火箭推进2025，Vol.51Issue(2)：10-20,11.DOI:10.3969/j.issn.1672-9374.2025.02.002
氧化亚氮自增压液体火箭动力系统设计与仿真
Design and simulation of a self-pressurized liquid rocket propulsion system with nitrous oxide
冯杰 1汪嘉睿1
作者信息
- 1. 西北工业大学 航天学院,陕西 西安 710072
- 折叠
摘要
Abstract
In order to determine the ideal configuration of nitrous oxide bi-propellant self-pressurized liquid propulsion system,and quickly provide accurate key parameters for subsequent component-level detailed design and overall rocket design,a system model library of nitrous oxide liquid rocket engine coupling the propulsion system with the external trajectory was built using Modelica language based on the REFPROP model.The self-pressurized tank module of nitrous oxide in the library was validated through experimental and simulation data published in public literature,and the pressure and mass results were in good agreement.The system model library was used to explore the different performance of two typical nitrous oxide bi-propellant liquid rocket engines with different pressurization methods during operation.The results show that the tank with a shared nitrous oxide pressure source has faster pressure and flow rate decay compared to the tank with separate pressure source,but the oxygen fuel ratio is more stable.For a small liquid sounding rocket used for verifying flight control system,the influence of different combustion chamber pressures on rocket flight performance was calculated under the same supply system.The results show that at an ambient temperature of 288 K,when the chamber pressure increases to about 82％or more of the N2O tank pressure,the rocket's powered flight time can reach over 8 s,while the maximum flight altitude can reach over 5.0 km.关键词
挤压式液体探空火箭/氧化亚氮/自增压/Modelica/系统仿真Key words
pressure-fed liquid sounding rocket/nitrous oxide/self-pressurization/Modelica/system simulation引用本文复制引用
冯杰,汪嘉睿..氧化亚氮自增压液体火箭动力系统设计与仿真[J].火箭推进,2025,51(2):10-20,11.
