SPATR发动机循环参数选择与特性分析  

Cycle parameter selection and characteristics analysis for SPATR

作　　者：梁振欣[1] 陈玉春[1] 黄兴鲁[1] 屠秋野[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《固体火箭技术》2010年第5期528-532,559,共6页Journal of Solid Rocket Technology

摘　　要：为了更好地选择固体推进剂吸气式涡轮火箭发动机(SPATR)的设计循环参数,以及拓宽SPATR发动机的工作范围,根据SPATR发动机的结构特点,建立了富燃燃气流量可调的SPATR发动机的性能计算数学模型,并编制了相应的计算程序。利用程序计算和分析了不同空燃比和涡轮进口参数下的SPATR发动机设计点性能,并以此对SPATR发动机设计点循环参数进行了合理的选择。利用程序分别计算了富燃燃气流量可调和不可调的SPATR发动机的高度、速度特性和节流特性,并对计算结果进行分析和比较。结果表明,富燃燃气流量可调节的SPATR发动机具有更好的高度、速度特性,并能够实现节流工况调节,满足飞行器对推力调节的需求。For selecting the cycle parameters and broadening the operating range of solid propellant air-turbo-rocket（SPATR）,a mathematical model to calculate the performance of SPATR with adjustable rich-fuel gas was set up,and the corresponding computing program was developed.By using the program,the effect of air-fuel ratio and parameters of turbine inlet on the SPATR performance at design condition was computed and analyzed,and the cycle parameters of design condition of SPATR were selected reasonably.The characteristics of SPATR were computed in two case,i.e.constant gas flow mass in turbine inlet and adjustable gas flow mass in turbine inlet,and the computing results were analyzed and compared.The results indicate that SPATR with adjustable rich-fuel gas not only has better altitude and velocity characteristics,but also meets the need of thrust adjustment for aircraft by throttling governing.

关 键 词：固体推进剂吸气式涡轮火箭发动机 循环参数 数学模型 控制规律 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]