Sub-Optimal Control of a Gas Turbine Engine.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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Gas turbine engine technology has been advanced to the point where it is increasingly difficult to apply conventional feedback control theory to the design of its necessary multiple-input and multiple-output control systems. Modern linear control theory was applied to the engine control problem in four stages. Stage 1 involved formulating a simple, reliable, and representative mathematical model of the engine and describing the model in state variable form. Stage 2 involved using a truncated Taylor series to linearize the engine state equations about a succession of engine equilibrium points and solving the linear optimal output regulator problem and the linear optimal tracking problem to minimize a quadratic Performance Index. In stage 3, the engine model was simulated on a digital computer via the MIMIC Simulation Language. The engine control laws were then realized in a FORTRAN function sub-program. Stage 4 consisted of testing the controlled engine for various throttle demands to verify the satisfactory operation of the controller. Author
- Jet and Gas Turbine Engines