脉冲推力器内弹道特性研究与改进  

Study and improvement on interior ballistic characteristics of an impulse thruster

作　　者：王骁 王浩[1] 阮文俊[1] 张磊[2] 臧敏 

机构地区：[1]南京理工大学能源与动力工程学院,南京210094 [2]中国船舶重工集团公司七一0所,宜昌443003

出　　处：《固体火箭技术》2017年第6期686-690,共5页Journal of Solid Rocket Technology

基　　金：基金项目:江苏省研究生培养创新工程(KYLX16_0477)

摘　　要：为了研究某脉冲推力器的内弹道特性,建立考虑点火过程的内弹道数学模型,对点火药量为0.6 g,主装药量分别为3.4 g和2.8 g的装药方案进行数值计算,并进行试验验证,数值计算结果与试验结果较一致。分析了脉冲推力器工作不稳定的因素,指出点火药颗粒度过大、燃速过慢会导致工作阶段输出不稳定。为改进脉冲推力器的内弹道性能,对颗粒度更小的点火药进行了数值计算。结果表明,使用颗粒度更小的点火药,可使脉冲推力器的内弹道性能有所改善。A mathematical model considering ignition process was established to study the interior ballistic characteristics of an impulse thruster. Numerical calculations and verification experiments for different charge plans were carried out, in which the igni- tion charge mass was 0.6 g, and the main charge masses were 3.4 g and 2.8 g, respectively. Theoretical and experimental results show a great agreement. The factors causing instability process of the impulse thruster were analyzed. It has been indicated that the excessive granularity of ignition powder as well as low burning rate can cause unstable output of the impulse thruster. To improve the interior ballistic characteristics, further numerical calculations were performed using the same propellant but thinner ignition powder. Computed results show that using thinner ignition powder would improve interior ballistic characteristics of the impulse thruster.

关 键 词：兵器发射理论与技术 脉冲推力器 内弹道 数值计算 颗粒度 

分 类 号：V439.7[航空宇航科学与技术—航空宇航推进理论与工程]