喷管型面对固体火箭发动机性能的影响

EFFECTS OF NOZZLE GEOMETRY ON THE PERFORMANCE OF SOLID ROCKET MOTORS

关键词:  收敛扩散喷管  跨音速流  二相流  计算方法  固体火箭发动机  计算

Key words:  Convergent divergent nozzle  Transonic flow  Two-Phase flow  Calculation method  Solid Rocket engine  Calculation

摘要:

用时间相关法数值计算跨音速喷管流动时,其控制方程分别采用守恒型和非守恒型方程.通过对JPL喷管进行计算发现:在相同的精度下,非守恒型方程的收敛速度比守恒型方程的收敛速度快一倍多.采用修正阻尼法(DASHCO法)进行数值计算,其收敛速度均提高六倍以上.最后,采用直接优化法研究了喷管收敛段型面及喉部型面对发动机性能的影响.

Abstract:

In this paper, the time-dependent method is applied to the numerical computation of transonic nozzle flows by using of conservation and nonconservation governing equations.The computation of the JPL nozzle shows that the convergent rate of the nonconservation equations is more than twice as much as that of the conservation equations with the same precision,and the computational and experimental results are fairly identical.When the corrected dashpot method is applied, the convergent rate is seven times higher than that of the corresponding time-dependent method with the same precision.The convergent rate varies widely with the damping factor K and the time interval r. Finally, the direct optimization technique is applied to the study of the effects of nozzle inlet and throat geometry on the performance of solid rocket motors. Some conclusions are drawn from the experimental results.