Aerodynamic control surface movement monitoring system for aircraft

Patent metadata

Field	Value
Publication number	US-10501201-B2
Application number	US-201715469740-A
Country	US
Kind code	B2
Filing date	Mar 27, 2017
Priority date	Mar 27, 2017
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

Abstract

Actuator systems and methods for controlling aerodynamic control surfaces of aircraft including a first actuator receiving a first input and a first linear translation element that moves based thereon, the first linear translation element operably connected to a first portion of the control surface. A first sensor assembly is disposed relative to the first actuator that generates an output based on a displacement of the first translation element. A second actuator receives a second input and a second linear translation element moves based on the second input, the second linear translation element operably connected to a second portion of the control surface. A second sensor assembly is disposed relative to the second actuator that generates a second sensor output based on a displacement of the second translation element. A controller generates the inputs and receives the sensor outputs to determine if an error condition exists for the system.

First claim

The invention claimed is:

1. An actuator system for controlling an aerodynamic control surface of an aircraft, the system comprising:
a first actuator receiving a first actuator input and a first linear translation element that moves based on the first actuator input, the first linear translation element operably connected to a first portion of the aerodynamic control surface to move the first portion of the aerodynamic control surface;
a first sensor assembly disposed relative to the first actuator that generates a first sensor output based on a displacement of the first linear translation element;
a second actuator receiving a second actuator input and a second linear translation element that moves based on the second actuator input, the second linear translation element operably connected to a second portion of the aerodynamic control surface to move the second portion of the aerodynamic control surface;
a second sensor assembly disposed relative to the second actuator that generates a second sensor output based on a displacement of the second linear translation element; and
a controller that generates the first and second actuator inputs and receives the first and second sensor outputs and determines if an error condition exists for the system based on the first and second sensor outputs
wherein the first linear translation element is a magnetic shaft formed from alternating magnetic elements that is driven by an electromagnetic stator,
wherein the first sensor assembly comprises a first magnetic sensor and a second magnetic sensor, wherein the first and second magnetic sensors are positioned relative to the first linear translation element to detect the alternating magnetic elements of the first linear translation element and the first and second magnetic sensors are positioned with an axial offset relative to the first linear translation element.

2. The actuator system of claim 1 , wherein the first and second actuators are electromagnetic actuators.

3. The actuator system of claim 1 , wherein the aerodynamic control surface is a flap or slat.

4. The actuator system of claim 1 , wherein the error condition is a skew condition of the aerodynamic control surface and is determined by the controller when the sensors outputs from the first and second sensor assemblies do not match.

5. The actuator system of claim 1 , further comprising a drive unit operably connected to the controller configured to drive a drive shaft that is operably connected to the first and second actuators, the drive unit causing the drive shaft to rotate based on signals received from the controller.

6. The actuator system of claim 1 , wherein the error condition is an actuator malfunction and is determined by the controller when at least one of the first actuator input and the second actuator input does not match a respective first or second sensor output.

7. The actuator system of claim 1 , wherein the magnetic sensors are Hall Effect sensors.

8. The actuator system of claim 1 , wherein the first sensor assembly comprises at least two sensing elements positioned relative to the linear translation element and configured to detect a position or movement of the linear translation element.

9. A method of controlling and monitoring an aerodynamic control surface of an aircraft, the method comprising:
sending an first actuator input from a controller to a first actuator to drive a movement of a first linear translation element that is operably connected to a first portion of the aerodynamic control surface;
sending an second actuator input from the controller to a second actuator to drive a movement of a second linear translation element that is operably connected to a second portion of the aerodynamic control surface;
generating a first sensor output with a first sensor assembly disposed relative to the first actuator, the first sensor output being based an amount of linear motion of the first linear translation element;
generating a second sensor output with a second sensor assembly disposed relative to the second actuator, the second sensor output being based an amount of linear motion of the second linear translation element;
comparing expected sensor outputs to the first and second sensor outputs using the controller to determine if an error condition exists; and
generating an error indication when the error condition exists,
wherein the first linear translation element is a magnetic shaft formed from alternating magnetic elements that is driven by an electromagnetic stator, the method further comprising detecting variations in magnetic field that correlate to linear motion of the first and second linear translation elements, and
wherein the first sensor assembly comprises a first magnetic sensor and a second magnetic sensor, wherein the first and second magnetic sensors are at least one of (i) positioned relative to the first linear translation element to detect the alternating magnetic elements of the first linear translation element or (ii) positioned with an axial offset relative to the first linear translation element.

10. The method of claim 9 , wherein the first and second actuators are electromagnetic actuators, the method further comprising detecting variations in magnetic field that correlate to linear motion of the first and second linear translation elements.

11. The method of claim 9 , wherein the error condition is at least one of (i) a skew condition of the aerodynamic control surface and is determined by the controller when the sensors outputs from the first and second sensor assemblies do not match or (ii) an actuator malfunction and is determined by the controller when at least one of the first actuator input and the second actuator input does not match a respective first or second sensor output.

12. The method of claim 9 , further comprising detecting a characteristic ofthe first and second linear translation elements and correlating the detected characteristics to linear motion of the respective first and second linear translation elements.

13. An actuator system for controlling an aerodynamic control surface of an aircraft, the system comprising:
a first actuator receiving a first actuator input and a first linear translation element that moves based on the first actuator input, the first linear translation element operably connected to a first portion of the aerodynamic control surface to move the first portion of the aerodynamic control surface;
a first sensor assembly disposed relative to the first actuator that generates a first sensor output based on a displacement of the first linear translation element;
a second actuator receiving a second actuator input and a second linear translation element that moves based on the second actuator input, the second linear translation element operably connected to a second portion of the aerodynamic control surface to move the second portion of the aerodynamic control surface;
a second sensor assembly disposed relative to the second actuator that generates a second sensor output based on a displacement of the second linear translation element; and
a controller that generates the first and second actuator inputs and receives the first and second sensor outputs and determines if an error condition exists for the system based on the first and second sensor outputs,
wherein the first linear translation element is a threaded ball screw shaft that is driven by a ball nut, and
wherein the first sensor assembly comprises a first optical sensor and a second optical sensor, wherein the first and second optical sensors are positioned relative to the first linear translation element to detect the threads of the first lin

Assignees

• Hamilton Sundstrand Corp

Inventors

• Harrington Erik
• Miller Christian
• Bishop Yuniya S

Classifications

• B64D45/0005 Primary

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

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64C9/22

  at the front of the wing · CPC title

• B64C9/16

  at the rear of the wing · CPC title

• B64C13/28

  mechanical · CPC title