Abstract: An air data system with a digital interface includes least one air data component, a receiving system and at least one digital connection. The at least one digital connection is between the receiving system and the air data component. A method for transmitting data in an air data system with a digital interface includes measuring at least one air data parameter with at least one air data component. The method includes generating a digital signal representative of the at least one air data parameter with the at least one air data component, sending the digital signal to a receiving system, and processing the at least one air data parameter with the receiving system.

Abstract: A aircraft health management system for identifying an anomalous signal from one or more air data systems (ADS) includes one or more of a frequency processor, configured to provide a spectral signal that is representative of a frequency content of the first ADS signal, a noise processor, configured to provide a noise signal that is representative of a noise level of the first ADS signal, and a rate processor, configured to provide a rate signal that is representative of a rate of change of the first ADS signal. The aircraft health management system also includes a comparator configured to provide a differential signal between the first ADS signal and the second ADS signal, and a prognostic processor configured to determine if the ADS signal is anomalous by comparing values representative of a flight condition signal, the differential signal, and the spectral, noise, and/or rate signals.

Abstract: A system includes a heating element, a signal injector, and a signal receiver. The heating element is coupled between a first node and a second node. The signal injector is communicatively coupled the heating element via the first node. The signal generator is configured to provide a test signal to the heating element. The signal receiver is communicatively coupled to the heating element via the second node. The signal receiver is configured to receive the test signal from the heating element and to determine a capacitance of the heating element based upon the received test signal.

Abstract: An air data system for an aircraft includes a multi-function probe (MFP) and an inertial reference unit (IRU). The MFP is positioned to sense a pressure of airflow about an exterior of the aircraft. A first electronics channel of the MFP is electrically coupled to the IRU to generate air data parameter outputs based on the pressure sensed by the MFP and inertial data sensed by the IRU.

Abstract: A system and method of augmenting an existing air data system includes a multi-function probe (MFP) having a portion extending into an oncoming airflow about an exterior of an aircraft. A plurality of pressure sensing ports in the portion includes at least first and second static pressure ports. A first electronics channel of the MFP includes pressure sensors communicating with the first and second static pressure ports and is configured to determine first and second altitude values based on sensed static pressures at the first and second static pressure ports, respectively, that are independent of the existing air data system.

Abstract: A system includes an air data computer (ADC) having a single pneumatic port for receiving a pneumatic input, a plurality of electrical inputs for receiving one or more electrical signals, and an output. The ADC can transmit, via the output, air data parameters based on the received pneumatic input and the received one or more electrical signals. In a further example embodiment, the system includes a first pressure sensing probe discrete from the ADC and a pneumatic connection joining a pressure sensing port of the first probe to the pneumatic input of the ADC. Second and third pressure sensing probes pneumatically coupled to respective pressure modules, which output electrical signals to the ADC, the electrical signals being representative of pressures sensed by the second and third pressure sensing probes, respectively.

Abstract: A aircraft health management system for identifying an anomalous signal from one or more air data systems (ADS) includes one or more of a frequency processor, configured to provide a spectral signal that is representative of a frequency content of the first ADS signal, a noise processor, configured to provide a noise signal that is representative of a noise level of the first ADS signal, and a rate processor, configured to provide a rate signal that is representative of a rate of change of the first ADS signal. The aircraft health management system also includes a comparator configured to provide a differential signal between the first ADS signal and the second ADS signal, and a prognostic processor configured to determine if the ADS signal is anomalous by comparing values representative of a flight condition signal, the differential signal, and the spectral, noise, and/or rate signals.

Abstract: An air data system with a digital interface includes least one air data component, a receiving system and at least one digital connection. The at least one digital connection is between the receiving system and the air data component. A method for transmitting data in an air data system with a digital interface includes measuring at least one air data parameter with at least one air data component. The method includes generating a digital signal representative of the at least one air data parameter with the at least one air data component, sending the digital signal to a receiving system, and processing the at least one air data parameter with the receiving system.

Abstract: A system includes a heating element, a signal injector, and a signal receiver. The heating element is coupled between a first node and a second node. The signal injector is communicatively coupled the heating element via the first node. The signal generator is configured to provide a test signal to the heating element. The signal receiver is communicatively coupled to the heating element via the second node. The signal receiver is configured to receive the test signal from the heating element and to determine a capacitance of the heating element based upon the received test signal.

Abstract: A system and method of augmenting an existing air data system includes a multi-function probe (MFP) having a portion extending into an oncoming airflow about an exterior of an aircraft. A plurality of pressure sensing ports in the portion includes at least first and second static pressure ports. A first electronics channel of the MFP includes pressure sensors communicating with the first and second static pressure ports and is configured to determine first and second altitude values based on sensed static pressures at the first and second static pressure ports, respectively, that are independent of the existing air data system.

Abstract: A system includes an air data computer (ADC) having a single pneumatic port for receiving a pneumatic input, a plurality of electrical inputs for receiving one or more electrical signals, and an output. The ADC can transmit, via the output, air data parameters based on the received pneumatic input and the received one or more electrical signals. In a further example embodiment, the system includes a first pressure sensing probe discrete from the ADC and a pneumatic connection joining a pressure sensing port of the first probe to the pneumatic input of the ADC. Second and third pressure sensing probes pneumatically coupled to respective pressure modules, which output electrical signals to the ADC, the electrical signals being representative of pressures sensed by the second and third pressure sensing probes, respectively.

Abstract: An air data system for an aircraft includes a multi-function probe (MFP) and an inertial reference unit (IRU). The MFP is positioned to sense a pressure of airflow about an exterior of the aircraft. A first electronics channel of the MFP is electrically coupled to the IRU to generate air data parameter outputs based on the pressure sensed by the MFP and inertial data sensed by the IRU.