摘要
为提升固体火箭发动机喷管扩张段烧蚀台阶工作性能,优化扩张段材料。通过喷管CFD数值计算与地面静止试验,获得喷管优化前后的烧蚀型面与喷管设计质量系数。试验表明优化后烧蚀台阶处烧蚀量下降83.8%,喷管设计质量系数提高3.1%,数值计算表明优化后烧蚀台阶处斜激波减弱。喷管推力系数的数值计算结果略低于试验结果,误差小于8.2%,可为喷管设计提供参考。
Aiming at the problem of performance degradation caused by the erosion step of the nozzle divergent section of the solid rocket motor,the composite winding material used in the expansion section is optimized.Through the CFD numerical calculation of the nozzle and the ground static test,the ablation surface and the nozzle design quality coefficient before and after the nozzle optimization are obtained.The test results show that the ablation amount at the erosion step decreases by 83.8%and the nozzle design quality coefficient increases by 3.1%after optimization.The numerical calculation shows that there is a strong oblique shock wave at the erosion step before optimization,and the oblique shock wave is weakened after optimization.The thrust coefficient of the nozzle calculated by numerical method is lower than the experimental results,and the error is less than 8.2%,which can provide reference for nozzle design and optimization.
作者
林啸
李晓梦
程钟毓
杨明
张志
LIN Xiao;LI Xiaomeng;CHENG Zhongyu;YANG Ming;ZHANG Zhi(Shanghai Space Propulsion Technology Institute,Shanghai 201100,China)
出处
《兵器装备工程学报》
北大核心
2025年第S1期128-133,共6页
Journal of Ordnance Equipment Engineering
作者简介
林啸(1993-),男,硕士,工程师,E-mail:linxiao_aero@163.com;通信作者:程钟毓(1995-),男,硕士,工程师。
