脉冲触发对固体火箭发动机内弹道压强抬升的影响  

Effect of pulse triggering on internal ballistic pressure rise of solid rocket motor

作　　者：张文昊 李军伟[1] 曾佳进 卢健程 牛俊博 王宁飞[1] ZHANG Wenhao;LI Junwei;ZENG Jiajin;LU Jiancheng;NIU Junbo;WANG Ningfei(School of Astronautics,Beijing Institute of Technology,Beijing 100081,China;Xi'an Shenlan Aerospace Technology Co.Ltd.,Xi'an 710075,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]西安深蓝航天科技有限公司,西安710075

出　　处：《固体火箭技术》2024年第3期310-320,共11页Journal of Solid Rocket Technology

摘　　要：为了解固体火箭发动机在脉冲触发激励下的工作性能,设计了一种脉冲触发实验系统并开展实验研究,建立了脉冲触发内弹道模型。结果表明,实验系统压强抬升响应时间在25 ms以内,相较于延长段位置,发动机头部的压强扰动更大,扰动传播速度为1259 m/s;脉冲触发器峰值压强与发动机压强抬升预示误差均小于6%;延长段越长,脉冲触发产生的压强抬升越小;脉冲药量越大,压强抬升越大,脉冲药量与压强抬升呈近线性关系,药量从3 g增加到8 g,发动机压强抬升率从8.142%提升到31.594%;发动机压强抬升随脉冲触发器节流孔径的提升显著增大,孔径从1 mm增大到4 mm,压强抬升率从1.656%提升到了27.448%,壅塞作用导致1 mm的节流孔径无法达到脉冲触发效果;发动机压强抬升随着发动机喉径的增大而减小,喉径从12.50 mm提升到14.00 mm,压强抬升率从19.204%降低到了14.771%;对于本实验系统,触发时刻对发动机压强抬升影响小。In order to understand the working performance of solid rocket motors under pulse trigger excitation,a pulse trigger experimental system was designed and experiments were carried out,and a pulse trigger internal ballistics model was established.The results show that the pressure rise response time of the experimental system is within 25 ms.Compared with the extended section position,the pressure disturbance at the motor head is greater,and the disturbance propagation speed is 1259 m/s.The prediction errors between pulse trigger peak pressure and motor pressure rise are both less than 6%.The longer the extension section,the smaller the pressure rise caused by pulse triggering;the greater the pulse charge,the higher the pressure rise.The relationship between pulse charge and pressure rise is near linear,the increase of pulse charge from 3 g to 8 g,the motor pressure rise rate from 8.142% to 31.594%;the motor pressure rise increases significantly with the increase of throttling aperture of pulse trigger,the aperture increases from 1 mm to 4 mm,and the pressure rise rate increases from 1.656% to 27.448%.The choke effect causes that the throttling aperture of 1 mm cannot achieve the pulse trigger effect.The motor pressure rise decreases with the increase of the throat diameter,the throat diameter increases from 12.50 mm to 14.00 mm,and the pressure rise rate decreases from 19.204% to 14.771%.For the experimental system,the trigger time has little effect on the motor pressure rise.

关 键 词：脉冲触发 固体火箭发动机 内弹道 压强抬升 复合推进剂 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]