US 12,386,362 B2
Aircraft control systems and methods using sliding mode control and feedback linearization
Aymeric Kron, Beaconsfield (CA)
Assigned to BOMBARDIER INC., Dorval (CA)
Filed by BOMBARDIER INC., Dorval (CA)
Filed on May 10, 2024, as Appl. No. 18/660,437.
Application 18/660,437 is a continuation of application No. 17/038,441, filed on Sep. 30, 2020, granted, now 12,019,456.
Claims priority of provisional application 62/907,839, filed on Sep. 30, 2019.
Prior Publication US 2024/0295881 A1, Sep. 5, 2024
Int. Cl. G05D 1/00 (2024.01); G05D 1/46 (2024.01); G05D 1/49 (2024.01); G06F 17/11 (2006.01)
CPC G05D 1/044 (2013.01) [G05D 1/085 (2013.01); G05D 1/46 (2024.01); G05D 1/49 (2024.01); G06F 17/11 (2013.01)] 22 Claims
OG exemplary drawing
 
1. A method for controlling a heading angle (ψ) of an aircraft during flight, the method comprising:
receiving a commanded heading angle (ψcmd) for the aircraft;
computing a heading angle error (ψ_err) indicative of a difference between the heading angle (ψ) of the aircraft and the commanded heading angle (ψcmd);
computing a target rate of change (ψdes) for the heading angle (ψ) of the aircraft using a sliding mode control technique, an input of the sliding mode control technique including the heading angle error (ψ_err);
computing a commanded bank angle (ϕcmd) for the aircraft using a feedback linearization (FL) control technique, an input to the FL control technique including the target rate of change (ψdes) for the heading angle (ψ) of the aircraft; and
using the commanded bank angle (ϕcmd) to control one or more actuators of the aircraft during flight.