Bleed air duct leak system real-time fault detection

Patent metadata

Field	Value
Publication number	US-9823154-B2
Application number	US-201414539485-A
Country	US
Kind code	B2
Filing date	Nov 12, 2014
Priority date	Nov 12, 2014
Publication date	Nov 21, 2017
Grant date	Nov 21, 2017

Abstract

A method and apparatus for testing a duct leak detection system of an aircraft is disclosed. A sensor of the duct leak detection system is selected at an interface of the duct leak detection system. An alternating current is sent through the selected sensor and a resistance of the selected sensor is measured using the alternating current. An indicative signal is generated at the interface when the measured resistance of the selected sensor is outside of a specification of the selected sensor.

First claim

The invention claimed is:

1. A method of monitoring and interactively testing a duct leak detection system of an aircraft having bleed air ducts, comprising:
monitoring in real time plural air duct sensors by a control system;
displaying in real time, on an interface coupled to the control system, faults, ruptures or possible emergencies sensed by the sensors, wherein the interface includes a display and a selector switch;
the method further comprising interactively:
selecting with the interface, one of the sensors for sensor health testing;
sending, by the control system, an alternating current through the selected sensor;
measuring, by the control system, a resistance of the selected sensor ( 212 ) in response to the test current, wherein the resistance is a loop resistance ( 352 ) and a to-ground resistance ( 354 ) related to the selected sensor ( 212 ); and
displaying, with the interface measured results; and
in additional to displaying measured results, generating an indicative signal that is displayed with the interface when the measured resistance of the selected sensor is outside of a specification of the selected sensor.

2. The method of claim 1 , further comprising measuring the resistance of the selected sensor when the airplane is in a powered state.

3. The method of claim 1 , wherein the resistance is indicative of a health of the sensor.

4. The method of claim 1 , further comprising testing an air duct associated with the selected sensor using a command selected from the interface.

5. The method of claim 1 , further comprising displaying the resistance of the selected sensor at the interface.

6. The method of claim 1 , further comprising selecting a command at the interface to send the alternating current through the selected sensor.

7. An apparatus for monitoring and interactively testing a bleed duct detection system having bleed air ducts, comprising:
an interface, that includes a display and a selector switch, for operation of the bleed duct detection system;
a circuit coupled to the interface, the circuit configured to:
monitor in real time plural air duct sensors;
display in real time, with the interface, faults, ruptures or possible emergencies sensed by the sensors;
the circuit further configured to interactively:
receive a selection from the interface, one of the sensors of the duct leak detection system for sensor health testing;
send a test current which is an alternating current through the selected sensor of the bleed duct detection system, and
measure a resistance of the selected sensor in response to the test current, wherein the resistance is a loop resistance and a to-ground resistance; and
display, with the interface, measured results; and
in additional to the display of the measured results, display, with the interface an indicative signal generated when the measured resistance of the selected sensor is outside of a selected specification of the selected sensor.

8. The apparatus of claim 7 , wherein the circuit is further configured to measure the resistance of the selected sensor when the airplane is powered up.

9. The apparatus of claim 7 , wherein the interface is located in an electronics bay of the aircraft.

10. The apparatus of claim 7 , further comprising a circuit for testing an air duct associated with the selected sensor.

11. The apparatus of claim 7 , wherein the interface is adapted to display a resistance value of the selected sensor at the interface.

12. The apparatus of claim 7 , wherein the interface is adapted to display a loop circuit for the selected sensor at the interface.

13. The apparatus of claim 7 , further comprising a test circuit for measuring a parameter of the bleed duct using the selected sensor.

Assignees

• Kidde Tech Inc

Inventors

• Norris Robert J

Classifications

• B64D13/00

  Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space · CPC title

• G01K13/02

  for measuring temperature of moving fluids or granular materials capable of flow · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• G01R31/2829

  Testing of circuits in sensor or actuator systems (testing of apparatus for measuring electric or magnetic variables G01R35/00; testing of indicating or recording apparatus G01D; in airbag systems B60R21/0173; checking gas analysers G01N33/007; monitoring or fail-safe circuits for electromagnets H01F7/1844) · CPC title

• G01M3/002 Primary

  by using thermal means · CPC title