长尾喷管气凝胶隔热层结构设计  

Structural design of aerogel insulation layer forlong tail nozzle

作　　者：高煜航 郑健[1] 上官子晗 GAO Yuhang;ZHENG Jian;SHANGGUAN Zihan(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学机械工程学院,江苏南京210094

出　　处：《推进技术》2024年第5期166-175,共10页Journal of Propulsion Technology

摘　　要：固体火箭发动机长尾喷管外围通常放置舵机等控制系统,为了满足控制系统的工作温度要求,设计了一种用于长尾喷管段的新型热防护复合结构。长尾段隔热层采用具有低热导率、低密度特点的二氧化硅气凝胶材料。首先建立了气凝胶材料热导率计算模型,并对高温环境气凝胶材料导热性能进行测试。随后结合气凝胶材料热导率计算,建立了长尾喷管的热防护复合结构模型,并对喷管热防护结构模型进行了瞬态传热分析和力学性能分析。结果表明,喷管热防护结构设计满足材料力学性能。在发动机工作20 s后气凝胶材料可以将喷管的长尾段外壳壁面温度控制在320 K以下。相较于传统的高硅氧酚醛隔热材料,气凝胶材料隔热效果表现更优,且可以有效减少喷管热防护结构的消极质量。The control system such as steering gear is usually placed around the long tail nozzle of solid rocket motor.In order to meet the working temperature requirements of the control system,a new thermal protec⁃tion composite structure for the long tail nozzle section is designed.The long tail insulation layer adopts silica aerogel material with low thermal conductivity and low density.Firstly,the thermal conductivity calculation mod⁃el of aerogel materials was established,and the thermal conductivity of aerogel materials in high temperature en⁃vironment was tested.Then,combined with the thermal conductivity calculation of aerogel material,the thermal protection composite structure model of long tail nozzle was established,and transient heat transfer analysis and the mechanical properties of the nozzle thermal protection structure model were carried out.The results show that the nozzle thermal protection structure design meets the mechanical properties.After the engine working 20 s,the gas gel material can control the long-tail shell temperature of the nozzle below 320 K.Compared with the tradi⁃tional high silica phenolic insulation material,the aerogel material has better heat insulation effect and can effec⁃tively reduce the negative mass of the nozzle thermal protection structure.

关 键 词：固体火箭发动机 长尾喷管 热防护 二氧化硅气凝胶 传热 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]