长时间工作固体火箭发动机长尾喷管外绝热装置设计  

External insulation device design for long-tail nozzle oflong-time working solid rocket motor

作　　者：王相宇[1] 向进[1] 章惠君[2] 王鹍鹏[1] 余小波[1] 朱雯娟[1] 刘梦珂 马以博 WANG Xiangyu;XIANG Jin;ZHANG Huijun;WANG Kunpeng;YU Xiaobo;ZHU Wenjuan;LIU Mengke;MA Yibo(Hubei Institute of Aerospace Chemotechnology,Xiangyang 441003,China;China Airborne Missile Academy,Luoyang 471000,China)

机构地区：[1]湖北航天化学技术研究所,襄阳441003 [2]中国空空导弹研究院,洛阳471000

出　　处：《固体火箭技术》2024年第5期629-637,共9页Journal of Solid Rocket Technology

摘　　要：固体火箭发动机长尾喷管周围一般安装有电子仪器,故而对喷管壳体表面温度有严格的限制。对于某长时间工作的发动机,为满足喷管壳体表面温度要求,同时降低消极质量,设计了一种新型双腔外绝热装置,以实现在较小的消极质量下具有较好的绝热性能。对该绝热装置进行了内流场及传热计算分析,而后进行了绝热结构优化及试验验证。结果表明:该双腔外绝热装置可以将长时间工作固体火箭发动机长尾喷管外壁温度从483℃降低至103℃,降低约78.7%;而采用同等材料同等质量的常规外防护装置只能从483℃降低至227℃,降低约53.0%;而要达到相同的防护效果,同等材料常规外防护装置的质量将增加约160%。双腔外绝热装置中段及尾端处温度随时间变化趋势与实测结果吻合较好,有望应用于其他长时间工作发动机。Electronic instruments are usually installed around the long-tail nozzle of a solid rocket motor(SRM)with strictly limits the surface temperature of nozzle shell.For a long-time working SRM,in order to meet the requirements of the nozzle shell surface temperature,while reducing the negative mass,a new double-cavity external insulation device was designed,which has better thermal insulation performance under less negative mass.The internal flow field and heat transfer of this insulation device were calculated and analyzed,and then the insulation construction was optimized and tested.The results show that outer shell temperature of long-tail nozzle of the long-time working SRM is reduced from 483℃to 103℃,a decrease of about 78.7%.However,the conventional external protection device with the same material and the same mass can only reduce the temperature from 483℃to 227℃,about 53.0%lower;To achieve the same protection effect,mass of the conventional external insulation device with same material will be increased by about 160%.The changing trend of temperature with time at the middle and tail section of double-cavity external insulation device is in good agreement with the test data.This double-cavity external insulation device can also be applied to other long working time solid rocket motors.

关 键 词：固体火箭发动机 长时间工作 长尾喷管 外绝热装置 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]