# US 2014/0156113 A1 · Method of managing a steering command for a steerable portion of aircraft landing gear

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- Number: US 2014/0156113 A1
- Document ID: US20140156113A1
- Status: Published application
- Kind: A1
- Application number: 13/779,397
- Filed: 2013-02-27
- Published: 2014-06-05
- Earliest claimed: 2012-02-06
- Assignees: Messier-Bugatti-Dowty
- Applicants: Messier-Bugatti-Dowty
- Inventors: Michael BENMOUSSA; David POIRET; Jerome FRAVAL
- Web page: https://patentgrep.com/patent/US20140156113A1

## CPC

- B64C 19/00: Aircraft control not otherwise provided for
- B64C 25/50: Steerable undercarriages; Shimmy-damping
- G05D 1/0083: {to help an aircraft pilot in the rolling phase}
- B64C: AEROPLANES; HELICOPTERS
- G05D: SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES

## Abstract

The invention relates to a method of managing a steering command for a steerable portion 3 of nose landing gear 2 of an aircraft 1, the method implementing servo-control to servo-control a steering actuator 6 to an angle position setpoint θset for the steerable portion 3, the servo-control including calculating an error ε by subtracting a reference angle θest from the angle position setpoint θset. According to the invention, 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.

## Claims

### Claim 1

A method of managing a steering command for a steerable portion (3) of nose landing gear (2) of an aircraft (1), the method implementing servo-control to servo-control a steering actuator (6) to an angle position setpoint (θset) for the steerable portion (3), the servo-control including calculating an error (ε) by subtracting a reference angle (θest) from the angle position setpoint (θset), the method being characterized in that 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).

### Claim 2 (depends on 1)

A method of managing a steering command according to claim 1, wherein the reference angle is determined using the formula:
θ


est
=
arctan

(
L
·
τ
Vlong
)
where Vlong is the longitudinal speed of the aircraft, τ is the yaw rate of the aircraft, and L is the distance between main landing gear of the aircraft and the nose landing gear (2).

### Claim 3 (depends on 1)

A method of managing a steering command according to claim 1, wherein the servo-control is performed by a servo-control loop including a PID controller (18) for generating a steering command (Icomm) for the actuator (6) as a function of the error (ε).

### Claim 4 (depends on 1)

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).