Method of managing a steering command for a steerable portion of aircraft landing gear
AssigneeMessier-Bugatti-Dowty
InventorsMichael Benmoussa, David Poiret, Jerome Fraval
Life of this patent
Estimating the term…
Abstract
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.
Claims3
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).
Dependencies are inferred from the claim text.