A measurement unit for measuring a first static pressure of the ambient air in a first measurement zone of the aircraft, a measurement unit for measuring a second pressure of the ambient air, at least one static pressure probe, in a second measurement zone of the aircraft, the second pressure having a value lower than the first static pressure, a computation unit for estimating a Mach number using these two measured pressures and a data transmission unit configured to transmit the estimated Mach number to a user system.

A control system may generate a first simulated value for an aircraft sensor by applying one or more first input parameters to a sensor map model via a processor. The control system may compare the first simulated value and the first output of the aircraft sensor to determine a first calibration value and save calibration data in a memory based on the first calibration value. The control system may generate a calibrated simulation value of the aircraft sensor based on the sensor map model and the calibration data. The control system may determine validity of a second output of the aircraft sensor, utilize the second output of the aircraft sensor to perform an operation of the aircraft when the second output of the aircraft sensor is valid, and utilize the calibrated simulation value to perform the operation of the aircraft when the second output of the aircraft sensor is invalid.

A control system may generate a first simulated value for an aircraft sensor by applying one or more first input parameters to a sensor map model via a processor. The control system may compare the first simulated value and the first output of the aircraft sensor to determine a first calibration value and save calibration data in a memory based on the first calibration value. The control system may generate a calibrated simulation value of the aircraft sensor based on the sensor map model and the calibration data. The control system may determine validity of a second output of the aircraft sensor, utilize the second output of the aircraft sensor to perform an operation of the aircraft when the second output of the aircraft sensor is valid, and utilize the calibrated simulation value to perform the operation of the aircraft when the second output of the aircraft sensor is invalid.

A system may include a static air temperature probe attached to an aircraft, an electronic flight instrument system, and a processor. The processor may be configured to measure a static air temperature at the aircraft using the static air temperature probe. The processor may further be configured to calculate a Mach number associated with the aircraft based at least partially on the static air temperature. The processor may also be configured to calculate a true air speed of the aircraft based on the Mach number. The processor may display an indication of the true air speed using the electronic flight instrument system. The processor may also be configured to calculate the speed of sound based at least partially on the static air temperature.

A system may include a static air temperature probe attached to an aircraft, an electronic flight instrument system, and a processor. The processor may be configured to measure a static air temperature at the aircraft using the static air temperature probe. The processor may further be configured to calculate a Mach number associated with the aircraft based at least partially on the static air temperature. The processor may also be configured to calculate a true air speed of the aircraft based on the Mach number. The processor may display an indication of the true air speed using the electronic flight instrument system. The processor may also be configured to calculate the speed of sound based at least partially on the static air temperature.

[Object] To detect airspeed and an airflow direction with respect to an airframe of a motorized aircraft with high accuracy without increasing the cost and weight and rapidly control attitudes of an electric propulsion system and the airframe in accordance with fluctuations of the airspeed and airflow direction. [Solving Means] An electric propulsion system control device includes: a first airspeed measurement unit that is mounted on an airframe of an aircraft and includes a first propulsion system parameter detector that detects a propulsion system parameter, the propulsion system parameter being a parameter of an electric propulsion system, the electric propulsion system being driven by an electric motor and rotating about a rotation axis as a center, and a first airspeed calculator that calculates first airspeed on a basis of the propulsion system parameter, the first airspeed being airspeed with respect to a first direction that is a direction of the rotation axis; a second airspeed measurement unit that is mounted on the airframe and measures second airspeed, the second airspeed being airspeed with respect to a second direction different from the first direction; and an airflow calculator that calculates airspeed and airflow direction with respect to the airframe on a basis of the first direction and the first airspeed and the second direction and the second airspeed.

[Object] To detect airspeed and an airflow direction with respect to an airframe of a motorized aircraft with high accuracy without increasing the cost and weight and rapidly control attitudes of an electric propulsion system and the airframe in accordance with fluctuations of the airspeed and airflow direction. [Solving Means] An electric propulsion system control device includes: a first airspeed measurement unit that is mounted on an airframe of an aircraft and includes a first propulsion system parameter detector that detects a propulsion system parameter, the propulsion system parameter being a parameter of an electric propulsion system, the electric propulsion system being driven by an electric motor and rotating about a rotation axis as a center, and a first airspeed calculator that calculates first airspeed on a basis of the propulsion system parameter, the first airspeed being airspeed with respect to a first direction that is a direction of the rotation axis; a second airspeed measurement unit that is mounted on the airframe and measures second airspeed, the second airspeed being airspeed with respect to a second direction different from the first direction; and an airflow calculator that calculates airspeed and airflow direction with respect to the airframe on a basis of the first direction and the first airspeed and the second direction and the second airspeed.