Abstract: In order to investigate the thrust performance of plug nozzle while the obliquity of the primary nozzle varied continuously, a research model was set up and an approximate method for plug nozzle design was adopted The optimum obliquity was determined in the prescript conditions The relations of the height of the base, the expansion ratio of primary nozzle, the engine expansion ratio, the total pressure of the gas, the flight altitude and the optimum obliquity was analyzed Preliminary tests were conducted and analyzed in comparison with the theoretical results

Key words: Rocket engine;Plug nozzle;Slope angle;Angle properties;Nozzle thrust coefficient

摘要： 首先建立了塞式喷管角度特性的研究模型 ,并运用简化的塞锥设计方法设计塞锥型面 ,在此基础上 ,通过连续改变主喷管倾角来研究主喷管倾角对塞式喷管的推力性能的影响 ,并确定在给定设计条件下的主喷管最佳倾角 ,还分析研究了底部高度、内膨胀比、总膨胀比、总压和飞行高度与主喷管最佳倾角的关系以及变化规律。针对特定的塞式喷管实验发动机 ,进行了初步的变角度实验 ,并与计算结果进行比较和分析

关键词: 火箭发动机;塞式喷管;倾角;角度特性;喷管推力系数