Monitoring system for an assembly having a kinematic coupling

Patent metadata

Field	Value
Publication number	US-11708178-B2
Application number	US-202017119289-A
Country	US
Kind code	B2
Filing date	Dec 11, 2020
Priority date	Dec 12, 2019
Publication date	Jul 25, 2023
Grant date	Jul 25, 2023

Abstract

A monitoring system for monitoring a kinematic coupling between an actuator and an element controlled by the latter includes a first sensor to detect the operative movement of the actuator. A second sensor is designed to detect the actual movement of the controlled element. A computer unit, based on the operative movement of the actuator, determines an anticipated movement of the controlled element and compares this anticipated movement with the actual movement of the controlled element. An error message is emitted when a value of the deviation between the anticipated movement and the actual movement exceeds a predefined threshold value.

First claim

The invention claimed is:

1. A monitoring system for monitoring a kinematic coupling between an actuator and a controlled element of an aircraft, wherein the monitoring system comprises:
a first sensor disposed such that said first sensor is configured to detect an operative movement of the actuator and, based on the detected operative movement of the actuator, to provide a first signal;
a second sensor disposed such that said second sensor is configured to detect a movement of the controlled element and, based on the detected movement of the controlled element, to provide a second signal;
a computer unit connected to the first sensor and the second sensor and configured to receive the first signal and the second signal;
wherein the computer unit, based on the first signal, is configured to determine an anticipated movement of the controlled element and to compare the anticipated movement with the detected movement corresponding to the second signal and to provide a deviation between the anticipated movement and the detected movement,
wherein the computer unit is configured to carry out a task which is usually carried out by a dedicated testing apparatus at predefined maintenance intervals on ground, and to carry out the task during operation of the aircraft in the air;
wherein the computer unit is configured to compare the anticipated movement with the detected movement, and determine a deviation between the anticipated movement and the detected movement; and
wherein the computer unit is configured to output an indication when the deviation exceeds a threshold value.

2. The monitoring system according to claim 1 , wherein the computer unit is configured to compare the deviation between the anticipated movement and the detected movement with a threshold value and to emit an error message when the deviation reaches or exceeds the threshold value.

3. The monitoring system according to claim 1 , wherein the computer unit, based on a model of the kinematic coupling, is configured to determine the anticipated movement of the controlled element.

4. The monitoring system according to claim 1 , wherein the first sensor as well as the second sensor are sensors selected from the group consisting of: a movement sensor, an angular rate sensor, a rotational position sensor, an angle sensor, a linear variable differential transformer, an optical sensor, a mechanical sensor having moving parts, a magnetic sensor, and a Hall effect sensor.

5. The monitoring system according to claim 1 , wherein the second sensor is configured to detect the movement of the controlled element at a scanning rate of more than 1 kHz.

6. The monitoring system according to claim 1 , wherein the computer unit is configured to supply the second signal to a filter and to use the filtered signal for the comparison with the first signal.

7. An aircraft, having a monitoring system according to claim 1 .

8. The aircraft according to claim 7 , wherein the controlled element is a control surface of the aircraft;
wherein the actuator is an actuator connected to the control surface by way of a kinematic coupling.

9. The aircraft according to claim 8 , wherein the second sensor is disposed so as to detect a relative movement between the control surface and a fuselage or any other component of the aircraft that is connected to the fuselage.

10. The aircraft according to claim 7 , wherein the computer unit is configured to implement functions of the flight controls for the aircraft.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Köhler Thomas

Classifications

• B64F5/60 Primary

  Testing or inspecting aircraft components or systems · CPC title

• B64C13/18

  using automatic pilot · CPC title

• G01B21/22

  for measuring angles or tapers; for testing the alignment of axes · CPC title

• B64C13/28 Primary

  mechanical · CPC title

• B64D45/0005

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title