ACTUATOR MONITORING SYSTEM

Abstract

An actuator monitoring system is provided with an electric actuator having a motor and a control unit which outputs a control command (CMD) to the motor to control the operation of the motor. The control unit calculates a use time of the electric actuator based on the control command (CMD) outputted to the motor. Moreover, the control unit estimates the lifetime of the electric actuator based on the calculated use time.

Description

TECHNICAL FIELD

The present invention is relates to an actuator monitoring system which monitors an actuator installed in an aircraft.

BACKGROUND ART

Actuators are installed in an aircraft to drive an airfoil, a taking-off and landing unit and so on. The actuator is repaired or replaced when it fails or reaches repair timing. The repair timing is typically determined by a serviceman based on a past repair record.

However, strictly, operation records differ from each other for every aircraft. Therefore, there is a possibility that the actuator fails prior to previously set repair timing. Also, there is a case that the actuator can be used sufficiently even if the previously set repair timing has passed away. Therefore, the technique which can estimate the lifetime of the actuator in a high precision is demanded.

Patent Literature 1 discloses a technique that can know the exchange timing of the actuator even if the aircraft is in a flight condition. Specifically, a position sensor attached to the actuator detects a position of a piston of the actuator and outputs a position signal to a control unit. The control unit calculates a movement amount of the piston of the actuator based on a position signal. When a total movement amount of the piston of the actuator exceeds a preset threshold value, the control unit outputs a notice signal. The notice signal is outputted even if the aircraft is in the flight condition.

CITATION LIST

[Patent literature 1]: JP 2010-247602A

SUMMARY OF THE INVENTION

One object of the present invention is to provide a technique which can estimate a lifetime of an actuator installed in an aircraft in a high precision.

[The means to solve a problem] will be described using the number and the code which is used for the following in [the form to implement invention]. These numbers and a code were added in the one with the brackets to clarify compatible relation between the mention of [the Scope of Patent to be claimed] and [the form to implement invention]. But, do not use those numbers and a code for the interpretation of the technical range of the invention which is mentioned to [the Scope of Patent to be claimed].

In one aspect of the present invention, an actuator monitoring system (1) is provided with an electric actuator (10) having a motor (11), and a control unit (20) which outputs a control command (CMD) to the motor (11) to control the operation of the motor (11). The control unit (20) calculates a use time of the electric actuator (10) based on the control command (CMD) outputted to the motor (11). Moreover, the control unit (20) estimates a lifetime of the electric actuator (10) based on the calculated use time.

The motor (11) may feed back a feedback signal (FB) showing a value of electric current which flows through itself, to the control unit (20). In this case, the control unit (20) calculates a torque of the motor (11) based on the feedback signal (FB). Then, the control unit (20) estimates the lifetime of the electric actuator (10) based on the calculated use time and the calculated torque.

When the actuator reaches the estimated lifetime earlier than the previously set repair timing, the control unit (20) may output a warning through a warning unit (30).

According to the present invention, the lifetime of the actuator installed in the aircraft can be estimated in a high precision.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a block diagram showing a configuration of an actuator monitoring system according to a first embodiment of the present invention; and

FIG. 2 is a block diagram showing a configuration of the actuator monitoring system according to a second embodiment of the present invention.

DESCRIPTION OF EMBODIMENTS

Hereinafter, embodiments of the present invention will be described with reference to the attached drawings

First Embodiment

FIG. 1 is a block diagram showing a configuration of an actuator monitoring system 1 according to a first embodiment of the present invention. The actuator monitoring system 1 is installed in an aircraft. The actuator monitoring system 1 is composed of an electric actuator 10, a control unit 20 and a warning unit 30.

The electric actuator 10 drives a control surface and a taking-off and landing unit of the aircraft. The electric actuator 10 is composed of an electric motor 11.

The control unit 20 may be typically a flight control computer (FCC) which is installed in the aircraft. The control unit 20 controls the operations of other units installed in the aircraft. Especially, in the present embodiment, the control unit 20 outputs a control command CMD to the motor 11 to control the operation of the motor 11. For example, the control command CMD is used to instruct ON/OFF of the motor 11 and instruct the number of rotations of the motor 11 and so on.

Also, the control unit 20 is composed of a storage unit 21. RAM (Random Access Memory) and HDD (Hard Disk Drive) are exemplified as the storage unit 21. Repair timing data RP, use time data UT, and estimated lifetime data LT are stored in the storage unit 21. The repair timing data RP shows previously set timing of the repair of the electric actuator 10. The use time data UT shows a use time of the electric actuator 10 calculated by the control unit 20 to be mentioned later. The estimated lifetime data LT shows a lifetime of the electric actuator 10 which is estimated by the control unit 20 to be mentioned later.

A display and lights are exemplified as the warning unit 30.

The operation of the actuator monitoring system 1 according to the present embodiment will be described as follows.

First, the repair timing of the electric actuator 10 is previously set based on past repair records. The repair timing data RP showing the repair timing is stored in the storage unit 21 of the control unit 20.

In the operation of the aircraft, the control unit 20 outputs the control command CMD to the motor 11 to control the operation of the motor 11 of the electric actuator 10. For example, the control command CMD is outputted to instruct ON/OFF of the motor 11 and instruct the number of rotations of the motor 11 and so on.

The control unit 20 calculates the use time of the electric actuator 10 based on the control command CMD outputted to the motor 11. The use time data UT showing the calculated use time is stored in the storage unit 21 of the control unit 20. Because the use time of the electric actuator 10 can be known, the lifetime of the electric actuator 10 can be estimated by referring to a database showing the past results. That is, the control unit 20 estimates an actual lifetime of the electric actuator 10 based on the above calculated use time. The estimated lifetime data LT showing the estimated lifetime is stored in the storage unit 21 of the control unit 20. It should be noted that the use time data UT and the estimated lifetime data LT are updated at any time by the control unit 20.

Also, the control unit 20 compares the estimated lifetime shown by the estimated lifetime data LT with the repair timing shown by the repair timing data RP. When the estimated lifetime ends earlier than the repair timing, the control unit 20 drives the warning unit 30. The warning unit 30 output a warning to a pilot. For example, when the warning unit 30 is a display, the warning is displayed on the display. When the warning unit 30 is a light, the light is lighted up. Also, when the electric actuator 10 does not reach the estimated lifetime but reaches the repair timing, the control unit 20 may drive the warning unit 30.

As described above, according to the present embodiment, the lifetime of the electric actuator 10 can be estimated in a high precision based on the control command CMD outputted to the motor 11. Thus, it becomes possible to prevent a failure of the electric actuator 10 prior to the previously set repair timing. As a result, the reliability of the control system of the aircraft can be improved.

Second Embodiment

FIG. 2 is a block diagram showing a configuration of the actuator monitoring system 1 according to a second embodiment of the present invention. The description which overlaps the first embodiment will be appropriately omitted.

In the second embodiment, the motor 11 feeds back the feedback signal FB showing the value of electric current which flows through itself, to the control unit 20. The control unit 20 calculates the torque of the motor 11 based on the feedback signal FB received from the motor 11. Thus, the control unit 20 can estimate a load imposed on the electric actuator 10. Load record data LD showing a record of the estimated load is stored in the storage unit 21 of the control unit 20. It should be noted that the load record data LD is updated at any time by the control unit 20.

The control unit 20 estimates an actual lifetime of the electric actuator 10 in the consideration of the record of the estimated load shown by the load record data LD, in addition to the use time shown by the use time data UT. Therefore, the precision of the estimation of the lifetime of the electric actuator 10 can be further improved than the first embodiment.

Third Embodiment

The control unit 20 is not limited only to a flight control computer (FCC). For example, the control unit 20 may contain an actuator control computer (ACC). The FCC outputs a position command to the ACC, and the ACC outputs the control command CMD of the electric current command and so on to the motor 11 of the electric actuator 10. In this case, the ACC may estimate the actual lifetime of the electric actuator 10 based on the control command CMD outputted to the motor 11 and the feedback signal FB received from the motor 11. In this case, the ACC outputs the warning signal to the FCC, and the FCC drives the warning unit 30 in response to the warning signal. By such a configuration, the same effect as in the above embodiments can be attained.

The embodiments of the present invention have been described with reference to the attached drawings. However, the present invention is not limited to the above-mentioned embodiments and can be appropriately modified without deviating from the spirit of the present invention.

The present application claims a priority on convention based on Japanese Patent Application JP 2011-075987 filed on Mar. 30, 2011. The disclosure thereof is incorporated herein by reference.

Claims

1. An actuator monitoring system comprising: an electric actuator comprising a motor; anda control unit configured to output a control command to said motor to control an operation of said motor,wherein said control unit calculates a use time of said electric actuator based on the control command outputted to said motor, and estimates a lifetime of said electric actuator based on the calculated use time.

2. The actuator monitoring system according to claim 1, wherein said motor feeds back a feedback signal to said control unit to show a value of electric current which flows through said motor, and wherein said control unit calculates a torque of said motor based on the feedback signal and estimates the lifetime of said electric actuator based on the calculated use time and the calculated torque.

3. The actuator monitoring system according to claim 1, wherein when said electric actuator reaches the lifetime earlier than a previously set repair timing, said control unit drives a warning unit to output a warning.

4. (canceled)

5. The actuator monitoring system according to claim 2, wherein when said electric actuator reaches the lifetime earlier than a previously set repair timing, said control unit drives a warning unit to output a warning.

6. An aircraft comprising an actuator monitoring system which comprises: an electric actuator comprising a motor; anda control unit configured to output a control command to said motor to control an operation of said motor,wherein said control unit calculates a use time of said electric actuator based on the control command outputted to said motor, and estimates a lifetime of said electric actuator based on the calculated use time.

7. The aircraft according to claim 6, wherein said motor feeds back a feedback signal to said control unit to show a value of electric current which flows through said motor, and wherein said control unit calculates a torque of said motor based on the feedback signal and estimates the lifetime of said electric actuator based on the calculated use time and the calculated torque.

8. The aircraft according to claim 6, wherein when said electric actuator reaches the lifetime earlier than a previously set repair timing, said control unit drives a warning unit to output a warning.

9. The aircraft according to claim 7, wherein when said electric actuator reaches the lifetime earlier than a previously set repair timing, said control unit drives a warning unit to output a warning.