端部初始燃面可变的星孔火箭装药燃烧特性  

Combustion Characteristics of Star Shaped Rocket Grain with Variable Initial End Burning Surface Area

作　　者：牛公杰[1] 钱建平[1] 刘荣忠[1] 

机构地区：[1]南京理工大学机械工程学院,江苏南京210094

出　　处：《火炸药学报》2011年第5期82-86,共5页Chinese Journal of Explosives & Propellants

摘　　要：采用上、下端面均无包覆星孔装药的小型自由装填式固体火箭发动机,其药柱端面与垫片间的间隙会受温度等因素影响而发生变化。端部初始燃面变化规律较为复杂,无法使用经典的燃面计算理论。通过引入端面燃烧参与度和端面等效燃烧厚度的方法,结合试验条件导出了燃面面积经验计算公式,解决了端部初始燃面可变的星孔火箭装药燃面计算问题。研究了不同温度条件下火箭发动机性能的变化,得出了温度对火箭发动机性能的影响规律和可用于指导实际工程应用的结论。For the small free loading solid rocket motor with ends-non-coated star shaped grain,the clearance between the tail end face of grain and the gaskets will be affected by factors,e.g.temperature variations.Due to the complexity in initial end burning surface area,the classical theory of burning surface calculation cannot be employed.By introducing the end burning proportion,end burning equivalent thickness and considering the experimental conditions,a calculation formula of burning surface area was derived,and the burning surface area calculation problem of star shaped rocket grain with variable initial end burning surface area was solved.By studying the performance on solid rocket engine under different temperature circumstance,the effecting rule of temperature on the solid rocket motor performance is obtained.These conclusions can be used in the practical application.

关 键 词：物理化学 星孔火箭装药 端面燃烧 端面等效燃烧厚度 固体火箭发动机 燃烧特性 

分 类 号：TJ55[兵器科学与技术—军事化学与烟火技术] V43[航空宇航科学与技术—航空宇航推进理论与工程]