论文部分内容阅读
以双下侧进气布局的固体火箭冲压发动机为研究对象,以补燃室中燃气与空气的掺混燃烧效率规律为研究目标,将燃气喷管数量、补燃室头部距离、补燃室长径比、空气进气角度、空气进气速度5个因子作为二次燃烧效率的影响因子,基于试验设计方法,建立了5因子2水平的全因子试验表,并以该表为基础对构建出的32种不同掺混结构的固体火箭冲压发动机补燃室的反应流场进行数值模拟。用试验设计中的数据处理方法对计算结果进行分析,获得了5个显著因子及各因子对燃烧效率的影响规律。为了验证分析结果的正确性,从试验设计表中选取5种掺混结构进行了地面连管试验,试验结果与分析结论一致。将试验设计方法应用到固体火箭冲压发动机燃烧性能的研究中,为发动机性能寻优提供了新途径,具有较高的工程应用价值。
In this paper, the solid rocket ramjet engine with double bottom intake is taken as the research object, and the combustion efficiency of gas and air in the afterburner is taken as the research goal. The number of gas nozzle, the head distance of the afterburner, Length-diameter ratio, air intake angle and air intake speed as the influencing factors of secondary combustion efficiency. Based on the experimental design method, a full-factor test table of 5 factors and 2 levels was established. Based on this table, Out of 32 different mixed structure of solid rocket ramjet combustion chamber after the reaction flow field numerical simulation. The data processing method in the experimental design is used to analyze the calculation results, and five significant factors and the influence laws of each factor on the combustion efficiency are obtained. In order to verify the correctness of the analysis results, five kinds of mixed structures were selected from the experimental design table to carry on the ground connection test, the test results are consistent with the analysis. The experimental design method applied to the combustion performance of solid rocket ramjet engine provides a new way for optimizing engine performance and has high engineering application value.