Rapid Decompression Detection System and Method

• US 20110201262A1
• Filed: 03/09/2009
• Published: 08/18/2011
• Est. Priority Date: 03/07/2008
• Status: Active Grant

• Current Assignee: Adams Rite Aerospace
• Original Assignee: Adams Rite Aerospace
• Inventors: Lehmann, Michael
• Granted Patent: US 9,180,959 B2
• Time in Patent Office: Days
• US Class Current: 454/74
• CPC Class Codes: B64C 1/1469 Doors between cockpit and cabin
• CPC Class Codes: B64C 2001/009 comprising decompression panels or valves for pressure equalisation in fuselages or floors
• CPC Class Codes: B64D 13/02 the air being pressurised

Abstract

A system for monitoring pressure change within at least one compartment of an aircraft is provided. The system includes a primary pressure sensor for providing a signal corresponding to a pressure within a primary compartment of the aircraft, a primary monitoring channel coupled to the primary pressure sensor, and an output driver coupled to the primary monitoring channel. The primary monitoring channel includes a band pass filter for receiving and filtering the primary pressure signal, a pressure change circuit for determining a change in the filtered pressure signal and for providing a pressure change output signal corresponding to the change in pressure, and a threshold logic circuit for determining whether the pressure change output signal meets a predetermined threshold and for providing a threshold output signal indicating that a decompression event has occurred if the pressure change output signal meets the predetermined threshold. The output driver receives the primary threshold output signal and outputs a notification signal.

Claims

1. A system for monitoring pressure change within at least one compartment of an aircraft, comprising:

a primary pressure sensor for providing a signal corresponding to a pressure within a primary compartment of an aircraft;

a primary monitoring channel, coupled to the primary pressure sensor, comprising;

a band pass filter for receiving and filtering the primary pressure signal,

a pressure change circuit for determining a change in the filtered pressure signal and for providing a pressure change output signal corresponding to the change in pressure; and

a threshold logic circuit for determining whether the pressure change output signal meets a predetermined threshold and for providing a threshold output signal indicating that a decompression event has occurred if the pressure change output signal meets the predetermined threshold; and

an output driver, coupled to the primary monitoring channel, for receiving the primary threshold output signal and for outputting a notification signal.

2. The system of claim 1, further comprising:

a secondary pressure sensor for providing a signal corresponding to a pressure within a secondary compartment of an aircraft adjacent to the primary compartment;

a secondary monitoring channel, coupled to the secondary pressure sensor, comprising;

a band pass filter for receiving and filtering the secondary pressure signal,

a pressure change circuit for determining a change in the filtered pressure signal and for providing a pressure change output signal corresponding to the change in pressure; and

a threshold logic circuit for determining whether the pressure change output signal meets the predetermined threshold and for providing a threshold output signal indicating that a decompression event has occurred if the pressure change output signal meets the predetermined threshold; and

wherein the output driver is coupled to the secondary monitoring channel and receives the secondary threshold output signal.

3. The system of claim 2, wherein each of the primary and secondary monitoring channels includes respective symmetry checkers for determining whether the decompression event is valid.

4. The system of claim 3, wherein each of the primary and secondary monitoring channels includes respective fault detection comparison circuits for comparing the primary and secondary pressure sensor signals to known values, or to each other, to determine whether an input error occurs, and fault detection reporting circuits for reporting that an input error has occurred if so determined.

5. The system of claim 4, wherein each of the fault detection comparison circuits monitor respective band pass filter signals, pressure change signals, and symmetry checker signals.

6. The system of claim 2, wherein each of the primary and secondary pressure sensors includes a pressure detector and an amplifier for receiving a pressure signal from the pressure detector, wherein the output of the amplifier provides a feedback input to the amplifier.

7. The system of claim 6, wherein the pressure sensor amplifier is coupled to a positive and a negative voltage supply.

8. The system of claim 6, wherein each of the primary and secondary pressure sensors includes a series resistor-capacitor (RC) filter having an input coupled to the pressure detector and an output coupled to the amplifier.

9. The system of claim 6, wherein each of the primary and secondary pressure monitoring channels includes a DC coupling circuit disposed within the band pass filter.

10. The system of claim 6, wherein each of the primary and secondary band pass filters includes a voltage divider for adjusting the gain of the filter.

11. The system of claim 6, wherein each of the primary and secondary pressure change signal circuits includes an amplifier coupled to a positive and a negative voltage supply, wherein the output of the amplifier provides a feedback input to the amplifier.

12. The system of claim 2, wherein each of the primary and secondary band pass filters filter signals outside a range of about 4 psi/second to about 200 psi/second.

13. A method of monitoring pressure change within at least one compartment of an aircraft, comprising:

receiving a pressure signal corresponding to a pressure within a primary compartment of an aircraft;

determining a change in the primary pressure signal;

determining whether the primary pressure change meets a predetermined threshold; and

if the primary pressure change meets the predetermined threshold, providing a notification signal indicating that a decompression event has occurred.

14. The method of claim 13, further comprising filtering the primary pressure signals that are outside a predetermined frequency band.

15. The method of claim 14, further comprising:

receiving a pressure signal corresponding to a pressure within a secondary compartment of the aircraft disposed adjacent to the first compartment;

determining a change in the secondary pressure signal;

determining whether the secondary pressure change meets a predetermined threshold;

if the secondary pressure change meets the predetermined threshold, providing a notification signal indicating that a decompression event has occurred.

16. The method of claim 15, further comprising filtering the secondary pressure signals that are outside a predetermined frequency band.

17. A system for monitoring pressure change within at least one compartment of an aircraft, comprising:

means for receiving a pressure signal corresponding to a pressure within a primary compartment of an aircraft;

means for filtering the primary pressure signals that are outside a predetermined frequency band;

means for determining a change in the primary pressure signal;

means for determining whether the primary pressure change meets a predetermined threshold; and

means for providing a notification signal indicating that a decompression event has occurred if the primary pressure change meets the predetermined threshold.

18. The system of claim 17, further comprising:

means for receiving a pressure signal corresponding to a pressure within a secondary compartment of the aircraft adjacent to the first compartment;

means for filtering the secondary pressure signals that are outside a predetermined frequency band;

means for determining a change in the secondary pressure signal;

means for determining whether the secondary pressure change meets a predetermined threshold;

means for providing a notification signal indicating that a decompression event has occurred if the secondary pressure change meets the predetermined threshold.