A fluidic flight control system has been flight tested to develop and evaluate vortex rate sensors, fluidic amplifiers, dynamic shaping techniques, and system accuracy. Discussed are results which have confirmed applicability of conventional control theory and projected high reliability. Also discussed is a stabilization system featuring an electropneumatic servo actuator with variable transfer function and unique characteristics for application to a range of stabilization problems. Recent electronic system studies have shown substantial improvement in reliability, maintainability, size, weight, and cost reduction by use of microelectronic functional modules as alternates to individually-mounted discrete components.
Automatic Flight Control Development for General Aviation
Sae Technical Papers
3rd Annual Business Aircraft Conference (1967) ; 1967
1967-02-01
Aufsatz (Konferenz)
Englisch
Development of an Automatic Flight Path Controller for a DA42 General Aviation Aircraft
Springer Verlag | 2017
|Changes in General Aviation Flight Operations
British Library Conference Proceedings | 2003
|Composites Taking Flight in General Aviation
British Library Conference Proceedings | 2006
|