Abstract: An example system includes a common mode pneumatic event detector to detect a common mode pneumatic event at pitot tubes of an aircraft, a latch, a relay switch in communication with the latch, and a latch controller to set the latch in a first state to cause the latch to output a first latch signal, the relay switch to output a first pressure signal in response to the first latch signal, the first pressure signal based on pressure data from the pitot tubes, and set the latch in a second state to cause the latch to output a second latch signal based on the detection of the common mode pneumatic event. The relay switch is to output a second pressure signal in response to the second latch signal. The second pressure signal includes estimated pressure data.

Abstract: Example apparatus, systems, and methods for managing common mode pneumatic events are disclosed herein. An example system includes a common mode pneumatic event detector to detect a common mode pneumatic event at pitot tubes of an aircraft, a latch, a relay switch in communication with the latch, and a latch controller to set the latch in a first state to cause the latch to output a first latch signal, the relay switch to output a first pressure signal in response to the first latch signal, the first pressure signal based on pressure data from the pitot tubes, and set the latch in a second state to cause the latch to output a second latch signal based on the detection of the common mode pneumatic event. The relay switch is to output a second pressure signal in response to the second latch signal. The second pressure signal includes estimated pressure data.

Abstract: A flight control module for computing glideslope deviation during landing of an aircraft is provided. The flight control module includes a communication interface and a processor. The communication interface is configured to receive inertial data for the aircraft. The processor is coupled to the communication interface and configured to compute an inertial glideslope deviation based on the inertial data.

Abstract: A flight control module for computing localizer deviation during landing of an aircraft is provided. The flight control module includes a communication interface and a processor. The communication interface is configured to receive inertial data for the aircraft. The processor is coupled to the communication interface and is configured to compute an inertial localizer deviation based on the inertial data.

Abstract: A flight control module for computing localizer deviation during landing of an aircraft is provided. The flight control module includes a communication interface and a processor. The communication interface is configured to receive inertial data for the aircraft. The processor is coupled to the communication interface and is configured to compute an inertial localizer deviation based on the inertial data.

Abstract: A flight control module for computing localizer deviation during landing of an aircraft is provided. The flight control module includes a communication interface and a processor. The communication interface is configured to receive inertial data for the aircraft. The processor is coupled to the communication interface and is configured to compute an inertial localizer deviation based on the inertial data.

Abstract: A flight control module for computing glideslope deviation during landing of an aircraft is provided. The flight control module includes a communication interface and a processor. The communication interface is configured to receive inertial data for the aircraft. The processor is coupled to the communication interface and configured to compute an inertial glideslope deviation based on the inertial data.

Abstract: A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack.

Abstract: A signal selection and fault detection system is provided. The system includes four input equalization circuits each configured to receive an input signal from an associated sensor, wherein the input signal is indicative of a parameter measured by the associated sensor, and output an equalized signal based on the received input signal. The system further includes a five-input output selection circuit coupled to the four input equalization circuits, the five-input output selection circuit configured to receive an equalized signal from each of the four input equalization circuits, receive a previous frame output signal, and select an output signal from the four equalized signals and the previous frame output signal.

Abstract: A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack.

Abstract: A signal selection and fault detection system is provided. The system includes four input equalization circuits each configured to receive an input signal from an associated sensor, wherein the input signal is indicative of a parameter measured by the associated sensor, and output an equalized signal based on the received input signal. The system further includes a five-input output selection circuit coupled to the four input equalization circuits, the five-input output selection circuit configured to receive an equalized signal from each of the four input equalization circuits, receive a previous frame output signal, and select an output signal from the four equalized signals and the previous frame output signal.