摘要
基于热力学第一定律的一般表达式,推导了单燃速和双燃速固体火箭发动机零维内弹道能量方程,并指出一些有关固体火箭发动机原理的教材中给出的单燃速零维内弹道方程在理论上并不严格一致的两个原因:一是忽略了发动机点火启动过程中燃烧室内的温度变化;二是忽略了因推进剂燃面退移控制系统所做的容积功.在一个算例中,教材中的内弹道方程计算出的点火启动时间比本文方程计算出的时间约长40%,说明不宜忽略点火启动过程中燃烧室内燃气温度的变化.
Zero-dimensional internal ballistic equations for single burning rate solid rocket motor(SRM) in some textbooks on the principal of SRM were not strictly identical with each other.On the basis of the general expression of the First Law of Thermodynamics,stricter zero-dimensional internal ballistic energy equations for single-and dual-burning rate SRM were deduced,in the equations,the volume work due to the regress of burning surface of propellant was considered.The above inconsistency was explained on the b...
出处
《华中科技大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2007年第12期103-106,共4页
Journal of Huazhong University of Science and Technology(Natural Science Edition)
关键词
固体火箭发动机
内弹道方程
双燃速
solid rocket motor（SRM）
internal ballistic equation
dual-burning rate
