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US 12,386,362 B2Granted
Aircraft control systems and methods using sliding mode control and feedback linearization
AssigneeBombardier Inc.
InventorAymeric Kron
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Abstract
Methods and systems for controlling a bank angle, a heading angle and an altitude of an aircraft during flight are provided. The methods and systems disclosed herein make use of sliding mode control and feedback linearization control (nonlinear dynamic control) techniques. The methods and systems can provide autopilot-type functions that can autonomously execute aggressive maneuvers as well as more gentle maneuvers for aircraft.
Claims22
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 ({dot over (ψ)}des) 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 ({dot over (ψ)}des) 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.
3 more elements
A system for controlling a heading angle (ψ) of an aircraft during flight, the system comprising:
- one or more computers operatively coupled to receive one or more signals indicative of a commanded heading angle (ψcmd) for the aircraft, the one or more computers being configured to:
- compute a heading angle error (ψ_err) indicative of a difference between the heading angle (ψ) of the aircraft and the commanded heading angle (ψcmd);
- compute a target rate of change ({dot over (ψ)}des) 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);
- compute 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 ({dot over (ψ)}des) for the heading angle (ψ) of the aircraft;
- and
- use the commanded bank angle (ϕcmd) to control one or more actuators of the aircraft during flight.
3 more elements
Dependencies are inferred from the claim text.