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论文类型：期刊论文
发表时间：2022-06-28
发表刊物：固体火箭技术
所属单位：运载工程与力学学部
期号：2
页面范围：208-213
ISSN号：1006-2793
摘要：A general calculation model based on thermal coupling at burning face and PDF combustion model was proposed to simulate the flow and combustion in hybrid rocket motor. Two dimensional hybrid rocket motors were simulated by this calculation model and regression rate was obtained.The calculation results agree well with test data,which means the PDF model can simulate the diffusion combustion in hybrid rocket combustor and the simplified one dimensional thermal coupling method at burning surface can be used in multi-dimensional calculations.The calculation model can be widely used in hybrid rocket flowfield simulation and al-so be used to predict the fuel regression rate.
备注：新增回溯数据