摘要
针对某大长径比固体火箭发动机试验过程中出现的压强异常升高、推力异常振荡、工作时间大幅缩短的现象,通过试验数据分析、声腔模态分析、大涡模拟(LES)及单项试验验证等多种手段,分析了发动机燃烧室内阻尼因助推级工作结束、喉通比减小等因素而降低,使得阻尼小于推进剂燃烧增益是导致某大长径比发动机发生不稳定燃烧的主要原因。同时,提出了可以通过优化续航级推进剂配方解决发动机不稳定燃烧。随后,通过T型燃烧器试验筛选,获得了一种低压强耦合响应函数的续航级推进剂配方,并使用该配方开展了一系列验证试验。试验结果表明,在更换压强耦合响应函数较低的新配方后,参与试验的多发发动机未发生不稳定燃烧,通过更换配方解决发动机不稳定燃烧的措施有效。
Aiming at some abnormal phenomena of pressure rise,thrust oscillation and greatly shortened working time during the test of the solid rocket motor with large aspect ratio,by means of test data analysis,acoustic chamber modal analysis,the large-eddy-simulation(LES)and single test verification,the reduction of internal damping in the combustion chamber of the motor due to the booster stage ending and the reduction of throat to port ratio was analyzed.The results show the internal damping less than the propellant combustion gain is the main reason for the unstable combustion of a large aspect ratio motor.At the same time,it is proposed that the unstable combustion of the motor can be solved by optimizing the propellant formula of the sustained motor.Through screening test of T-type burner,a sustained propellant formula with low-pressure coupling response function was obtained,and a series of verification tests were carried out with this formula.The test results show that after the substitution of new formula with low-pressure coupling response function,most of motors in these tests have no combustion instability.the measure to solve the unstable combustion by using new formula is effective.
作者
陈子豪
韩文超
章致海
吴敏
方恒
CHEN Zihao;HAN Wenchao;ZHANG Zhihai;WU Min;FANG Heng(Missile Academy,Wuhan Guide Infrared Co.Ltd,Wuhan 430205,China;Hubei Institute of Aerospace Chemical Technology,Xiangyang 441003,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2022年第4期631-638,共8页
Journal of Solid Rocket Technology
