Experimental identification and control-oriented modeling of a micro turbojet propulsion system with thrust vectoring for vertical take-off and landing applications

The project experimentally identifies and creates a control‑oriented model of a micro turbojet vertical‑take‑off‑and‑landing (VTVL) propulsion system that includes thrust‑vectoring vanes. Because the structure can flex and distort force measurements, the method first identifies the structural dynamics and then uses an inverse‑transfer‑function filter to clean up the signals. Experiments cover the engine’s full operating range, from 0 % to 100 % of rated RPM, and produce up to about 364 N of thrust. The thrust‑vectoring vanes are tested over a ±6° deflection range. At a typical operating point of 60 % commanded RPM (which yields 153 N of thrust), the vanes generate a roughly linear lateral force of 10–12 N

around the neutral position. The whole propulsion system is modeled with a hybrid approach: a nonlinear static map captures steady‑state behavior, while a dynamic transfer function represents the system’s dynamics. This combination yields a very accurate, control‑focused model that can be used to design and evaluate guidance, navigation, and control (GNC) algorithms for advanced VTVL aerospace applications.

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