摘要
基于国内现有的单燃速固体火箭发动机热力学参数计算部级标准,文中推导了理论上比较严格、形式上尽可能简单的双燃速固体发动机零维两相内弹道方程,其中包括一种新形式的能量方程,以及简单可行的计算点火上升段和拖尾段比冲和特征速度的方法。作为示例,计算了"长二丙"运载火箭上面级固体发动机的内弹道,结果表明文中方法的预示精度满足工程要求。
Based on the domestic ministerial standard for computing thermodynamic parameters of single burning rate solid rocket motors, the theoretically strict and formally simple zero-dimensional two-phase internal ballistic equations were deduced; these included a new type of energy equation, a simple and feasible algorithm for calculating the specific impulse and characteristic velocity of ignition process and tail off portion. As an illustrative example, the internal ballistics of the upper stage solid motor of CZ-2C launch vehicle was calculated, the computational result shows that the predicted precision meets engineering requirement.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第4期150-153,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
固体火箭发动机
内弹道方程
双燃速
零维
solid rocket motor
internal ballistic equation
dual-burning rate
zero-dimensional
