Online optimization-based flight control system

Patent metadata

Field	Value
Publication number	US-10370099-B2
Application number	US-201615297029-A
Country	US
Kind code	B2
Filing date	Oct 18, 2016
Priority date	Oct 18, 2016
Publication date	Aug 6, 2019
Grant date	Aug 6, 2019

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.

First claim

What is claimed is:

1. 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.

2. The method of claim 1 , wherein the set of inputs is associated with a set of inceptor output values.

3. The method of claim 1 , wherein the set of inputs is provided by an autopilot or other automated flight computer.

4. The method of claim 1 , wherein the inputs include values other than forces and moments and said values other than forces and moments are mapped to determine the requested forces and moments.

5. The method of claim 1 , wherein said optimal mix is computed onboard the aircraft in real time.

6. The method of claim 1 , wherein computing the optimal mix of actuators and associated actuator parameters includes enforcing one or more constraints with respect to one or both of said actuators and said actuator parameters.

7. The method of claim 6 , wherein said one or more constraints includes one or more of minimum and/or maximum rotation speed or torque, minimum and/or maximum deflection angle, and minimum and/or maximum rate of change.

8. The method of claim 1 , wherein the optimal mix is computed based at least in part on a vehicle model that is linear.

9. The method of claim 8 , wherein the optimal mix is computed at least in part by formulating an associated optimization problem as a quadratic program.

10. The method of claim 8 , wherein the vehicle model is linearized, for any set of inputs, about a current operating point or a reference points near the current operating point.

11. The method of claim 1 , wherein the cost functions includes a term that penalizes actuator power consumption, deviation from a reference position, or uneven distribution across actuators.

12. The method of claim 11 , wherein the cost functions penalizes actuator power consumption, deviation from a reference position, or uneven distribution across actuators in a way that does not affect the optimality of the force and moment realization.

13. The method of claim 1 , wherein the cost functions includes a term that penalizes actuator power consumption and the power consumption term is modeled by a linear approximation or a set of piecewise linear approximations.

14. The method of claim 1 , wherein said weighted set of costs associated with one or more errors includes one or more different weights, each at a value determined at least in part to achieve in the case of saturation a priority associated with an axis with which the weight is associated.

15. The method of claim 14 , wherein said priority includes prioritizing moments associated with stability in a plane defined by a transverse axis and a longitudinal axis of the aircraft over one or more other forces and moments.

16. The method of claim 1 , wherein a solution space in which said optimal mix is found is determined at least in part based on sensor data.

17. The method of claim 16 , wherein said sensor data includes one or more of airspeed, ambient temperature, actuator temperature, and actuator health.

18. The method of claim 16 , wherein said sensor data is used to determine a current effectiveness of one or more actuators.

19. The method of claim 16 , wherein said sensor data is used to determine a current availability of one or more actuators.

20. The method of claim 1 , wherein the requested set of forces and moments is received from a flight controller.

21. The method of claim 1 , further comprising providing to each actuator included in the optimal mix a respective control signal reflecting a corresponding actuator parameter determined for the actuator.

22. The method of claim 21 , wherein the actuators in the mix include one or more of a propeller, a control surface, an actuator to change the orientation of aerodynamic surfaces or tilting or non-fixed motors, and a mix of actuators.

23. The method of claim 1 , wherein one or both of a cost function and a set of one or more constraints used to compute said optimal mix varies with vehicle state.

24. The method of claim 23 , wherein said vehicle state includes one or more of airspeed, angle of attack, and mode of operation.

25. 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.

26. 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.

Assignees

• Kitty Hawk Corp

Inventors

• Mahboubi Zouhair
• Hoffmann Gabe
• Toupet Olivier
• Martins-Rivas Herve

Classifications

• B64C27/28

  with forward-propulsion propellers pivotable to act as lifting rotors · CPC title

• B64C29/0025

  the propellers being fixed relative to the fuselage · CPC title

• B64C29/00 Primary

  Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft (rotorcraft B64C27/00) · CPC title

• G05D1/085

  to ensure coordination between different movements · CPC title

• G05D1/101

  specially adapted for aircraft · CPC title