固体火箭发动机点火过程内流场的二维预示

TWO DIMENSIONAL PREDICTION FOR SOLID PROPELLANT ROCKET MOTOR INTERNAL FLOWFIELD DURING STARTING TRANSIENTS

本文对固体火箭发动机点火过程的内流场进行了二维无粘非定常分析,计算得到了该阶段燃烧室中压强、温度和速度的分布。本文还提出了用以近似预示复杂三维装药发动机内流场的有效容积法。

Internal flow during starting transient process was analysised with 2D, in viscid, unsteady, compressible model. The MacCormack's two-step explicit finite difference scheme is adopted for the solution of the Euler governing equations. The distribution of presure, temperature and velocity has been predicted with this model. Also a new equal volume approximate technique was presented to analysis the internal flowfield in 3D grain post during the ignition process.