Aircraft landing gear

Abstract

An aircraft landing gear is disclosed having a wheel rotatably mounted on an axle, a first gearing element that rotates with the wheel, a second gearing element configured to mesh with the first gearing element such that rotation of the first gearing element causes rotation of the second gearing element, wherein the second gearing element is connected to a generator, such that rotation of the second gearing element causes the generator to generate electrical energy, further comprising a heat dissipation device connected to the generator wherein the heat dissipation device comprises an electrical heating element connectable to the generator to receive generated electrical energy and convert it to heat energy, and a fluid receptacle adjacent the heating element, such that fluid in the receptacle can be heated.

1 . An aircraft landing gear comprising:
 an axle and a wheel rotatably mounted on the axle,   a cavitation braking device for slowing rotation of the wheel about the axle, wherein the braking device comprises:
 a first part connected to the axle, the first part having a first cavitation surface, 
 a second part connected to the wheel, the second part having a second cavitation surface, and 
 a liquid channel between the first and second cavitation surfaces, 
   
       wherein both of the first and second cavitation surfaces are provided with a number of indent portions such that, when the wheel is rotating on the axle and the second part is rotating with respect to the second part and when liquid is supplied to the liquid channel, the liquid is caused to cavitate when at least one indent portion on the first cavitation surface lines up with an indent portion on the second cavitation surface. 
     
     
         2 . An aircraft landing gear as claimed in  claim 1 , wherein at least one of the indent portions is in the form of a blind hole in the cavitation surface. 
     
     
         3 . An aircraft landing gear as claimed in  claim 1 , wherein the braking device further comprises a liquid supply line for supplying liquid to the liquid channel. 
     
     
         4 . An aircraft landing gear as claimed in  claim 3 , wherein the liquid supply line comprising a pump for urging liquid into the liquid channel. 
     
     
         5 . An aircraft landing gear as claimed in  claim 1 , wherein the aircraft landing gear further comprises:
 a first gearing element connected to the wheel, such that it rotates with the wheel,   a second gearing element, wherein the second gearing element is configured to mesh with the first gearing element such that rotation of the second gearing element causes rotation of the first gearing element,   
       wherein the second gearing element is connected a motor, such that rotation of the second gearing element by the motor drives rotation of the first gearing element and the wheel. 
     
     
         6 . An aircraft landing gear as claimed in  claim 5 , wherein the motor is configured to act as a generator to generate electrical energy upon rotation of the second gearing element by the first gearing element. 
     
     
         7 . An aircraft landing gear as claimed in  claim 1 , wherein the first and second cavitation surfaces are substantially parallel to each other and at an angle to the wheel axle, such that the liquid channel forms a cone shape. 
     
     
         8 . An aircraft landing gear as claimed in  claim 1 , wherein bearings are provided between the first part or axle and the second part. 
     
     
         9 . An aircraft landing gear as claimed in  claim 1 , wherein the second part is mounted externally to the first part with respect to the axle. 
     
     
         10 . An aircraft landing gear as claimed in  claim 9 , wherein the first cavitation surface is externally facing with respect to the axle and the second cavitation surface is internally facing with respect to the axle. 
     
     
         11 . An aircraft landing gear as claimed in  claim 1 , wherein the aircraft landing gear further comprises an additional braking device for slowing rotation of the wheel about the axle at lower rotational speeds than the cavitation braking device. 
     
     
         12 . An aircraft comprising the aircraft landing gear of  claim 1 . 
     
     
         13 . A method of braking an aircraft wherein the aircraft is the aircraft of  claim 12 . 
     
     
         14 . A method of braking an aircraft, comprising the steps of:
 providing the aircraft landing gear of  claim 1 ,   rotating the wheel about the axle such that the second part rotates with respect to the first part, thereby causing the indent portions in the first and second cavitation surfaces to momentarily line up with each other, and   supplying liquid to the liquid channel, such that the liquid cavitates when the indent portions momentarily line up.