Abstract: The present invention provides a cabin pressure control system that comprises a first outflow valve having a first motor controlled by a first outflow valve controller, the first outflow valve having a first backup motor controlled by a first backup controller. A second outflow valve has a second motor controlled by a second outflow valve controller, the second outflow valve also having a second backup motor controlled by a second backup controller. Upon failure of the first outflow valve controller, the second outflow valve controller controls the first outflow valve via the first backup controller and the first backup motor; and upon failure of the second outflow valve controller, the first outflow valve controller controls the second outflow valve via the second backup controller and the second backup motor.

Abstract: An aircraft cabin pressure control system implements control logic that significantly reduces potentially uncomfortable pressure bumps that can occur during aircraft take-off rotation both with and without cabin pressuring fluid flowing into the aircraft cabin. The control logic implemented by the cabin pressure control system, among other things, determines whether the cabin pressurizing fluid is flowing into the aircraft cabin. If the cabin pressurizing fluid is flowing into the aircraft cabin, aircraft cabin altitude is controlled to at least a first predetermined minimum altitude value below the take-off altitude. If the cabin pressurizing fluid is not flowing into the aircraft cabin, aircraft cabin altitude is controlled to at least a second predetermined minimum altitude value above the take-off altitude.

Abstract: The present invention provides a cabin pressure control system that comprises a first outflow valve having a first motor controlled by a first outflow valve controller, the first outflow valve having a first backup motor controlled by a first backup controller. A second outflow valve has a second motor controlled by a second outflow valve controller, the second outflow valve also having a second backup motor controlled by a second backup controller. Upon failure of the first outflow valve controller, the second outflow valve controller controls the first outflow valve via the first backup controller and the first backup motor; and upon failure of the second outflow valve controller, the first outflow valve controller controls the second outflow valve via the second backup controller and the second backup motor.

Abstract: An integrated cabin pressure control system valve that uses a dual, redundant channel electronic control unit for both control of the valve and to supply alarm, indication, and control signals to the aircraft's avionics system. Each channel in the electronic control unit includes an instrumentation and control circuit that uses multiple, dissimilar sensors and signals for warnings, indications, and controls. This configuration reduces the likelihood for a common mode failure that could result in a postulated gradual decompression without indication event.

Abstract: An integrated cabin pressure control system valve that uses a dual, redundant channel electronic control unit for both control of the valve and to supply alarm, indication, and control signals to the aircraft's avionics system. Each channel in the electronic control unit includes an instrumentation and control circuit that uses multiple, dissimilar sensors and signals for warnings, indications, and controls. This configuration reduces the likelihood for a common mode failure that could result in a postulated gradual decompression without indication event.