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为研究火箭贮箱增压系统起动、关闭瞬变过程中压力冲击的产生过程和传播规律,采用可应用于多种气体计算的拉格朗日坐标下的一维非定常气体运动方程有限差分格式求解管路流动,管路元件由反映其动态过程的常微分方程数值求解,气体摩擦损失使用准稳态公式计算.采用B-B(Beattie-Bridgeman)方程描述真实气体热力学关系.对某增压系统模型起动、关闭中包括压力冲击在内的动态过程进行了计算.计算表明:起动过程中,压力冲击变化大,压力振荡周期短、频率高、衰减迅速;关闭过程中,压力冲击变化小,压力振荡周期长、频率低、衰减缓慢.两种过程中都出现了高于气瓶增压压力的冲击压力峰值.数学模型和方法在火箭贮箱增压系统瞬变过程的计算中显示了较好的有效性.
In order to study the generation process and propagation law of pressure shock during start-up and shutdown transient of rocket tank pressurization system, a one-dimensional unsteady gas equation of motion equation in finite difference format Solving the pipe flow, the pipeline elements are solved by the ordinary differential equations that reflect the dynamic process, and the gas friction loss is calculated by the quasi-steady state formula. The BB (Beattie-Bridgeman) equation is used to describe the real gas thermodynamic relationship. The dynamic process including pressure impact during start-up and shut-down is calculated. The calculation shows that during the start-up process, the pressure shock changes greatly, the pressure oscillation period is short, the frequency is high and the attenuation is rapid; during the closing process, the pressure impact changes little and the pressure oscillation Long period, low frequency and slow decay. Both of them have higher peak value of impact pressure than cylinder pressure. Mathematical model and method show good performance in the calculation of transient process of rocket tank pressurization system Effectiveness.