摘要
根据某探测器的具体结构及工作条件,分析和计算探测器上火箭发动机的热环境参数.利用有限元法计算火箭发动机固壁辐射热流密度,依据热流边界条件设计热防护方案;利用有效发射率表征多层隔热材料隔热性能并进行温度场数值仿真.由于多层隔热材料性能参数的不易确定性,计算了参数在较大范围内的热防护效果.通过仿真计算验证热防护方案的有效性和可靠性,并分析影响热防护效果的主要因素;计算结果表明多层隔热材料的有效发射率是影响隔热性能最重要的因素,比热容、表面发射率、密度对热防护性能影响很小.
Heat environment parameters of rocket motor were analyzed and computed based on structure and work condition of certain detector.Solid radiation heat flux of rocket motor was computed by finite element method,and thermal protection scheme was designed according to heat flux boundary condition.Multilayer insulation material performance was expressed by equivalent emissivity and temperature field was simulated.As the performance parameters are difficult to determine,the temperature field was computed in wide parameter range.Efficiency and reliability of thermal protection scheme were validated and primary influential factors to thermal protection performance were analyzed,providing a theoretical basis for design and selection of thermal protection scheme.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第6期1407-1411,共5页
Journal of Aerospace Power
关键词
火箭发动机
辐射热流密度
多层隔热材料
热防护
数值仿真
rocket motor
radiation heat flux
multilayer insulation material
thermal protection
numerical simulation
