Rudder control method and system for an aircraft

Patent metadata

Field	Value
Publication number	US-10054955-B2
Application number	US-201514966170-A
Country	US
Kind code	B2
Filing date	Dec 11, 2015
Priority date	Dec 19, 2014
Publication date	Aug 21, 2018
Grant date	Aug 21, 2018

Abstract

The system includes a rudder bar configured to be able to be actuated by a pilot of the aircraft, a unit for automatically detecting a position value corresponding to a position of the rudder bar, an auxiliary unit for generating a trim value, a computation unit configured to generate a control value as a function of the position value of the rudder bar and of the trim value. The computation unit is configured to generate the control value according to a nonlinear kinematic relative to the position value of the rudder bar.

First claim

The invention claimed is:

1. A rudder control method for an aircraft, said method comprising:
automatically detecting a position value (PP) corresponding to a position of a rudder bar of the aircraft, said rudder bar being configured to be able to be activated by a pilot of the aircraft;
generating a trim value (TL); and
generating a control value (OP) as a function of the position value (PP) of the rudder bar and of the trim value (TL), said control value (OP) being transmitted to at least one actuator of a rudder of the aircraft,
wherein the control value (OP) is generated so as to follow a nonlinear kinematic (C 1 to C 8 ) relative to the position value (PP) of the rudder bar, the kinematic being such that at least one of the two following conditions is fulfilled: when the position value of the rudder bar corresponds to a maximum endstop position (PMax) of the rudder bar, the control value is at a maximum value, and when the position value of the rudder bar corresponds to a minimum endstop position (PMin) of the rudder bar, the control value is at a minimum value, and
wherein the kinematic relative to a neutral position value (PN) of the rudder bar has a linear segment extending from a first predetermined threshold on one side of the neutral position to a second predetermined threshold on another side of the neutral position, the linear segment representing the control value based on the trim value having a non-zero value.

2. The method as claimed in claim 1 , wherein the absolute value of the difference (Δ 1 , Δ 2 ) between the control value (OP) and a non-trimmed control value increases at least once between the minimum position (PMin) and a neutral position (PN) of the rudder bar and decreases at least once between the neutral position (PN) and the maximum position (PMax) of the rudder bar.

3. The method as claimed in claim 2 , wherein the absolute value (Δ 1 ) of the difference between the control value (OP) and the non-trimmed control value increases linearly and decreases linearly.

4. The method as claimed in claim 3 , wherein the absolute value (Δ 1 ) of the difference between the control value (OP) and the non-trimmed control value increases linearly between the minimum position (PMin) and a first position (P 1 ) of the rudder bar situated between the minimum position (PMin) and the neutral position (PN) and/or decreases linearly between a second position (P 2 ) of the rudder bar and the maximum position (PMax), the second position (P 2 ) being situated between the neutral position (PN) and the maximum position (PMax).

5. The method as claimed in claim 1 , wherein the control value OP, the position value of the rudder bar PP and the trim value TL are defined, each, by normalized values in a range ranging from −100% to 100%, the nonlinear kinematic being such that the control value OP bears out the following relationships:
OP=(1−TL/50%)×(PP−50%)+(TL+50%), if the position value PP of the rudder bar ( 2 ) is greater than 50%;
OP=(1+TL/50%)×(PP−50%)+(TL−50%), if the position value PP of the rudder bar ( 2 ) is less than −50%;
OP=PP+TL, if the position value PP of the rudder bar ( 2 ) lies between −50% and 50%.

6. The method as claimed in claim 1 , wherein the nonlinear kinematic (C 1 to C 8 ) comprises at least three straight-line segments.

7. A rudder control method for an aircraft, said method comprising:
automatically detecting a position value (PP) corresponding to a position of a rudder bar of the aircraft, said rudder bar being configured to be able to be activated by a pilot of the aircraft;
generating a trim value (TL); and
generating a control value (OP) as a function of the position value (PP) of the rudder bar and of the trim value (TL), said control value (OP) being transmitted to at least one actuator of a rudder of the aircraft,
wherein the control value (OP) is generated so as to follow a nonlinear kinematic (C 1 to C 16 ) relative to the position value (PP) of the rudder bar, the kinematic being such that at least one of the two following conditions is fulfilled: when the position value of the rudder bar corresponds to a maximum endstop position (PMax) of the rudder bar, the control value is at a maximum value, and when the position value of the rudder bar corresponds to a minimum endstop position (PMin) of the rudder bar, the control value is at a minimum value,
wherein the kinematic relative to a neutral position value (PN) of the rudder bar has a linear segment extending from a first predetermined threshold on one side of the neutral position to a second predetermined threshold on another side of the neutral position, and
wherein the control value (OP) is generated so as to be a maximum or a minimum only at the moment when the position value (PP) of the rudder bar reaches a maximum thereof or a minimum thereof.

8. The method of claim 7 , wherein the absolute value of the difference (Δ 1 , Δ 2 ) between the control value (OP) and a non-trimmed control value increases at least once between the minimum position (PMin) and a neutral position (PN) of the rudder bar and decreases at least once between the neutral position (PN) and the maximum position (PMax) of the rudder bar.

9. The method of claim 8 , wherein the absolute value (Δ 1 ) of the difference between the control value (OP) and the non-trimmed control value increases linearly and decreases linearly.

10. The method as claimed in claim 9 , wherein the absolute value (Δ 1 ) of the difference between the control value (OP) and the non-trimmed control value increases linearly between the minimum position (PMin) and a first position (P 1 ) of the rudder bar situated between the minimum position (PMin) and the neutral position (PN) and/or decreases linearly between a second position (P 2 ) of the rudder bar and the maximum position (PMax), the second position (P 2 ) being situated between the neutral position (PN) and the maximum position (PMax).

11. The method as claimed in claim 7 , wherein the control value OP, the position value of the rudder bar PP and the trim value TL are defined, each, by normalized values in a range ranging from −100% to 100%, the nonlinear kinematic being such that the control value OP bears out the following relationships:
OP=(1−TL/50%)×(PP−50%)+(TL+50%), if the position value PP of the rudder bar ( 2 ) is greater than 50%;
OP=(1+TL/50%)×(PP−50%)+(TL−50%), if the position value PP of the rudder bar ( 2 ) is less than −50%;
OP=PP+TL, if the position value PP of the rudder bar ( 2 ) lies between −50% and 50%.

12. The method as claimed in claim 7 , wherein the nonlinear kinematic (C 1 to C 8 ) comprises at least three straight-line segments.

13. A rudder control system for an aircraft, of electric type, comprising:
a rudder bar configured to be actuated by a pilot of the aircraft;
a unit for automatically detecting a position value (PP) corresponding to a position of the rudder bar;
an auxiliary unit for generating a trim value (TL); and
a computation unit configured to generate a control value (OP) as a function of the position value (PP) of the rudder bar and of the trim value (TL), said control value (OP) being configured to be transmitted to at least one actuator of a rudder of the aircraft, wherein the computation unit is configured to generate the control value (OP) according to a nonlinear kinematic relative to the position value (PP) of the rudder bar, the kinematic being such that at least one of the following two conditions is fulfilled: when the position value of the rudder bar corresponds to a maximum endstop position (PMax) of the rudder bar, the control value is at a maximum value, and when the position value of the rudder bar co

Assignees

• Airbus Operations Sas

Inventors

• Brot Patrice
• Devineau Sylvain

Classifications

• B64C13/507 Primary

  with artificial feel · CPC title

• B64C13/503

  Fly-by-Wire · CPC title

• B64C13/24

  Transmitting means · CPC title

• G05D1/0816 Primary

  to ensure stability · CPC title