Method of managing a steering command for a steerable portion of aircraft landing gear
View Patent ↗A method of managing a steering command for a steerable portion 3 of nose landing gear 2 of an aircraft 1 . The method implements servo-control to servo-control of a steering actuator 6 to an angle position setpoint θset for the steerable portion 3 . The servo-control includes calculating an error ε by subtracting a reference angle θest from the angle position setpoint θset. The reference angle θest is an angle determined by calculation as a function of a longitudinal speed Vlong and a yaw rate τ of the aircraft 1.
1. A method of managing a steering command for a steerable portion ( 3 ) of nose landing gear ( 2 ) of an aircraft ( 1 ), using a servo-control, comprising:
implementing servo-control of a steering actuator ( 6 ) to an angle position setpoint (θset) for the steerable portion ( 3 ),
calculating an error (ε) by subtracting a reference angle (θest) from the angle position setpoint (θset), and
determining the reference angle (θest) by calculation as a function of a longitudinal speed (Vlong) and a yaw rate (τ) of the aircraft ( 1 ), wherein the reference angle is determined using the formula:
θ
est
=
(
L
·
τ
V
long
)
where Vlong is the longitudinal speed of the aircraft, τ is the yaw rate of the aircraft, and L is the distance between the main landing gear of the aircraft and the nose landing gear ( 2 ).
2. A method of managing a steering command according to claim 1 , wherein the servo-control is performed by a servo-control loop including a proportional integral derivative (PID) controller ( 18 ) for generating a steering command (Icomm) for the actuator ( 6 ) as a function of the error (ε).
3. A method of managing a steering command according to claim 1 , wherein the servo-control is implemented in a controller ( 13 ) arranged in the aircraft ( 1 ), the controller ( 13 ) delivering a command current (Icomm) to a command member ( 12 ) for delivering calibrated power to the steering actuator ( 6 ).