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.
出处
《火炸药学报》
EI
CAS
CSCD
北大核心
2011年第5期82-86,共5页
Chinese Journal of Explosives & Propellants
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
physical chemistry
star shaped rocket grain
end burning
end burning equivalent thickness
solid rocket motor
combustion characteristic
