Results are presented of flight tests conducted to evaluate a three-axis mechanical stability augmentation system (MSAS), known as 'Dynagyro', on a UH-1 helicopter. The purpose of a stability augmentation system is to augment the stability and control characteristics of unstable or weakly stable aircraft so as to provide satisfactory flying qualities. The tests encompassed 9-1/2 flight hours and approximately 3 hours of ground and hangar testing. The MSAS included an entirely new concept: vortex valve fluidic servoactuators. The magnitude of the installation and conversion procedure for installing the MSAS, was relatively small. The MSAS, as tested, did not perform as well in the helicopter as it did in the laboratory or as well as theory indicated it should. (Author)
Flight Test Evaluation of the Three-Axis Mechanical Stability Augmentation System
1970
114 pages
Report
Keine Angabe
Englisch
Aircraft , Flight control systems , Helicopters , Stabilization systems , Flight testing , Fluidics , Valves , Vortices , Aerodynamic characteristics , Servomechanisms , Performance(Engineering) , Acceptability , Stability augmentation systems , H-1 aircraft , Sas(Stability augmentation systems) , Uh-1 aircraft
Three-Axis Fluidic Stability Augmentation System
NTIS | 1971
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