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A Fluidically Controlled Aircraft Fuel Transfer System
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English
Abstract
Traditional methods of electrical sensing and control in jet aircraft fuel transfer systems have proven expensive, hard to maintain, and sometimes unreliable. This paper presents a new concept in fuel sensing and control using fluidics. The objective was to construct a general three-tank model system for exploring concept feasibility. Although a single medium (fuel) approach was sought, the interim model used a pneumatic logic and sensing system for fuel control. The laboratory model effectively demonstrated fuel level control, diversion of fuel transfer at the command of an automatic logic system, and pilot override. A trade study showed gains in reliability and maintainability over the current method of aircraft fuel transfer control. Advantages were: no dependence on electric or hydraulic power, ease of maintenance, and fail-safe operation.
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Citation
McGregor, R., "A Fluidically Controlled Aircraft Fuel Transfer System," SAE Technical Paper 700786, 1970, https://doi.org/10.4271/700786.Also In
References
- Kelley L. R. Boothe W. A. “Hydraulic Fluidics.” Paper No. 68-WA/FE-26 presented at the ASME Winter Annual Meeting and Energy Systems Exposition New York August 1968
- Cisco R. L. “Level Sensor Characteristics and Uses.” Report No. F61R0139 Parker Aircraft Company Los Angeles November 1962
- Adams R. B. “Application of Fluidic Valves.” Moore Products Company Technical Paper 992, presented at the ASME Winter Annual Meeting Chicago November 1965
- Hollis C. P. “Trade Study Report - Fluidics vs. Electrical Logic and Control of Aircraft Fuel Transfer Systems (Preliminary).” LTV Vought Aeronautics Report Dallas December 1969