mode, the brushless DC motor is operable to draw electrical power from the alternative aircraft DC power source or the rectified AC power source, and
during the second, reduced cooling mode, the brushless DC motor is electrically isolated from the alternative aircraft DC power source and the rectified AC power source, and is configured to draw electrical power from the thermoelectric device configured to convert thermal energy from the brake into electrical energy.
13 . An aircraft comprising a first landing gear arrangement and a second aircraft landing gear arrangement each according to claim 1 , the first aircraft landing gear arrangement is located on a port side of the aircraft and the second aircraft landing gear arrangement being located on a starboard side of the aircraft.
14 . A method of cooling an aircraft landing gear brake, the method comprising:
operating a brushless DC motor to power one or more aircraft brake cooling blades in a:
first enhanced cooling mode in which the brushless DC motor draws electrical power from at least one of: (i) a thermoelectric device or photovoltaic material configured to convert thermal energy from the brake into electrical energy or (ii) a kinetic energy convertor, and
second reduced cooling mode in which the brushless DC motor draws power from one or both of: (i) the thermoelectric device configured to convert thermal energy from the brake into electrical energy or (ii) the kinetic energy convertor.
15 . An aircraft landing gear arrangement comprising:
a wheel;
a brake operable to inhibit rotation of said wheel;
one or more fan blades rotatable to cool the brake;
a brushless DC motor operable to rotate the one or more fan blades;
a kinetic energy convertor configured to convert kinetic energy from the wheel into electrical energy, and
a cover mountable on the wheel, the cover defining a cover volume within which is the brushless DC motor;
wherein at least a portion of the kinetic energy convertor is within the cover volume.
16 . The aircraft landing gear arrangement according to claim 15 , in which the kinetic energy convertor comprises a first portion movable relative to a second portion, movement of the first portion relative to the second portion generates electrical power, and in which one or both of the first portion and the second portion is within the cover volume.
17 . The aircraft landing gear arrangement according to claim 15 , in which the brushless DC motor is operable in a first, enhanced cooling mode and a second, reduced cooling mode.
18 . The aircraft landing gear arrangement according to claim 17 , further comprising:
an alternative aircraft DC power source or a rectified AC power source;
wherein, during the first, enhanced cooling mode, the brushless DC motor is operable to draw electrical power from the alternative aircraft DC power source or the rectified AC power source, and
during the second, reduced cooling mode, the brushless DC motor is electrically isolated from the alternative aircraft DC power source and the rectified AC power source and is configured to draw electrical power from the kinetic energy convertor.