In order to reduce the large amount of flight hours necessary for the determination of performance data of an aircraft, a method has been developed to extract these data from a single dynamic flight maneuver. The paper gives a description of the instrumentation on board of the proto type of a twin turbofan medium size aircraft, which was used for a short test program in order to evaluate the applicability of the method for such type of aircraft. The instrumentation consists of a strap.down inertial system, an accurate measurement system and a measurement system for the settings of the aircrafts control surfaces. The data are acquired and stored on magnetic tape by a computer controlled data acquisition system, which also controls the sensor systems.
Paper presented at the 25th International Instrumentation Symposium, organized by Aerospace Industries Division and Test Measurement Division of the Instrument Society of America (Anaheim, Gal. USA, May 7-10, 1979).