An instrumentation system for flight tests in nonsteady flight is described. The system comprises several high accuracy transducers and a high quality data logging system. The flight test method applied is based on deduction of aircraft performance as well as stability and control characteristics from measurements obtained during a nominally symmetric nonsteady maneuver. The maneuver is characterized by a nearly constant acceleration of the aircraft from low to high speed in a time interval of about 200 seconds. At more or less equal time intervals the aircraft is forced to oscillate about the lateral axis by manually controlled oscillations of the elevator. Stability and control characteristics are derived from measurements obtained during the aircraft's oscillations. Aircraft performance and the polar drag curve are determined from the quasi-stationary parts between the oscillations. (Author)
Advanced Flight Test Instrumentation: Design and Calibration
1974
18 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft performance , Calibrating , Kalman-schmidt filtering , Onboard equipment , Performance tests , Accelerometers , Aircraft control , Aircraft stability , Data reduction , Flight tests , Oscillations , Positioning , Pressure sensors , Temperature measuring instruments , Thrust measurement
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