تست سخت افزار در حلقه شير كنترل دبي سوخت يك موتور توربوجت

This thesis focuses on the design an‎d implementation of a Hardware-in-the-Loop (HIL) simulation platform for testing an‎d eva‎luating the electrohydraulic fuel control unit of a turbojet engine. The primary objective of the research is to provide a safe, cost-effective, an‎d reliable environment for investigating the dynamic performance of the fuel control system under conditions close to real engine operation, without the need for direct testing on an operational engine. To this end, a real-time model of the turbojet engine, including thermodynamic an‎d dynamic subsystems, has been developed. The model is capable of reproducing both steady-state an‎d transient engine behavior, including variations in shaft rotational speed in response to changes in fuel flow rate. This model serves as the core of the simulator an‎d interacts online with the physical hardware. The electrohydraulic unit under study includes a fuel pump which, in real applications, is driven by the engine shaft through a gearbox. In the HIL simulation platform, an AC motor coupled with an inverter is used instead of the turbojet engine, allowing the pump rotational speed to be adjusted according to the speed calculated by the real-time engine model. In this way, the physical dependency between shaft speed an‎d pump performance is realistically emulated. Fuel flow control is achieved through the displacement of a valve spool, actuated by a DC servo motor an‎d a cam mechanism. In the HIL test setup, the fuel flow comman‎d is generated by the real-time simulator an‎d applied to the servo system, enabling eva‎luation of the mechanical an‎d hydraulic response of the system under various operating conditions. To measure fuel flow rate, a hydraulic motor equipped with an encoder is employed. The rotational speed of the hydraulic motor is proportional to the passing flow rate an‎d can be measured via the encoder signal. This structure enables accurate indirect flow measurement an‎d provides the necessary feedback loop for eva‎luating the control performance of the system. In this research, an integrated architecture comprising the numerical engine model, the electric pump drive, the valve actuation servo system, the flow measurement unit, an‎d the data exchange subsystem has been designed an‎d implemented. The results demonstrate that the proposed platform is capable of accurately reproducing the transient behavior of the fuel control unit an‎d enables analysis of stability, time response, an‎d control performance under various scenarios. In addition to reducing the cost an‎d risk of field testing, this approach provides an efficient platform for the development, validation, an‎d optimization of turbojet engine fuel control systems.

مصطفي نصيري

مرضيه رضازاده

ايمان فخاري گلپايگاني , حامد رضوي بني