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Journal of System Simulation

Xuesen Yang, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China; National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine, Beijing 100190, China
Wei Zhao, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China; National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine, Beijing 100190, China; School of Aeronautics and Astronautics, University of Chinese Academy of Sciences, Beijing 100049, China
Binglong Zhang, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China; National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine, Beijing 100190, China
Sanqun Ren, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China; National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine, Beijing 100190, China
Xiaorong Xiang, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China; National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine, Beijing 100190, China; School of Aeronautics and Astronautics, University of Chinese Academy of Sciences, Beijing 100049, China
Qingjun Zhao, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China; National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine, Beijing 100190, China; School of Aeronautics and Astronautics, University of Chinese Academy of Sciences, Beijing 100049, China; Beijing Key Laboratory of Distributed Combined Cooling Heating and Power System, Beijing 100190, China

Abstract

Abstract: To satisfy the requirements for validating the control law of air turbo rocket (ATR) engines, a semi-physical simulation approach was proposed based on serial communication. This platform integrated a rapid prototype system, a supply system, a measurement and control system, a signal simulator, a fault injection system, and a real-time computer. A digital model of the engine was developed based on cross-compilation technology, enabling the coupling and semi-physical simulation of the engine control system and the supply system. A semi-physical simulation of the ATR engine in the startup process was carried out, and the fault handling strategy of the controller under the situation of turbine outlet temperature exceeding the limit was tested. The results demonstrate that using frequency measurements as rotational speed signal instructions of the signal simulator achieves a simulation accuracy of up to 0.01%FS, with a refresh time of less than 1 ms. When the flow rate of the gas generator kerosene pump reaches 16.2% of the maximum value, the engine enters a self-sustaining speed state, and the back pressure of the gas generator kerosene pump and the liquid oxygen pump is 1.28 MPa. Once the flow rate of the gas generator kerosene pump reaches its maximum, the engine speed and thrust simultaneously reach the designed status. When the turbine outlet temperature exceeds the limit of 50 ° C, the overtemperature protection mechanism is initiated. The speed of the electric pumps is set to zero to avoid potential operating risks for the engine.

First Page

2061

Last Page

2073

CLC

TP391.9

Recommended Citation

Yang Xuesen, Zhao Wei, Zhang Binglong, et al. Study on Semi-physical Simulation Method of Air Turbo Rocket Engine in Startup Process[J]. Journal of System Simulation, 2025, 37(8): 2061-2073.

Corresponding Author

Zhao Qingjun

DOI

10.16182/j.issn1004731x.joss.24-0271

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