摘要
针对固体火箭发动机地面模拟过载试验，开展了燃烧室凝相粒子所受加速度理论分析，认为粒子主要受哥氏加速度和气相阻力的作用，离心加速度的作用并不占优。最后，针对3组不同过载下的缩比发动机，分别开展了三维两相流数值计算并进行了地面旋转模拟过载试验，数值计算得到的粒子聚集区维持在第Ⅰ象限偏第Ⅳ象限60°～80°之间；旋转试验解剖后的结果反映了颗粒冲刷严重部位及烧蚀严重部位维持在第Ⅰ象限偏第Ⅳ象限70°～90°之间。两种结果具有一定吻合性，也验证了理论分析的合理性和正确性。
Aiming at solid rocket motor overload ground simulation test, the acceleration theoretical analysis for condensate phase particle was carried out. The results show that the particles are mainly affected by the Coriolis acceleration and gas drag role, but the role of the centrifugal acceleration is not dominant. Finally,3D two-phase flow calculations as well as the ground simulation overload test under three groups overload conditions were carried out. Numerical calculation results reveal that particle deposition zone maintain between 60°-80° along the first quadrant to the four quadrant direction;the rotation test results reflect that serious erosion site and ablation site maintain between 70°-90° along the first quadrant to the four quadrant direction. Two results coincide well to a certain extent,which verify that the theoretical analysis is reasonable adn correct.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2014年第4期486-489,共4页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
凝相粒子
哥氏加速度
离心加速度
solid rocket motor
condensed phase particles
Coriolis acceleration
centrifugal acceleration
