Development of a computer based aircraft pitot-static instruments test system

This paper is focusing on designing of a pitot-static instruments test system for aircraft using a personal computer. Pitot-static pressure was acquired using data acquisition system then sent to the computer. Then the computer calculates the corresponding values of true airspeed, indicated airspeed, vertical speed, altitude, and Mach number according to mathematical models. These values are displayed in a graphical user interface program designed using Visual Basic program. In addition to that the designed software allows the user to carry out aircraft pitot-static pressure leakage test. The developed system had been applied to check the operation of the airspeed indicator of MI-17 as an example. From experiments the airspeed indicator average error about 0.005km/h and negligible at higher speeds. The altitude indicator average error about 0.47m and increase when the altitude is above 11 km. the true air speed indicator has an average error about 0.525km/h and increase at altitudes above 12km.