Actuator system for aircraft control surface

Patent metadata

Field	Value
Publication number	US-10029782-B2
Application number	US-201514682232-A
Country	US
Kind code	B2
Filing date	Apr 9, 2015
Priority date	Apr 16, 2014
Publication date	Jul 24, 2018
Grant date	Jul 24, 2018

Abstract

An actuator system includes an actuator which is configured to generate a loading on a control surface, as a function of an actuation order received, a command unit of the actuator, which is configured to compute an actuation order of the actuator, a reception element for receiving a current value of the loading generated by the actuator, and a limitation unit configured to reduce the control authority of the command unit as a function of the current value of the loading and to limit the loading of the actuator to a predetermined setpoint value.

First claim

The invention claimed is:

1. An actuator system for an aircraft control surface, said system comprising:
at least one actuator configured to generate a loading, as a function of an actuation order received;
a command unit of the at least one actuator configured to receive a control signal and an indication of position of the control surface, and to compute an actuation order with the aid of said control signal and of said position indication, said actuation order being transmitted to said at least one actuator; and
an activation unit comprising:
an auxiliary reception element configured to receive a current value of at least one parameter relating to at least one movement able to be linked to said at least one actuator;
a verification element configured to verify, with the aid at least of said current value, whether at least one activation condition is fulfilled; and
activation elements,

wherein said at least one actuator comprises:
at least one sensor configured to measure a current loading generated by the at least one actuator and to transmit a corresponding current value; and
a reception element for receiving the current value of the loading generated by the at least one actuator,

wherein the command unit comprises a limitation unit configured to limit and command the loading generated by the actuator, said limitation unit comprising:
a first unit configured to reduce the control authority of the command unit, as a function of said current value of the loading; and
a second unit configured to limit the loading of the actuator to a predetermined setpoint value,

wherein the first unit comprises:
a first computation element configured to compute a value of gain, as a function of a predetermined gain table and of said current value of the loading, received from the reception element; and
a second computation element configured to apply said gain to said actuation order, before transmitting said actuation order to said at least one actuator;

wherein the activation elements are configured to activate the first and second units when said at least one activation condition is fulfilled.

2. The system as claimed in claim 1 , wherein the second unit comprises:
a third computation element for comparing the current value of the loading received from the reception element, with said setpoint value;
a fourth computation element for computing a corrective term, if said current value of the loading is greater than said setpoint value; and
a fifth computation element for applying the corrective term to said actuation order, before transmitting said actuation order to said actuator.

3. A chain for positional slaving of an aircraft control surface, said slaving chain comprising:
at least one actuator system according to claim 1 ;
said control surface which is movable, and whose position is adjusted by said at least one actuator;
at least one position sensor for measuring the effective position of said control surface and for emitting a position indication corresponding to the effective position;
wherein said at least one actuator is configured to generate a loading, as a function of an actuation order received, so as to adjust the position of the control surface; and
a command unit of the at least one actuator configured to receive a control signal and said position indication, and to compute an actuation order with the aid of said control signal and of said position indication, said actuation order being transmitted to said at least one actuator.

4. A system of electric flight controls of an aircraft, said system comprising:
at least one control unit for producing a control signal for at least one control surface of the aircraft; and
at least one chain for positional slaving of the control surface according to claim 3 .

Assignees

• Airbus Operations Sas

Inventors

• Kossentini Chiheb
• Larrieu Nicholas
• Delabre Mathieu
• Pol Xavier

Classifications

• B64C13/504

  using electro-hydrostatic actuators [EHA's] · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C13/505 Primary

  having duplication or stand-by provisions · CPC title

• G01D5/2291

  Linear or rotary variable differential transformers (LVDTs/RVDTs) having a single primary coil and two secondary coils · CPC title

• B64C13/503

  Fly-by-Wire · CPC title