CAJ | 학술논문

选取颗粒轨道模型，对Al／AP粉末颗粒在粉末火箭发动机内流动和燃烧进行三维数值模拟，为以Al粉末燃料和AP粉末氧化剂作为推进剂的新型燃烧室的设计以及实验研究提供参考。文中提出了一种粉末火箭发动机构型，通过对发动机燃烧室进行冷态和热态数值模拟，研究了氧燃比、Al粉末颗粒大小、燃烧室体积等因素对粉末火箭发动机燃烧室燃烧性能的影响。结果表明，一定范围内氧燃比较高时，燃烧室温度反而较低；较小粉末颗粒在燃烧室内更易离散；Al颗粒粒径越小越易燃烧，Al燃烧率也越高；验证了在Al／AP粉末火箭发动机的设计中引入特征长度来匹配Al粉粒径与燃烧室体积的合理性。
선취과립궤도모형，대Al／AP분말과립재분말화전발동궤내류동화연소진행삼유수치모의，위이Al분말연료화AP분말양화제작위추진제적신형연소실적설계이급실험연구제공삼고。문중제출료일충분말화전발동궤구형，통과대발동궤연소실진행랭태화열태수치모의，연구료양연비、Al분말과립대소、연소실체적등인소대분말화전발동궤연소실연소성능적영향。결과표명，일정범위내양연비교고시，연소실온도반이교저；교소분말과립재연소실내경역리산；Al과립립경월소월역연소，Al연소솔야월고；험증료재Al／AP분말화전발동궤적설계중인입특정장도래필배Al분립경여연소실체적적합이성。
3D flow and combustion in the chamber of Al/AP powder rocket was numerically simulated by the particle trajectory model so as to provide reference for the design of the thrust chamber and the experimental investigation.The effects of oxidizer/fuel radio,particle diameter of Al and the volume of the combustion chamber were analyzed by a new engine configuration. The results show that the temperature of the chamber is lower when the oxidant/fuel ratio is higher in certain range,the combustion is easier when the particle of Al is smaller and the combustion efficiency of Al is higher. It is reasonable to choose an appropriate chamber characteristic length to adapt to the particle diameter of Al.