Abstract
A personal computer (PC) based generic developmental fuel control system for expendable turbojet engines has been developed and demonstrated. This system provides a means of experimentall y evaluating the engine hardware, fuel metering devices, control sensors, and control logic of turbojet missile propulsion systems independently Of installation in the flight vehicle. The system is generic in nature to permit the evaluation of a variety of engine models (from various manufacturers), metering devices, and control algorithms with only minor adaptations. The design specifications for the fuel control system are presented. Detailed descriptions of the electronic hardware utilized are provided. A discussion of the software utilized in the system is presented. The software structure and the function of various programs are described in detail. An overview of the engine fuel control logic algorithms is given. The results of an experimental system evaluation are presented.
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