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Huang, H.M., Xu, X.L. and Jiang, G.Q. (2009) Discrimination for Ablative Control Mechanism in Solid-Propellant Rocket Nozzle. Science in China Series E: Technological Sciences, 52, 2911-2917.
https://doi.org/10.1007/s11431-009-0274-2

has been cited by the following article:

• TITLE: Simulation Study of Solid Rocket Motor C/C Throat Liner Ablation Based on Two Regions

  AUTHORS: Guanneng Chen, Yihua Xu, Xiaojiang Zha, Hemeng Shi, Bing Liu

  KEYWORDS: Dual-Area Ablation Model, C/C Throat Liner, Ablation Environment, Ablation Program

  JOURNAL NAME: Journal of Power and Energy Engineering, Vol.12 No.4, April 17, 2024

  ABSTRACT: Based on the ablation micro-morphological characteristics, thermo-chemical ablation mechanism, and mechanical stripping mechanism, a dual-region solid rocket motor C/C throat liner ablation model and physical model are established. The ablation program was written and the experimental data of 70 lb BATES engine platform was used for model validation. The relative errors between the simulation calculation results and the experimental results were −6.83% - 10.20%. The ablation program was applied to study the effects of combustion chamber temperature, pressure, oxidation component concentration, throat particle concentration and particle scouring angle on the nozzle throat liner, which provides a reference for the design of the nozzle throat liner and the estimation of solid rocket motor ablation.