Abstract: A method for heating an unpressurized aircraft includes receiving a desired air temperature, calculating a target duct air temperature based on the desired air temperature, determining an actual duct air temperature via a duct air temperature sensor, calculating a target modulation of one or more ram air valves based on a difference between the target duct air temperature and the actual duct air temperature, modulating one or more of the ram air valves based on the target modulation, introducing a bleed air from a turbine engine to a heat exchanger, introducing a temperature control air from one of the one or more ram air valves to the heat exchanger for cooling the bleed air to provide a temperature-controlled air, mixing the temperature-controlled air from the heat exchanger with an ejector ram air in an ejector, and providing air from the ejector to an occupied compartment of the unpressurized aircraft.

Abstract: A remote sensor data acquisition system for an aircraft includes a plurality of remote sensors co-located onboard the aircraft and adapted to measure one or more aircraft-related parameters. A remote sensor interface is co-located with the plurality of remote sensors. The remote sensor interface includes a communication bus having a plurality of nodes to transmit data from the plurality of remote sensors. A plurality of subsystems are each adapted to receive data from the plurality of remote sensors simultaneously and in real time via the remote sensor interface. A remote sensor data acquisition method for an aircraft includes sensing one or more parameters onboard the aircraft via a plurality of remote sensors and transmitting sensor data from the plurality of remote sensors to a plurality of subsystems independently and in real time via a remote sensor interface.

Abstract: A remote sensor data acquisition system for an aircraft includes a plurality of remote sensors co-located onboard the aircraft and adapted to measure one or more aircraft-related parameters. A remote sensor interface is co-located with the plurality of remote sensors. The remote sensor interface includes a communication bus having a plurality of nodes to transmit data from the plurality of remote sensors. A plurality of subsystems are each adapted to receive data from the plurality of remote sensors simultaneously and in real time via the remote sensor interface. A remote sensor data acquisition method for an aircraft includes sensing one or more parameters onboard the aircraft via a plurality of remote sensors and transmitting sensor data from the plurality of remote sensors to a plurality of subsystems independently and in real time via a remote sensor interface.

Abstract: A conditional switched rate filter system having a two stage digital filter to remove noise from the input signal. The first stage of the filter effectively removes the random noise from the input signal higher in frequency (cut-off frequency) than outside the characteristic response of the closed loop system. The second stage of the filter is used to filter out noise that is at same frequency response as the closed loop system.

Abstract: A liquid based ice protection test system for testing an aircraft part having a first heating element comprises a tub configured for retaining a low temperature bath. The system also includes a first support member for suspending the aircraft part in the tub and a first temperature sensing device for sensing temperatures from one or more locations of a skin of the aircraft part.

Abstract: A liquid based ice protection test system for testing an aircraft part having a first heating element comprises a tub configured for retaining a low temperature bath. The system also includes a first support member for suspending the aircraft part in the tub and a first temperature sensing device for sensing temperatures from one or more locations of a skin of the aircraft part.

Abstract: A liquid based ice protection test method tests an aircraft part that includes at least a first heating element mounted on an inside surface of an aircraft skin. The method includes bringing the aircraft skin into contact with a low temperature bath and taking one or more temperature readings of the aircraft skin. A liquid based deicing test system includes a container that holds a low temperature bath, a fixture to suspend the aircraft part within the container, and a temperature sensing device for reading temperatures on an outside surface of the aircraft part. A liquid based ice protection test method includes sealing off ends of an aircraft part, attaching at least one temperature sensing device on the aircraft part and at least partially submerging it in a low temperature bath, and obtaining temperature information from the temperature sensing device.

Abstract: A liquid based ice protection test method tests an aircraft part that includes at least a first heating element mounted on an inside surface of an aircraft skin. The method includes bringing the aircraft skin into contact with a low temperature bath and taking one or more temperature readings of the aircraft skin. A liquid based deicing test system includes a container that holds a low temperature bath, a fixture to suspend the aircraft part within the container, and a temperature sensing device for reading temperatures on an outside surface of the aircraft part. A liquid based ice protection test method includes sealing off ends of an aircraft part, attaching at least one temperature sensing device on the aircraft part and at least partially submerging it in a low temperature bath, and obtaining temperature information from the temperature sensing device.