Patent ID: 9180959
Filing Date: 2015-11-10
Classification: B64C,B64D

Abstract:
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 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: 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.