An environmental control system of an aircraft includes a ram air input configured to receive ram air from a ram air duct of the aircraft and an electric motor driven compressor system. The system also includes a RAM heat exchanger and an ejector connected to the output of the RAM heat exchanger that is fluidly connected to the output of a compressor in the compressor system and that causes ram air received at the cooling flow input to be drawn through the RAM heat exchanger.

An aircraft humidification system includes a first duct configured to guide a first air stream, and a second duct configured to guide a second air stream, the second duct including a humidifier for humidifying the air stream in the second duct. A first conduit directs part of the second air stream to the first duct. The first conduit includes a first conduit inlet leading into the first duct and a first conduit outlet extending from the second duct. A second conduit directs part of the first air stream to the second duct, the second conduit including a second conduit inlet leading into the second duct and a second conduit outlet extending from the first duct. The first conduit outlet is arranged downstream of the humidifier, the second conduit inlet is arranged downstream of the first conduit outlet and the first conduit inlet is arranged downstream of the second conduit outlet.

The system includes a computer server receiving data representative of the temperature of the cabin and including a database containing, for the aircraft, a predetermined cycle of regulation of the temperature of the air of the cabin; a ground pre-conditioned air unit including: a pre-conditioned air generator and a control module; and a user interface connected to the computer server and transmitting a control signal to the control module; and the control module, upon receiving the control signal, controlling the pre-conditioned air generator, according to the predetermined cycle, which is modulated depending on the data. This system makes it possible to control the temperature of the cabin in real time, so as to correctly disinfect it.

A variable chiller exhaust system incorporate a plurality of chillers, each chiller having an inlet receiving air from a crown in an aircraft fuselage and an outlet connected to a manifold. A plurality of check valves are connected to the manifold and configured to maintain a differential back pressure on the plurality of chillers of 2″ water pressure or less. The check valves vent into the crown. An exhaust conduit is connected to direct air from the manifold to a variable speed fan. An outflow valve exhausts air from the variable speed fan to an exterior of the fuselage.

An example thermal management system may include a first heat exchanger including a bleed air inlet configured to receive input bleed air from a gas turbine engine and a bleed air outlet configured to output cooled bleed air. A turbine including a turbine inlet may be fluidically coupled to the bleed air outlet. The turbine may be configured to drive a shaft mechanically coupled to the turbine in response to expansion of the cooled bleed air through the turbine. A second heat exchanger may include an expanded bleed air inlet fluidically coupled to a turbine outlet of the turbine. The second heat exchanger may be configured to extract heat from at least one heat source using the expanded bleed air.

An environmental control system of a vehicle includes an inlet configured to receive a medium, a compression device fluidly connected to the inlet, and at least one heat exchanger fluidly connected to the compression device. A secondary fluid system is thermally coupled to the environmental control system. The secondary fluid system has a closed loop configuration through which a secondary fluid circulates. The secondary fluid system includes an evaporator and a condenser. The evaporator has an evaporator outlet fluidly connected to and configured to receive the medium output from an outlet of the heat exchanger outlet and the condenser is connected to the evaporator outlet. The condenser is fluidly connected to and receives the medium output from the evaporator.

An environmental control system of a vehicle includes an inlet configured to receive a medium, a heat exchanger fluidly connected to the inlet to receive the medium, and a ram air circuit including another inlet configured to receive ram air and including a ram air heat exchanger. A closed secondary fluid loop is operably coupled to the heat exchanger and to the ram air heat exchanger. The secondary fluid loop has a secondary fluid circulating therein that removes heat from the medium in the heat exchanger and that discharges heat to the ram air in the ram air heat exchanger.

Systems and methods are described herein that utilize a decentralized control panel architecture to monitor or control components or (sub-)systems of an aircraft or other vehicle. A controller can be used to receive information from multiple input sources and send a command to one or more output devices based on the received information. The received information may be of different types or formats that can be read by the controller. The controller may cause a visual or physical change to an actuator based on the command. One or more control panel entities can be communicatively coupled with the controller and used to access information about one or more (sub-)systems of the vehicle and send commands where appropriate.

An electric temperature control system for unpressurized aircraft and methods for operating are disclosed. The electric temperature control system may be electrically powered and used on all-electric aircraft or hybrid aircraft. The electric temperature control system may comprise a vapor cycle cooling system for cooling air and an electric heater for heating air. The electric heater may be a PTC electric heater with individually-controllable heating elements. Various input devices may be disposed in the aircraft allowing an operator to set a compartment temperature, an air source, and a fan speed. A controller controls operations of the electric temperature control system based on feedback received from a plurality of feedback devices and the operator inputs.

A method of operating an environmental control system of an aircraft includes providing a first medium to the environmental control system including a compressor and a turbine, wherein the first medium is provided to the compressor and the turbine sequentially and extracting work from a second medium provided to a power turbine operably coupled to the compressor to drive the compressor. In a first mode of operation, the first medium to be provided to a downstream load is output from the turbine, in a second mode of operation, at least a portion of the first medium to be provided to a downstream load bypasses the turbine, and in a third mode of operation, at least a portion of the first medium output from the compressor is provided to the power turbine.