摘要
针对月地高速再入返回飞行器在轨面临长期中真空环境的特殊挑战,热控设计需要评估不同真空度下多层隔热组件的传热性能差异.采用一维绝热型边界测试方法,对5单元、10单元、15单元与20单元多层隔热组件,在0.001-10000 Pa开展了传热性能的实验研究.根据测试数据,计算了不同真空度下的当量导热系数,在整器热分析模型中优选当量导热系数来计算整器温度水平,并利用正样热平衡试验和在轨温度遥测值验证了该方法的正确性.本文的测试结果不仅可为返回器提供基础数据,还可成为多层隔热组件不同真空条件下航天器热设计、热分析的重要依据.
The high-speed reentry capsule of lunar spacecraft will face a weak vacuum environment long-term on orbit, thus the difference of heat-transfer capability of the multi-layer insulation blankets under different vacuum degrees should be evaluated in thermal design. In this article, an one-dimensional method of mesurement with adiabatic boundary condition was constucted to test the heat tranfer performance of multi-layer insulation blankets with 5, 10, 15 and 20 under 0.001-10000 Pa. Based on the test data, equivalent thermal conductivities of different vacuum degrees were calculated. The proper equivalent thermal conductivity is selected in the entire spacecraft thermal analyses, and this method is proved to be correct through thermal balance test and on orbit temperature telemetry. This work achieves not only basic data for reentry capsule, but also important fundation of thermal design and thermal analyse with multi-layer insultaion blankets in different vacuum degree.
出处
《中国科学：技术科学》
EI
CSCD
北大核心
2015年第3期263-267,共5页
Scientia Sinica(Technologica)
基金
国家中长期科技发展规划重大专项资助项目
关键词
多层隔热组件
真空度
传热性能
热控设计
当量导热系数
multilayer insulation, vacuum, thermal performance, thermal control, equivalent thermal conductivity
