Numerical Simulation on Heat Transfer and Ablation for the Nozzle of a Solid Rocket Motor

BAI Taotao; SUN Zhenhua

doi:10.15892/j.cnki.djzdxb.2022.04.022

Journal of Projectiles, Rockets, Missiles and Guidance >

2022 , Vol. 42 >Issue 4: 119 - 124

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2022.04.022

Numerical Simulation on Heat Transfer and Ablation for the Nozzle of a Solid Rocket Motor

BAI Taotao ¹ ,
SUN Zhenhua ¹^,²

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¹ China Airborn Missile Academy, Luoyang 471009, Henan, China
² Aviation Key Laboratory of Science and Technology on Airborne Guided Weapons, Luoyang 471009, Henan, China

Received date: 2021-12-19

Online published: 2025-05-29

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Abstract

Aim at the nozzle of SRM, the heat transfer and ablation are programmed using the secondary development function of commercial CFD software, the calculation method of heat transfer and ablation for nozzle divergent is developed, and the fluid-solid-thermal coupling numerical calculation of nozzle is carried out, the density, specific heat capacity, thermal conductivity and temperature of nozzle divergent under different times are obtained, the variation of volume ablation, surface ablation and outside wall temperature with time for nozzle divergent are estimated, and comparisons are made between simulation and test results. It shows that: the surface ablation of divergent is centred on the left half that is close to throat, which is generated by the high pressure working section of SRM; the mass loss rate of volume ablation for nozzle divergent is the largest in the initial stage of working process for SRM, and then it gradually decreases.

Key words： solid rocket motor; nozzle; heat transfer; ablation; carbon phenolic

Cite this article

BAI Taotao , SUN Zhenhua . Numerical Simulation on Heat Transfer and Ablation for the Nozzle of a Solid Rocket Motor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2022 , 42(4) : 119 -124 . DOI: 10.15892/j.cnki.djzdxb.2022.04.022

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