Control system for controlling a landing gear drive system

Abstract

A control system for controlling a landing gear drive system for driving rotation of an aircraft wheel is disclosed having a control panel with a controller having a forward motion setting and a zero speed setting, a control unit for receiving a control input from the controller, and for providing a torque command to be applied to the wheel, and a speed sensor for sensing an aircraft taxi speed and for providing an indication of the aircraft taxi speed to the control unit. When the controller is moved from the forward motion setting to the zero speed setting, the control unit provides a torque command to the drive system to provide zero forwards driving torque to the wheel, and a braking command to apply a braking torque to the wheel.

1 . A control system for controlling a landing gear drive system on an aircraft, the drive system being capable of driving rotation of a wheel of the aircraft, the control system comprising:
 a control panel, provided with a controller, the controller having at least two settings:
 i) a forward motion setting, and 
 ii) a zero speed setting, 
   a control unit for receiving a control input from the controller, and for providing a torque command to be applied to the wheel, and   a speed sensor for sensing an aircraft taxi speed and for providing an indication of the aircraft taxi speed to the control unit,   
       wherein the control unit is arranged such that, when the controller is moved from the forward motion setting to the zero speed setting:
 a) the control unit provides a torque command to the drive system to provide zero forwards driving torque to the wheel, and 
 b) the control unit provides a braking command to apply a braking torque to the wheel to slow rotation of the wheel while the aircraft taxi speed is above zero. 
 
     
     
         2 . A control system as claimed in  claim 1 , wherein the drive system comprises a pinion gear driveable by a motor, the pinion gear being arrangeable to drive rotation of the wheel, and wherein the torque command to provide zero forwards driving torque to the wheel includes a command to reduce the driving torque provided by the motor to the pinion gear to zero. 
     
     
         3 . A control system as claimed in  claim 2 , wherein the command to reduce the driving torque provided by the motor to the pinion gear to zero is given when the indication of the aircraft taxi speed is below a predetermined lowness threshold. 
     
     
         4 . A control system as claimed in  claim 1 , wherein the braking command to apply a braking torque to the wheel to slow rotation of the wheel includes a command to a braking system of the aircraft to apply a braking torque to the wheel. 
     
     
         5 . A control system as claimed in  claim 4 , wherein the command to the braking system of the aircraft is given when the indication of the aircraft taxi speed is low. 
     
     
         6 . A control system as claimed in  claim 1 , wherein the braking command to apply a braking torque to the wheel to slow rotation of the wheel includes a command to the drive system of the aircraft to apply a braking torque to the wheel, wherein the drive system is commanded to provide a regenerative braking torque. 
     
     
         7 . A control system as claimed in  claim 6 , wherein the command to the drive system of the aircraft is given when the indication of the aircraft taxi speed is low. 
     
     
         8 . A control system for controlling a landing gear drive system on an aircraft, the drive system being capable of driving rotation of a wheel of the aircraft, the control system comprising:
 a control panel, provided with a controller, the controller having at least two forward motion settings:
 i) a low forward speed setting, and 
 ii) a high forward speed setting, 
   a control unit for receiving a control input from the controller, and for providing a torque command to be applied to the wheel, and   a speed sensor for sensing an aircraft taxi speed and for providing an indication of the aircraft taxi speed to the control unit,   
       wherein the control unit is arranged such that, when the controller is in the low forward speed setting, the control unit provides a torque command to the drive system, based on the indication of the aircraft taxi speed, to maintain the aircraft taxi speed at or near a desired speed. 
     
     
         9 . A control system as claimed in  claim 8 , wherein the desired speed is within the range between 1 and 3 knots, preferably 1.5 to 2.5 knots and more preferably 1.75 to 2.25 knots. 
     
     
         10 . A control system for controlling a landing gear drive system on an aircraft, the drive system being capable of driving rotation of a wheel of the aircraft, the control system comprising:
 a control panel, provided with a controller, the controller having at least two power settings:
 i) a normal power setting, and 
 ii) a boost power setting, and 
   a control unit for receiving a control input from the controller, and for providing a torque command to be applied to the wheel,   
       wherein the control unit is arranged such that, when the controller is in the normal power setting, the control unit provides a torque command to the drive system to provide a driving torque to the wheel up to a first power level, 
       and wherein the control unit is arranged such that, when the controller is in the boost power setting, the control unit provides a torque command to the drive system to provide a driving torque to the wheel at a second power level, higher than the first power level, and wherein the controller is biased away from the boost power setting and towards the normal power setting. 
     
     
         11 . A control system as claimed in  claim 10 , wherein the control unit is arranged to reduce the torque command to the first power level, if the controller is in the boost power setting and if an indication of the additional power provided to the drive system in the boost power setting has reached a set limit. 
     
     
         12 . A control system for controlling a landing gear drive system on an aircraft, the drive system being capable of driving rotation of a wheel of the aircraft, the control system comprising:
 a control panel, provided with a controller, the controller having a backwards motion setting,   a control unit for receiving a control input from the controller, and for providing a torque command to be applied to the wheel, and   a speed sensor for sensing an aircraft taxi speed and for providing an indication of the aircraft taxi speed to the control unit,   
       wherein the control unit is arranged such that, when the controller is in the backwards motion setting, the control unit provides a backwards driving torque command to the drive system, based on the indication of the aircraft taxi speed, to maintain the backwards aircraft taxi speed at or near a desired speed. 
     
     
         13 . A control system as claimed in  claim 12 , wherein the desired speed is within the range between 1 and 3 knots, preferably 1.5 to 2.5 knots and more preferably 1.75 to 2.25 knots. 
     
     
         14 . A control system for controlling a landing gear drive system on an aircraft, the drive system being capable of driving rotation of a wheel of the aircraft, the control system comprising:
 a control panel, provided with a controller, the controller having at least two settings:
 i) a backwards motion setting, and 
 ii) a zero speed setting, 
   a control unit for receiving a control input from the controller, and for providing a torque command to be applied to the wheel, and   a speed sensor for sensing an aircraft taxi speed and for providing an indication of the aircraft taxi speed to the control unit,   
       wherein the control unit is arranged such that, when the controller is moved from the backwards motion setting to the zero speed setting:
 a) the control unit provides a torque command to the drive system to provide zero backwards driving torque to the wheel, and 
 b) the control unit provides a braking command to apply a braking torque to the wheel to slow rotation of the wheel while the aircraft taxi speed is above zero. 
 
     
     
         15 . A control system as claimed in  claim 14 , wherein the drive system comprises a pinion gear driveable by a motor, the pinion gear being arrangeable to drive rotation of the wheel, and wherein the torque command to provide zero backwards driving torque to the wheel includes a command to reduce the backwards driving torque provided by the motor to the pinion gear to zero. 
     
     
         16 . A control system as claimed in  claim 14 , wherein the braking command to apply a braking torque to the wheel to slow rotation of the wheel includes a command to a braking system of the aircraft to apply a braking torque to the wheel. 
     
     
         17 . A control system as claimed in  claim 14 , wherein the braking command to apply a braking torque to the wheel to slow rotation of the wheel includes a command to the drive system of the aircraft to apply a braking torque to the wheel, wherein the drive system is commanded to provide a regenerative braking torque. 
     
     
         18 . An aircraft comprising an aircraft landing gear, having at least one wheel provided with a drive system for driving rotation of the wheel, the drive system comprising a motor, wherein the aircraft also comprises the control system of  claim 1 , the control system or control panel being arranged to control the drive system. 
     
     
         19 . A method of controlling an aircraft landing gear drive system capable of driving rotation of a wheel of an aircraft, the method comprising the step of using a control system of  claim 1 . 
     
     
         20 . A control panel of an aircraft, the control panel provided with a controller in the form of a rotary dial and having a forward motion setting for controlling forwards driving rotation of a wheel of the aircraft, wherein the forward motion setting is located at least partially between 9 o'clock and 12 o'clock on the rotary dial.