A pneumatic flow-control system and method for an aircraft provide efficient mixing of high-pressure engine bleed air with one or both of low-pressure engine bleed air and ambient air. A controller determines an amount of high- and low-pressure air and ambient air to provide based on ambient air temperature and pressure and a flow rate and temperature of the mixed air for improving engine performance during different phases of flight and for reducing a burden on an environmental control subsystem of the aircraft.

A pneumatic flow-control system and method for an aircraft provide efficient mixing of high-pressure engine bleed air with one or both of low-pressure engine bleed air and ambient air. A controller determines an amount of high- and low-pressure air and ambient air to provide based on ambient air temperature and pressure and a flow rate and temperature of the mixed air for improving engine performance during different phases of flight and for reducing a burden on an environmental control subsystem of the aircraft.

A control system for an aircraft system can include a controller configured to connect to one or more subsystems of the aircraft system, the controller having a built-in-test (BIT) module configured to test the one or more subsystems of the aircraft system and output test data. The control system can include a wireless communication module operatively connected to the controller and configured to receive the output data and to output a wireless signal as a function of the test data.

A cockpit pressurization and oxygen warning system includes a cabin pressure input and an aircraft pressure input. A pilot interface includes a first visual indicator having a first recognizable characteristic disposed in a first position that is made visually perceptible when a first signal is asserted and a second visual indicator having a second recognizable characteristic esthetically different from the first recognizable characteristic and disposed in a second position different from the first position that is made visually perceptible when a second signal is asserted. A control circuit that is responsive to the cabin pressure input and the aircraft pressure input determines an acceptable range for the cabin altitude that corresponds to the aircraft altitude. The control circuit asserts the first signal when the cabin altitude is within the acceptable range and asserts the second signal when the cabin altitude is not within the acceptable range.

In some examples, a cabin pressure control and monitoring system includes an outflow valve and a manual control panel comprising a selector switch and configured to generate a signal, wherein a value encoded in the signal is dependent on a position of the selector switch. The cabin pressure control and monitoring system also includes a controller configured to receive the signal from the manual control panel, determine a target rate of change for a cabin pressure based on the value encoded in the signal, and control the outflow valve based on the target rate of change.

In some examples, a cabin pressure control and monitoring system includes an outflow valve and a manual control panel comprising a selector switch and configured to generate a signal, wherein a value encoded in the signal is dependent on a position of the selector switch. The cabin pressure control and monitoring system also includes a controller configured to receive the signal from the manual control panel, determine a target rate of change for a cabin pressure based on the value encoded in the signal, and control the outflow valve based on the target rate of change.

An aircraft air distribution assembly providing integrated personally controllable air flow and cabin air flow is presented. The aircraft air distribution assembly comprises a plenum and a flow restriction system. The plenum is connected to a plurality of personal air outlets configured to provide the personally controllable air flow. The flow restriction system extends through at least one wall of the plenum, the flow restriction system configured to set a pressure for the cabin air flow.

An aircraft air distribution assembly providing integrated personally controllable air flow and cabin air flow is presented. The aircraft air distribution assembly comprises a plenum and a flow restriction system. The plenum is connected to a plurality of personal air outlets configured to provide the personally controllable air flow. The flow restriction system extends through at least one wall of the plenum, the flow restriction system configured to set a pressure for the cabin air flow.

This disclosure describes an on-board oxygen generating system (OBOGS) using open loop control. An example OBOGS includes a concentrator comprising at least two beds and a controller. Each bed has a valve to pneumatically couple the bed between a supply gas source and a vent; The controller receives at least one input signal from at least one sensor aboard an aircraft, and determines a predicted oxygen concentration output from the at least two beds into the based on the received input signals. The controller controls the valves of the at least two beds based on the determined predicted oxygen concentration to adjust charge/vent ratios of the at least two beds.

This disclosure describes an on-board oxygen generating system (OBOGS) using open loop control. An example OBOGS includes a concentrator comprising at least two beds and a controller. Each bed has a valve to pneumatically couple the bed between a supply gas source and a vent; The controller receives at least one input signal from at least one sensor aboard an aircraft, and determines a predicted oxygen concentration output from the at least two beds into the based on the received input signals. The controller controls the valves of the at least two beds based on the determined predicted oxygen concentration to adjust charge/vent ratios of the at least two beds.