The measurement of the static pressure is required on board of aircrafts for the evaluation
of altitude, vertical speed, speed, and Mach number. On the series aircraft,
the static pressure is measured through a port in the aircraft fuselage.
Several methods are available for the flight test calibration of the pressure measured
through such a static port. These methods are described and evaluated for an application
in civil flight test programs of transport category aircrafts. Different evaluation criteria
are considered. The achievable accuracy of the calibration methods is one evaluation criterion
of high importance. The applicable standards (FAR, JAR, ICAO) are discussed.
Based on these standards, the acceptable error of the calibration methods are determined.
For flight test calibration methods performed directly on the aircraft, the achievable accuracy
depends on the position where measurements are taken. Possible measurement positions are e.g.
in front of the aircraft nose, on the wing tip, or at the fin. The flow at each of these positions
shows a different rate of disturbance by the aircraft itself. Flow disturbance rates are
calculated in this thesis based on aerodynamic data predicted for the Airbus A3XX.
The evaluation finally identifies a laser-based system offered by Kayser Threde
as the most promising candidate for the calibration of the pressure measured through
the static port.
