Fluidic flight control system has been flight tested to develop and evaluate vortex rate sensors, fluidic amplifiers, dynamic shaping techniques and system accuracy; results which have confirmed applicability of conventional control theory and projected high reliability; stabilization system featuring electropneumatic servo actuator with variable transfer function and unique characteristics for application to range of stabilization problems; recent electronic system studies have been 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 -- Paper
SAE Meeting ; 1967 Control equipment
1967
11 pages
Conference paper
English
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Automatic Flight Control Development for General Aviation
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