Method and system for longitudinal control of aircraft

Patent metadata

Field	Value
Publication number	US-11460865-B2
Application number	US-201916715519-A
Country	US
Kind code	B2
Filing date	Dec 16, 2019
Priority date	Dec 20, 2018
Publication date	Oct 4, 2022
Grant date	Oct 4, 2022

Abstract

Methods and systems for longitudinal control of aircraft during flight are disclosed. One method comprises receiving a commanded normal acceleration of the aircraft and computing a target pitch rate for the aircraft based on the commanded normal acceleration. The target pitch rate is used in a control technique for controlling one or more flight control surfaces of the aircraft to achieve the target pitch rate for the aircraft. The control technique can include (e.g., incremental) nonlinear dynamics inversion.

First claim

What is claimed is:

1. A method for longitudinal control of an aircraft during flight, the method comprising:
receiving a commanded normal acceleration of the aircraft;
computing a target pitch rate for the aircraft based on the commanded normal acceleration;
using the target pitch rate in a control technique for controlling one or more flight control surfaces of the aircraft; and
controlling the one or more flight control surfaces of the aircraft using the control technique to achieve the target pitch rate for the aircraft;
wherein the method also includes:
computing the target pitch rate using a feedback controller;
computing a value of a handling quality criterion associated with the commanded normal acceleration of the aircraft, the handling quality criterion including a blend of normal acceleration and pitch rate of the aircraft as a function of a speed of the aircraft; and
using the value of the handling quality criterion as a set point for the feedback controller; and
wherein the handling quality criterion generates, at a first aircraft speed, a weak normal acceleration cue and a predominant pitch rate cue, and, at a second aircraft speed higher than the first aircraft speed, a weak pitch rate cue and a predominant normal acceleration cue.

2. The method as defined in claim 1 , wherein the control technique includes incremental nonlinear dynamics inversion.

3. The method as defined in claim 1 , wherein the control technique includes nonlinear dynamics inversion.

4. The method as defined in claim 1 , comprising computing the target pitch rate using a feedforward controller.

5. The method as defined in claim 1 , wherein computing the target pitch rate comprises:
using a feedforward controller to compute a pitch rate feedforward command;
using the feedback controller to compute a pitch rate feedback command; and
summing the pitch rate feedforward command and the pitch rate feedback command to compute the target pitch rate.

6. The method as defined in claim 1 , comprising:
receiving a pitch acceleration of the aircraft; and
using the pitch acceleration of the aircraft in the control technique.

7. The method as defined in claim 1 , comprising:
computing a pitch acceleration of the aircraft based on data acquired via one or more sensors; and
using the pitch acceleration of the aircraft in the control technique.

8. The method as defined in claim 1 , comprising:
receiving a position of at least one of the flight control surfaces of the aircraft; and
using the position of the at least one flight control surface in the control technique.

9. The method as defined in claim 1 , wherein the commanded normal acceleration of the aircraft is based on an input command originating from a pilot input device onboard the aircraft.

10. The method as defined in claim 1 , wherein the commanded normal acceleration of the aircraft is modified for speed stability.

11. The method as defined in claim 1 , wherein the commanded normal acceleration of the aircraft is modified for turn compensation.

12. A system for longitudinal control of an aircraft during flight, the system comprising:
one or more computers operatively coupled to receive one or more signals indicative of a commanded normal acceleration of the aircraft, the one or more computers being configured to:
compute a target pitch rate for the aircraft based on the commanded normal acceleration;
use the target pitch rate in a control technique for controlling one or more flight control surfaces of the aircraft; and
control the one or more flight control surfaces of the aircraft using the control technique to achieve the target pitch rate for the aircraft;
wherein the one or more computers are also configured to:
compute the target pitch rate using a feedback controller;
compute a value of a handling quality criterion associated with the commanded normal acceleration of the aircraft, the handling quality criterion including a blend of normal acceleration and pitch rate of the aircraft as a function of a speed of the aircraft; and
use the value of the handling quality criterion as a set point for the feedback controller; and
wherein the handling quality criterion generates, at a first aircraft speed, a weak normal acceleration cue and a predominant pitch rate cue, and, at a second aircraft speed higher than the first aircraft speed, a weak pitch rate cue and a predominant normal acceleration cue.

13. The system as defined in claim 12 , wherein the control technique includes incremental nonlinear dynamics inversion.

14. The system as defined in claim 12 , wherein the control technique includes nonlinear dynamics inversion.

15. The system as defined in claim 12 , wherein the one or more computers are configured to compute the target pitch rate using a feedforward controller.

16. The system as defined in claim 12 , wherein computing the target pitch rate comprises:
using a feedforward controller to compute a pitch rate feedforward command;
using the feedback controller to compute a pitch rate feedback command; and
summing the pitch rate feedforward command and the pitch rate feedback command to compute the target pitch rate.

17. The system as defined in claim 12 , wherein the one or more computers are configured to:
receive a pitch acceleration of the aircraft; and
use the pitch acceleration of the aircraft in the control technique.

18. The system as defined in claim 12 , wherein the one or more computers are configured to:
compute a pitch acceleration of the aircraft based on data acquired via one or more sensors; and
use the pitch acceleration of the aircraft in the control technique.

19. The system as defined in claim 12 , wherein the one or more computers are configured to:
receive a position of at least one of the flight control surfaces of the aircraft; and
use the position of the at least one flight control surface in the control technique.

20. The system as defined in claim 12 , wherein the commanded normal acceleration of the aircraft is based on an input command originating from a pilot input device onboard the aircraft.

21. The system as defined in claim 12 , wherein the commanded normal acceleration of the aircraft is modified for speed stability.

22. The system as defined in claim 12 , wherein the commanded normal acceleration of the aircraft is modified for turn compensation.

23. An aircraft comprising the system as defined in claim 12 .

Assignees

• Bombardier Inc

Inventors

• Kron Aymeric
• Olsthoorn Matthew

Classifications

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64C39/10

  All-wing aircraft · CPC title

• B64C2039/105

  of blended wing body type · CPC title

• B64C13/503

  Fly-by-Wire · CPC title

• B64C13/18

  using automatic pilot · CPC title