Abstract: A system includes a venturi duct, a first delta P sensor, a second delta P sensor, and an ECS controller. The venturi duct is configured to receive a first bleed air flow or a second bleed air flow. The first and second delta P sensors are configured to sense a first and second pressure difference between a first point and a second point of the venturi duct. The first and second delta P sensors are configured to sense pressure difference over different pressure ranges. The ECS controller is configured determine a flow rate of an ECS air flow based upon the first pressure and/or second sensed pressure differences.

Abstract: A system includes a venturi duct, a first delta P sensor, a second delta P sensor, and an ECS controller. The venturi duct is configured to receive a first bleed air flow or a second bleed air flow. The first and second delta P sensors are configured to sense a first and second pressure difference between a first point and a second point of the venturi duct. The first and second delta P sensors are configured to sense pressure difference over different pressure ranges. The ECS controller is configured determine a flow rate of an ECS air flow based upon the first pressure and/or second sensed pressure differences.

Abstract: A fuel and bleed controller is provided. The fuel and bleed controller includes a processor and a memory. The memory stores program instructions thereon. The program instructions are executable by the processor to cause the fuel and bleed controller to send status requests to systems of the aircraft. The systems comprise a bleed system and bleed user controllers. The program instructions are further executable by the processor to cause the fuel and bleed controller to receive status responses from the systems of the aircraft and determine fuel requirements based on the status responses in advance of operational needs by the systems of the aircraft. The program instructions are further executable by the processor to cause the fuel and bleed controller to control engines of the aircraft based on the fuel requirements.

Abstract: An electronic expansion valve (EEV) is employed in refrigeration systems to regulate the flow of refrigerant through an evaporator. The position of the EEV is controlled through a first control loop that generates a first position signal based on superheat feedback associated with the refrigeration system, and a second control loop that generates a second position signal based on pressure feedback associated with the refrigeration system. The larger of the first position signal and the second position signal is selected to control the position of the EEV value, and the selected position signal is provided in feedback to both the first control loop and the second control loop.

Abstract: A fuel and bleed controller is provided. The fuel and bleed controller includes a processor and a memory. The memory stores program instructions thereon. The program instructions are executable by the processor to cause the fuel and bleed controller to send status requests to systems of the aircraft. The systems comprise a bleed system and bleed user controllers. The program instructions are further executable by the processor to cause the fuel and bleed controller to receive status responses from the systems of the aircraft and determine fuel requirements based on the status responses in advance of operational needs by the systems of the aircraft. The program instructions are further executable by the processor to cause the fuel and bleed controller to control engines of the aircraft based on the fuel requirements.

Abstract: A method and system providing an airflow to a wing anti-ice system includes receiving an airflow from an outside air supply, compressing the airflow via an electric compressor, controlling a temperature of the airflow from the electric air compressor via a heat exchanger in fluid communication with the electric compressor and the wing anti-ice system, and providing the airflow to the wing anti-ice system via the heat exchanger.

Abstract: A method and system providing an airflow to a wing anti-ice system includes receiving an airflow from an outside air supply, compressing the airflow via an electric compressor, controlling a temperature of the airflow from the electric air compressor via a heat exchanger in fluid communication with the electric compressor and the wing anti-ice system, and providing the airflow to the wing anti-ice system via the heat exchanger.

Abstract: In one example, a system includes a component of an air management system of an aircraft and an active history memory module attached to the component. The active history memory module includes interface circuitry configured to receive data corresponding to one or more operational parameters of the aircraft. The active history memory module further includes computer-readable memory operably connected to the interface circuitry and configured to store the data corresponding to the one or more operational parameters.

Abstract: An electronic expansion valve (EEV) is employed in refrigeration systems to regulate the flow of refrigerant through an evaporator. The position of the EEV is controlled through a first control loop that generates a first position signal based on superheat feedback associated with the refrigeration system, and a second control loop that generates a second position signal based on pressure feedback associated with the refrigeration system. The larger of the first position signal and the second position signal is selected to control the position of the EEV value, and the selected position signal is provided in feedback to both the first control loop and the second control loop.

Abstract: A method of controlling a vapor cycle system having first and second compressors includes operating the first compressor to compress refrigerant while the second compressor is idle, sensing a motor temperature of the second compressor, activating a preheating mode in which the motor of the second compressor is powered to generate heat when the motor temperature of the second compressor is below a lower temperature threshold, turning off the preheating mode when the sensed motor temperature of the second compressor is above an upper temperature threshold, and limiting the maximum duration of the preheating mode to a preheating time period, such that the preheating mode is turned off after being activated for the preheating time period.