Rapid decompression detection system and method

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;

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;

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

respective symmetry checkers configured to determine whether the decompression event is valid, the symmetry checkers associated with each of the primary and secondary monitoring channels, the symmetry checkers each receiving an input from a respective symmetry band pass filter, and the symmetry checkers outputting a signal to the threshold logic circuit,

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 indicating a health condition exists in one of the primary or secondary pressure sensors, and fault detection reporting circuits for reporting that a health condition exists.

2. The system of claim 1 , wherein each of the fault detection comparison circuits monitor respective band pass filter signals, pressure change signals, and symmetry checker signals.

3. The system of claim 1 , 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.

4. The system of claim 3 , wherein the pressure sensor amplifier is coupled to a positive and a negative voltage supply.

5. The system of claim 3 , 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.

6. The system of claim 3 , wherein each of the primary and secondary pressure monitoring channels includes a DC coupling circuit disposed within the band pass filter.

7. The system of claim 3 , wherein each of the primary and secondary band pass filters includes a voltage divider for adjusting the gain of the filter.

8. The system of claim 3 , 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.

9. The system of claim 1 , 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.

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

receiving a pressure signal into a primary pressure sensor 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;

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

receiving a pressure signal into a secondary pressure sensor 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;

determining whether the decompression event is valid utilizing respective symmetry checkers, the symmetry checkers associated with each of the primary pressure signal and secondary pressure signal, the symmetry checkers each receiving an input from a respective symmetry band pass filter, and the symmetry checkers outputting a signal indicating validity,

comparing the primary and secondary pressure sensor signals to known values, or to each other, to determine whether an input error occurs indicating a health condition exists in one of the primary or secondary pressure sensors; and

reporting that a health condition exists via a fault detection reporting circuit.

11. The method of claim 10 , further comprising filtering the primary pressure signals that are outside a predetermined frequency band.

12. The method of claim 11 , further comprising filtering the secondary pressure signals that are outside a predetermined frequency band.

13. 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;

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

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;

means for determining whether the decompression event is valid comprising respective symmetry checkers, the symmetry checkers associated with each of the primary pressure signal and secondary pressure signal, the symmetry checkers each receiving an input from a respective symmetry band pass filter, and the symmetry checkers outputting a signal indicating validity; and

means for comparing the primary and secondary pressure sensor signals to known values, or to each other, to determine whether an input error occurs indicating a health condition exists in one of the primary or secondary pressure sensors; and

means for reporting that a health condition exists.