固体火箭发动机壳体固化过程温度场影响因素分析  

Analysis of influencing factors on the temperature field during the curing processes of solid rocket motor cases

作　　者：宋孟奇 侯晓 沙宝林 SONG Mengqi;HOU Xiao;SHA Baolin(The 41st Institute of Fourth Academy of CASC, Xi'an 710025,China)

机构地区：[1]中国航天科技集团有限公司四院四十一所

出　　处：《固体火箭技术》2019年第4期523-528,共6页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(U1837601)

摘　　要：考虑固化反应热的影响和固化过程中复合材料物性参数的发展变化,以某Φ1400 mm固体火箭发动机壳体模型为基础,对复合材料固化过程中温度场进行了热化学耦合有限元分析,并与实验测量结果进行了对比;为了优化固化工艺,提高壳体制造水平,针对固化制度中的最高温度保温时间、固化温度偏差、对流传热系数等影响壳体固化过程温度场的因素进行了分析。结果表明,所建立的热化学耦合数值模型的计算结果与试验测量数据绝对误差率在6%以内,验证了该数值模型的可靠性;固化工艺偏差和对流传热系数波动都会对绝热层内壁温度产生非常大的影响;为保障绝热层的完全硫化,应适当延长固化制度的最高温度保温时间,使工艺安全系数提高到2倍左右。Considering the effect of curing reaction heat and the variation of physical properties of the composites during their curing process, the thermal-chemical coupling finite element analysis of temperature field during these processes has been carried out on a φ1400 mm solid rocket motor case model. The numerical calculations were compared with the experimental results. In order to optimize the curing process and improve the manufacturing level of the case, the analysis has been carried out on the factors affecting the temperature field during the curing process, such as the holding time of maximum temperature, curing temperature deviation and convective heat transfer coefficient. The results show that, absolute error between the thermal-chemical coupling numerical calculation results and the experimental results is less than 6%, so that the reliability of the numerical model is verified. Both the curing process deviation and the fluctuation of heat transfer coefficient have great effect on the inner surface temperature of the insulation layer. In order to ensure the complete vulcanization of the insulation layer, the holding time of the highest temperature should be appropriately prolonged, so as to increase the processing safety factor to about twice.

关 键 词：壳体 固化工艺 热化学耦合 温度场 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]