Method and device for automatic management of an actuator controlled by a servo-valve

Patent metadata

Field	Value
Publication number	US-10144501-B2
Application number	US-201615212582-A
Country	US
Kind code	B2
Filing date	Jul 18, 2016
Priority date	Jul 21, 2015
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

The device for automatic management of an actuator controlled by a servo-valve, includes a sensor for measuring the actual value of a parameter at the output of the actuator for a given control command, a computation unit for computing a theoretical value of said parameter, by applying the control command to a nominal performance model which models the operation of the actuator exhibiting nominal performance, a computation unit for computing the difference between the measured actual value of the parameter and the computed theoretical value of said parameter, a control unit for computing an adapted gain as a function of this difference, and a link for applying the adapted gain to the servo-valve for it to use it as gain value, so as to allow the actuator to restore nominal performance.

First claim

The invention claimed is:

1. A method for automatic management of an actuator, said actuator being controlled by a servo-valve using at least one value of a gain and receiving a control command, said method comprising:
a measurement step including measuring, in real time, the actual value of a parameter at the output of the actuator for a given control command;
a first computation step including computing, in real time, a theoretical value of said parameter, by applying said control command to a nominal performance model, the nominal performance model modeling the operation of the actuator exhibiting nominal performance;
a second computation step including computing, in real time, the difference between the measured actual value of the parameter and the computed theoretical value of said parameter;
a control step including computing an adapted gain of the actuator as a function of the difference, wherein nominal performance is restored using the actuator when said adapted gain is applied to the servo-valve; and
an application step including applying, in real time, said adapted gain to the servo-valve for the servo-valve to use the adapted gain as gain value,
wherein, for adapting the gain of a servo-value of an aircraft steering actuator, at least to reduce the phase shift between said actuator and the nominal transfer function of the actuator, the computation step includes computing said adapted gain K using the following expression:

K
=

K
0

*

1

a
*

∫

(

φ
0

-
φ

)

in which:
K 0 is an initial gain of the servo-valve ( 4 );
φ 0 is a phase at the output of the nominal performance model;
φ is a phase at the output of the actuator; and
a is an adaptation gain setting the speed with which the adapted gain K converges toward a desired value.

2. The method as claimed in claim 1 , wherein said performance model comprises a transfer function between a control command of a control law and the position of the actuator.

3. The method as claimed in claim 1 , wherein said parameter is one of the following parameters:
a phase shift; and
a gain dispersion.

4. The method as claimed in claim 1 , wherein said difference corresponds to a phase difference, said phase difference being computed from the time difference between the zero crossing of the output of the actuator and the closest zero crossing of the output of the nominal performance model.

5. A device for automatic management of an actuator, said actuator being controlled by a servo-valve using at least one value of a gain and receiving a control command, said device comprising:
at least one sensor configured to measure, in real time, the actual value of a parameter at the output of the actuator for a given control command;
a first computation unit configured to compute, in real time, a theoretical value of said parameter, by applying said control command to a nominal performance model, the nominal performance model modeling the operation of the actuator exhibiting nominal performance;
a second computation unit configured to compute, in real time, the difference between the measured actual value of the parameter and the computed theoretical value of said parameter;
a control unit configured to compute an adapted gain as a function of the difference, wherein nominal performance is restored using the actuator when said adapted gain is applied to the servo-valve; and
a link configured to apply, in real time, said adapted gain to the servo-valve for it to use it as gain value,
wherein, for adapting the gain of a servo-valve of an aircraft steering actuator, at least to reduce the phase shift between said actuator and the nominal transfer function of the actuator, the computation step includes computing said adapted gain K using the following expression:

K
=

K
0

*

1

a
*

∫

(

φ
0

-
φ

)

in which:
K 0 is an initial gain of the servo-valve ( 4 );
φ 0 is a phase at the output of the nominal performance model;

φ is a phase at the output of the actuator; and
a is an adaptation gain setting the speed with which the adapted gain K converges toward a desired value.

6. The device according to claim 5 , wherein said performance model comprises a transfer function between a control command of a control law and the position of the actuator.

7. The device according to claim 5 , wherein said parameter is one of the following parameters:
a phase shift; and
a gain dispersion.

8. The device according to claim 5 , wherein said difference corresponds to a phase difference, said phase difference being computed from the time difference between the zero crossing of the output of the actuator and the closest zero crossing of the output of the nominal performance model.

9. An actuator for an aircraft, said actuator being controlled by a servovalve using at least one value of a gain and receiving a control command,
wherein the actuator comprises an automatic management device comprising: at least one sensor configured to measure, in real time, the actual value of a parameter at the output of the actuator for a given control command;
a first computation unit configured to compute, in real time, a theoretical value of said parameter, by applying said control command to a nominal performance model, the nominal performance model modeling the operation of the actuator exhibiting nominal performance;
a second computation unit configured to compute, in real time, the difference between the measured actual value of the parameter and the computed theoretical value of said parameter;
a control unit configured to compute an adapted gain as a function of the difference, wherein nominal performance is restored using the actuator when said adapted gain is applied to the servo-valve; and
a link configured to apply, in real time, said adapted gain to the servo-valve for it to use it as gain value;
wherein, for adapting the gain of a servo-valve of an aircraft steering actuator, at least to reduce the phase shift between said actuator and the nominal transfer function of the actuator, the computation step includes computing said adapted gain K using the following expression:

Assignees

• Airbus Operations Sas

Inventors

• Fabre Pierre

Classifications

• B64C13/16

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

• B64C2009/005

  Ailerons · CPC title

• B64C9/00 Primary

  Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) · CPC title

• G05B13/042 Primary

  in which a parameter or coefficient is automatically adjusted to optimise the performance · CPC title

• G05D1/0825

  using mathematical models · CPC title