CAJ | 학술논문

根据固体燃料超燃冲压发动机的工作特点，以飞行Ma＝6、高度25 km为设计条件，对发动机各部件进行了初步设计。采用数值模拟方法，研究了不同来流条件下发动机各部件及总体性能的变化规律。结果表明，设计状态下的进气道流量系数接近1，来流马赫数降到4时，进气道启动失败；随来流马赫数的增大，火焰温度整体升高，燃烧效率逐渐降低；发动机在设计状态下产生的推力最大，比冲随来流马赫数的增大而降低。
근거고체연료초연충압발동궤적공작특점，이비행Ma＝6、고도25 km위설계조건，대발동궤각부건진행료초보설계。채용수치모의방법，연구료불동래류조건하발동궤각부건급총체성능적변화규률。결과표명，설계상태하적진기도류량계수접근1，래류마혁수강도4시，진기도계동실패；수래류마혁수적증대，화염온도정체승고，연소효솔축점강저；발동궤재설계상태하산생적추력최대，비충수래류마혁수적증대이강저。
Based on the characteristics of solid fuel scramjet,various components were designed preliminarily under the condi-tion of free stream Ma=6 and flight altitude of 25 km.Numerical simulations were performed to analyze the performance variation law of each component and the whole engine under different inflow conditions.The results show that the flow capture ratio approximates 1 under the design point.When free stream Mach decreases to 4,the inlet becomes unstarted.With the free stream Mach increasing,the flame temperature increases and the combustion efficiency decreases gradually.The thrust is largest under the design point,and the specific impulse decreases with the increase of free stream Mach.