Online optimization-based flight control system
AssigneeKitty Hawk Corporation
InventorsZouhair Mahboubi, Gabe Hoffmann, Olivier Toupet, Herve Martins-Rivas
Life of this patent
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Abstract
Techniques to control flight of an aircraft are disclosed. In various embodiments, a set of inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is determined, including by minimizing a weighted set of costs that includes costs associated with one or more errors each corresponding to a difference between a requested force or moment and a corresponding force or moment achieved by the computed solution.
Claims26
A method of controlling flight of an aircraft, comprising:
- receiving a set of inputs associated with a requested set of forces and moments to be applied to the aircraft;
- and
- computing an optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments, including by minimizing a weighted set of costs that includes costs associated with one or more errors each corresponding to a difference between a requested force or moment and a corresponding force or moment achieved by the computed solution.
An aircraft flight control system, comprising:
- an interface configured to receive a set of inputs associated with a requested set of forces and moments to be applied to the aircraft;
- and
- a processor coupled to the interface and configured to compute an optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments, including by minimizing a weighted set of costs that includes costs associated with one or more errors each corresponding to a difference between a requested force or moment and a corresponding force or moment achieved by the computed solution.
A computer program product to control flight of an aircraft, the computer program product being embodied in a non-transitory computer readable medium and comprising computer instructions for:
- receiving a set of inputs associated with a requested set of forces and moments to be applied to the aircraft;
- and
- computing an optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments, including by minimizing a weighted set of costs that includes costs associated with one or more errors each corresponding to a difference between a requested force or moment and a corresponding force or moment achieved by the computed solution.
Dependencies are inferred from the claim text.