This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Automatic Flight Control Development for General Aviation
Annotation ability available
Sector:
Language:
English
Abstract
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.
Recommended Content
| Aerospace Standard | Flight Control Actuators - Dynamic Seals, Collection of Duty Cycle Data |
| Technical Paper | An Acoustic-Based Wiring Diagnostic System for Aircraft |
| Technical Paper | Evolution of an Optical Control System for Aircraft Hydraulics |
Authors
Topic
Citation
Vetter, L., "Automatic Flight Control Development for General Aviation," SAE Technical Paper 670255, 1967, https://doi.org/10.4271/670255.Also In
References
- Frudenfeld K. “Changing Concepts of Automatic Flight,” presented at SAE Business Aircraft Conference Wichita, Kan. 1966
- Driscoll N. R. “The Effect of a Light Aircraft Stability Augmentation System on Pilot Performance,” presented at SAE Business Aircraft Conference Wichita, Kan. 1966
- Lock W. P. Gee S. W. Rodgers D. L. “Design, Development and Flight Testing of a Pure Fluid Autopilot,” presented at SAE Committee A-6 Symposium on Fluidics San Francisco Oct. 21 1966
- Evans R. A. “Applied Fluids Technology,” presented at SAE-NASA Aerospace Vehicle Flight Control Conference P6
- Fosdick G. W. U. S. Army Aviation Materiel Labs R. V. Burton, Honeywell Inc., Aero Div. “A Hydraulic Fluidic Stability Augmentation System for Helicopters.”
- Special Report “Fluid Power and Control” Product Engineering Feb. 13 1967
- Schmidlin A. E. “Pneumatic Systems for Flight at Mach 3,” TNB, General Precision Aerospace V6 4th Quarter 1963
- Moore J. R. Ashby, R. M. Ph. D. “Microelectronics for Future Commerical Aircraft,” North American Aviation/Autonetics Feb. 7 1964
- Kobe C. M. “Microelectronic Flight Controls at Honeywell,” Paper No. T-145, presented at SAE A-18F Meeting No. 17 Aerospace Vehicle Flight Control Systems New Orleans, La. Jan. 19-21 1966