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US 12,754,554 B2Granted
Aircraft control systems and methods using sliding mode control and feedback linearization
AssigneeBombardier Inc.
InventorAymeric Kron
Life of this patent
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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.
Claims24
A method for controlling an altitude (h) of an aircraft during flight, the method comprising:
- receiving a commanded altitude (hcmd) for the aircraft;
- computing an altitude error (herr) indicative of a difference between the altitude (h) of the aircraft and the commanded altitude (hcmd);
- computing a target rate of change ({dot over (h)}des) for the altitude (h) of the aircraft using a sliding mode control technique, an input to the sliding mode control technique including the altitude error (herr);
- computing a value indicative of a target change in thrust force 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 (h)}des) of the altitude (h) of the aircraft;
- and
- using the value to control one or more actuators of the aircraft during flight.
3 more elements
A system for controlling an altitude (h) of an aircraft during flight, the system comprising:
- one or more computers operatively coupled to receive one or more signals indicative of a commanded altitude (hcmd) for the aircraft, the one or more computers being configured to:
- compute an altitude error (herr) indicative of a difference between the altitude (h) of the aircraft and the commanded altitude (hcmd);
- compute a target rate of change ({dot over (h)}des) for the altitude (h) of the aircraft using a sliding mode control technique, an input to the sliding mode control technique including the altitude error (herr);
- compute a value indicative of a target change in thrust force for the aircraft using a feedback linearization control technique, an input to the FL control technique including the target rate of change ({dot over (h)}des) of the altitude (h) of the aircraft;
- and
- using the value to control one or more actuators of the aircraft during flight.
3 more elements
Dependencies are inferred from the claim text.