Development of Optimal Control Modes for Advanced Technology Propulsion Systems.
Interim technical rept. 1 Feb-30 Jun 73,
UNITED AIRCRAFT RESEARCH LABS EAST HARTFORD CONN
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A nonlinear multivariable feedback controller was developed for the VSTOL hover application 80 to 100 percent thrust range of the Pratt and Whitney Aircraft F401 variable cycle turbofan engine. The analytical design involved 1 linearizing the F401 engine dynamics about two closely-spaced, steady-state operating points and applying linear optimization methods at each point, and 2 combining two optimal linear controllers into a single nonlinear controller having feedback gains that vary with system state. Variable fan, compressor, and exhaust geometries and changes in main burner fuel flow rate are coordinated by the controller to achieve improved engine dynamic response. Responses with the optimal controller were computed using a nonlinear digital simulation of the engine. The engine response evaluated was for a commanded thrust change from the VSTOL hover setting 80 percent to military rated thrust 100 percent. These responses were compared with those obtained using a state-of-the-art conventional controller designed to provide rapid thrust response the P and WA fast accel controller. Modified author abstract
- Jet and Gas Turbine Engines