Split-reference system and method for rapid re-trimming rate command of force trim release

Patent metadata

Field	Value
Publication number	US-11623740-B2
Application number	US-202117407379-A
Country	US
Kind code	B2
Filing date	Aug 20, 2021
Priority date	Feb 19, 2021
Publication date	Apr 11, 2023
Grant date	Apr 11, 2023

Abstract

A flight control system includes an active control inceptor, a flight control computer, and a force trim release. The active control inceptor includes a control member movable from a first position to a second position to command a vehicle-body rate and including a detent position that holds an attitude. The flight control computer generates a trim command from the second position, a reference position, and a vehicle-body state. With the force trim release selected when the control member is moved from the first position to the second position, the first position is designated as the reference position and the second position is designated as the detent position. Upon deselection of the force trim release with the control member at the second position, the second position is designated as the reference position and the trim command is designated as the detent position.

First claim

What is claimed is:

1. A flight control system of an aeronautic vehicle, the flight control system comprising:
an active control inceptor configured to selectively control a flight control surface of the aeronautic vehicle and comprising a control member, configured to be moved from a first stick position to a second stick position to command a vehicle-body rate of the aeronautic vehicle and comprising a detent position that holds an attitude of the aeronautic vehicle when an input force, applied to the control member by an operator, is zero;
a flight control computer coupled to the active control inceptor and programmed to generate a trim command from the second stick position, a reference position, and a vehicle-body state of the aeronautic vehicle; and
a force trim release coupled to the active control inceptor and to the flight control computer, wherein the force trim release is configured to be selected or deselected,
wherein:
with the force trim release selected when the control member is moved from the first stick position to the second stick position by application of the input force by the operator, the flight control computer designates the reference position to be equal to the first stick position and the active control inceptor designates the detent position to be equal to the second stick position; and
upon deselection of the force trim release with the control member at the second stick position, the flight control computer designates the reference position to be equal to the second stick position and the active control inceptor designates the detent position to be equal to the trim command.

2. The flight control system of claim 1 , wherein:
with the force trim release selected, the flight control computer is programmed to:
determine a stick delta between the reference position and the second stick position; and
generate a rate command from the stick delta; and

the trim command is generated from the rate command and the vehicle-body state.

3. The flight control system of claim 2 , further comprising a state sensor configured to generate a sensor signal representing the vehicle-body state.

4. The flight control system of claim 1 , wherein, upon deselection of the force trim release, the active control inceptor designates the detent position to be equal to the second stick position until the trim command is within a predefined threshold of the detent position, whereupon the active control inceptor designates the detent position to be equal to the trim command.

5. The flight control system of claim 1 , further comprising a trim rate limiter, configured to generate a rate limited trim command based on the trim command,
wherein, upon deselection of the force trim release, the active control inceptor designates the detent position to be equal to the rate limited trim command.

6. The flight control system of claim 5 , wherein, upon deselection of the force trim release, the active control inceptor designates the detent position to be equal to the second stick position until the rate limited trim command is within a predefined threshold of the detent position, whereupon the active control inceptor designates the detent position to be equal to the rate limited trim command.

7. The flight control system of claim 1 , wherein, with the force trim release deselected when the control member is moved from the first stick position to the second stick position, the flight control computer designates the reference position to be equal to the detent position when conditions of merge have been satisfied.

8. The flight control system of claim 1 , wherein:
the active control inceptor further comprises an inceptor actuator coupled to the control member and configured to selectively apply a back-drive force to the control member based on selection or deselection of the force trim release;
with the force trim release selected, the inceptor actuator is configured to not apply the back-drive force to the control member; and
with the force trim release deselected and the input force, applied to the control member by the operator, being zero, the inceptor actuator is configured to apply the back-drive force to the control member to automatically move the control member to the detent position.

9. The flight control system of claim 1 , wherein the force trim release is configured to be normally deselected.

10. An aeronautic vehicle comprising:
a flight control surface configured to selectively control an attitude of the aeronautic vehicle;
an active control inceptor configured to selectively control the flight control surface and comprising a control member, configured to be moved from a first stick position to a second stick position to command a vehicle-body rate of the aeronautic vehicle and comprising a detent position that holds the attitude of the aeronautic vehicle when an input force, applied to the control member by an operator, is zero;
a flight control computer coupled to the active control inceptor and programmed to generate a trim command from the second stick position, a reference position, and a vehicle-body state of the aeronautic vehicle; and
a force trim release coupled to the active control inceptor and to the flight control computer, wherein the force trim release is configured to be selected or deselected,
wherein:
with the force trim release selected when the control member is moved from the first stick position to the second stick position by application of the input force by the operator, the flight control computer designates the reference position to be equal to the first stick position and the active control inceptor designates the detent position to be equal to the second stick position; and
upon deselection of the force trim release with the control member at the second stick position, the flight control computer designates the reference position to be equal to the second stick position and the active control inceptor designates the detent position to be equal to the trim command.

11. The aeronautic vehicle of claim 10 , wherein:
with the force trim release selected, the flight control computer is programmed to:
determine a stick delta between the reference position and the second stick position; and
generate a rate command from the stick delta; and

the flight control computer is programmed to generate the trim command based on the rate command and the vehicle-body state.

12. The aeronautic vehicle of claim 11 , further comprising a state sensor configured to generate a sensor signal representing the vehicle-body state.

13. The aeronautic vehicle of claim 10 , wherein, upon deselection of the force trim release, the active control inceptor designates the detent position to be equal to the second stick position until the trim command is within a predefined threshold of the detent position, whereupon the active control inceptor designates the detent position to be equal to the trim command.

14. The aeronautic vehicle of claim 10 , wherein the active control inceptor further comprises a trim rate limiter, configured to generate a rate limited trim command based on the trim command,
wherein, upon deselection of the force trim release, the active control inceptor designates the detent position to be equal to the rate limited trim command.

15. The aeronautic vehicle of claim 14 , wherein, upon deselection of the force trim release, the active control inceptor designates the detent position to be equal to the second stick position until the rate limited trim command is within a predefined threshold of the detent position, whereupon the active control inceptor designates the detent

Assignees

• Boeing Co

Inventors

• Chu Bryan C
• Walrath Jacob
• Klein Gary D
• Hunter Donald J

Classifications

• B64C13/08

  Trimming zero positions · CPC title

• B64C13/0421

  control sticks for primary flight controls · CPC title

• B64C27/68

  using electrical energy, e.g. having electrical power amplification · CPC title

• B64C13/503 Primary

  Fly-by-Wire · CPC title

• B64C13/16

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