Working Fluid modeling Based on Air Turbine Rocket Engine and Propellant Comparative Analysis

Authors

  • Shangchun Wang
  • Yang Liu
  • Yue Wu
  • Zheng Ni

DOI:

https://doi.org/10.54097/hset.v1i.439

Keywords:

Propellant, Primary gas, Molar mass, Specific heat ratio

Abstract

The propellant of the Air Turbo Rocket (ATR) engine is burned in the gas generator to produce primary gas. This paper uses the established ATR engine working fluid calculation model to calculate the physical parameters and components of the primary gas produced by the combustion of four propellants at a given pressure and temperature, and compares and analyzes them according to the propellant selection requirements, Choose the appropriate propellant for the ATR engine.

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References

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Published

14-06-2022

Issue

Vol. 1 (2022): 5th International Conference on Computer Engineering, Information Science & Application Technology (ICCIA 2022)

Section

Articles

License

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This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.