TY - GEN
T1 - Numerical Simulation of Three-dimensional Combustion Flows of Pasty Propellant Rocket Motor
AU - Hu, Renjie
AU - Wang, Weizong
N1 - Publisher Copyright:
© 2022 IEEE.
PY - 2022
Y1 - 2022
N2 - Pasty propellant rocket motor (PPRM) is considered to be one of the promising advanced chemical propulsion technologies due to the advantages of flexible thrust adjustment and multi-pulse operation. To reveal the underlying characteristics of internal combustion flows of pasty propellant rocket motor, a three-dimensional CFD simulation is established, considering the grain pyrolysis process, gas-solid coupled heat transfer as well as complex chemical kinetics and verified by comparing with experiment data. The results show that the flow in the combustion chamber of PPRMs presents strong three-dimensional characteristics, and the combustion process takes place in the extremely thin layer adjacent to the surface of propellant grain. Furthermore, with the increase of flow rate by 3 times, the thrust of the combustion chamber increases by 3.32 times, indicating the effectiveness of variable thrust adjustment of pasty rocket engine. The simulation accurately captures the combustion and flow characteristics, which provides guidance for the subsequent design optimization of the pasty propellant rocket motor.
AB - Pasty propellant rocket motor (PPRM) is considered to be one of the promising advanced chemical propulsion technologies due to the advantages of flexible thrust adjustment and multi-pulse operation. To reveal the underlying characteristics of internal combustion flows of pasty propellant rocket motor, a three-dimensional CFD simulation is established, considering the grain pyrolysis process, gas-solid coupled heat transfer as well as complex chemical kinetics and verified by comparing with experiment data. The results show that the flow in the combustion chamber of PPRMs presents strong three-dimensional characteristics, and the combustion process takes place in the extremely thin layer adjacent to the surface of propellant grain. Furthermore, with the increase of flow rate by 3 times, the thrust of the combustion chamber increases by 3.32 times, indicating the effectiveness of variable thrust adjustment of pasty rocket engine. The simulation accurately captures the combustion and flow characteristics, which provides guidance for the subsequent design optimization of the pasty propellant rocket motor.
KW - combustion flows
KW - conical burning model
KW - pasty propellant rocket motor
KW - three-dimensional numerical simulation
UR - https://www.scopus.com/pages/publications/85137260846
U2 - 10.1109/ICMAE56000.2022.9852854
DO - 10.1109/ICMAE56000.2022.9852854
M3 - 会议稿件
AN - SCOPUS:85137260846
T3 - 2022 13th International Conference on Mechanical and Aerospace Engineering, ICMAE 2022
SP - 290
EP - 295
BT - 2022 13th International Conference on Mechanical and Aerospace Engineering, ICMAE 2022
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 13th International Conference on Mechanical and Aerospace Engineering, ICMAE 2022
Y2 - 20 July 2022 through 22 July 2022
ER -