Air system for cabin pressurization

A system comprising:

• a turbine assembly including a turbine, the turbine assembly configured to establish a deployed configuration relative to an aircraft body of an aircraft and establish a stowed configuration relative to the aircraft body,
• wherein the turbine is configured to receive a ram air flow and produce a mechanical power using the ram air flow when the turbine assembly is in the deployed configuration, and
• wherein the turbine assembly is configured to limit a receipt of the ram air flow by the turbine when the turbine assembly is in the stowed configuration;
• a compressor configured to receive an air flow, wherein the compressor is configured to compress the air flow to provide a compressed air flow using a compressor power, wherein the compressor is configured to produce the compressor power using at least one of an electrical power provided by an electrical distribution system of the aircraft or the mechanical power produced by the turbine;
• and
• a clutching mechanism having an engaged configuration and a disengaged configuration,
• wherein the clutching mechanism is configured to limit a delivery of the mechanical power from the turbine to the compressor in the disengaged configuration and increase the delivery of the mechanical power from the turbine to the compressor in the engaged configuration,
• wherein the clutching mechanism is configured to transition from the disengaged configuration to the engaged configuration when the electrical power provided by the electrical distribution system decreases below a threshold,
• wherein the turbine assembly is configured to transition from the stowed configuration to the deployed configuration when the electrical power provided by the electrical distribution system decreases below the threshold, and
• wherein the system is configured to provide the compressed air flow to a compartment supported by the aircraft.

A method, comprising:

• compressing, by a compressor using electrical power from an electrical distribution system of an aircraft, an inlet air flow, wherein the compressor is configured to compress the inlet air flow using at least one of the electrical power or a mechanical power produced by a turbine assembly;
• and
• causing, when the electrical power decreases below a threshold, and by transitioning a clutching mechanism from a disengaged configuration to an engaged configuration, the compressor to compress the inlet air flow using the mechanical power,
• wherein the clutching mechanism is configured to limit a delivery of the mechanical power from the turbine assembly to the compressor in the disengaged configuration and increase the delivery of the mechanical power from the turbine assembly to the compressor in the engaged configuration.