The flight test system described combines state-of-the-art microprocessor technology and high accuracy instrumentation with parameter identification technology which minimize data and flight time requirements. The system was designed to avoid permanent modifications of the test airplane and allow quick installation. It is capable of longitudinal and lateral-directional stability and control derivative estimation. Details of this system, calibration and flight test procedures, and the results of the Cessna 172 flight test program are presented. The system proved easy to install, simple to operate, and capable of accurate estimation of stability and control parameters in the Cessna 172 flight tests.
Development of a Simple, Self-Contained Flight Test Data Acquisition System
1982
250 pages
Report
No indication
English
Aircraft , Avionics , Airborne/spaceborne computers , Attitude stability , Cessna 172 aircraft , Data acquisition , Accelerometers , Aerodynamic stability , Attitude control , Computer programs , Computer techniques , Data processing , Equipment specifications , Flight tests , Flight time , Gyroscopes , Microprocessors , Onboard equipment , Parameterization
Development of a Simple, Self-Contained Flight Test Data Acquisition System
SAE Technical Papers | 1981
|