喉栓式推力可调发动机喷管流场数值模拟  

Numerical simulation on steady flow field of variable thrust motor nozzle with pintle

作　　者：滑利辉[1] 田维平[1] 甘晓松[1] 武渊[1] 

机构地区：[1]中国航天科技集团公司四院四十一所固体火箭发动机燃烧热结构与内流场国防科技重点实验室,西安710025

出　　处：《固体火箭技术》2008年第4期344-349,共6页Journal of Solid Rocket Technology

摘　　要：对喉栓式推力可调固体火箭发动机喷管流场进行了数值模拟,并对喉栓型面进行了过程优化;针对喉栓不同作动速度和自由容积,分析了流场内各参数的变化;进行了非同轴喉栓发动机试验研究。计算结果表明,细长锥型喉栓总体性能最优;发动机压强建立过程与喉栓作动速度和自由容积关系密切;模拟结果与试验数据差别不大,可为喉栓式推力可调固体火箭发动机的研发提供参考。The flow field of the variable thrust motor nozzle with pintle was numerically simulated, and the throat pintle contour was optimized. Under different actuating velocity and free volume of the throat pintle, all the parameters in the flow field were analyzed. The non-coaxial pintle motor was investigated by means of the test. The calculation results show that system performance of slender wedge throat pintle was optimal. Motor pressure depends mainly on actuating velocity and free volume of the throat pintle. The simulation results are close to experimental results, which can provide a reference for development of the variable thrust motor nozzle with pintle.

关 键 词：喉栓式推力可调固体火箭发动机 数值模拟 过程优化 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]