Investigation of Carbon–Carbon Nozzle Throat Erosion in a Solid Rocket Motor Under Acceleration Conditions

Wang, Liwu; Tian, Weiping; Chen, Linquan; Guo, Yunqiang

doi:10.1007/s42405-020-00277-4

Cited by 16 publications

(1 citation statement)

References 21 publications

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“…The occurrence of ablation will cause the retreat of the inner wall surface and size changes, which directly affects the engine thrust, speed and range and other overall performance indicators. Therefore, it is of great scientific and engineering significance to study the ablation pattern of throat lining to help understand the stresses on key engine components, optimize the design, improve the performance, and ensure the operational safety [1].…”

Section: Introductionmentioning

confidence: 99%

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

Chen,

Xu,

Zha

et al. 2024

JPEE

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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.

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Section: Introductionmentioning

confidence: 99%