This application relates to an aircraft static port testing device in which a static leech may fixed to the static port of an aircraft. The static leech may be held in place by a suction cup surrounding the static port and the static port may be connected to an aircraft air data testing unit through a static port fitting. Vacuum may be created in the suction cup through a vacuum syringe or a vacuum pump.

This application relates to an aircraft static port testing device in which a static leech may fixed to the static port of an aircraft. The static leech may be held in place by a suction cup surrounding the static port and the static port may be connected to an aircraft air data testing unit through a static port fitting. Vacuum may be created in the suction cup through a vacuum syringe or a vacuum pump.

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.

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.

An aircraft probe includes a base, a strut that extends from the base, at least one port, and an electronics assembly insertable into the strut and removable from the strut. The electronics assembly includes at least one pressure sensor that is pneumatically connected to the at least one port to sense a first pressure when in the inserted position.

An aircraft probe includes a base, a strut that extends from the base, at least one port, and an electronics assembly insertable into the strut and removable from the strut. The electronics assembly includes at least one pressure sensor that is pneumatically connected to the at least one port to sense a first pressure when in the inserted position.

An aircraft probe includes a base, a strut that extends from the base, at least one port, and an electronics assembly insertable into the strut and removable from the strut. The electronics assembly includes at least one pressure sensor that is pneumatically connected to the at least one port to sense a first pressure when in the inserted position.

An aircraft probe includes a base, a strut that extends from the base, at least one port, and an electronics assembly insertable into the strut and removable from the strut. The electronics assembly includes at least one pressure sensor that is pneumatically connected to the at least one port to sense a first pressure when in the inserted position.

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.

[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.