摘要
低温多层隔热组件作为重要的航天器热控产品之一,通常用于舱内设备的隔热,以及减少航天器舱板、舱外设备等与外部空间的辐射换热,它在热控分系统产品配套的质量占比也较为可观。随着大型航天器向高性能、高载质比等方向发展,热控产品的减重需求日益突出。针对减重需求所开发的轻型低温多层隔热组件,反射屏采用了双面镀铝聚酯凸纹薄膜,兼顾了反射屏与间隔层的隔热功能,从而实现了结构优化。针对这种新型轻质多层的隔热性能,开展了试验研究,辅助以仿真计算验证,并通过在轨飞行数据进一步验证其有效性。结果表明:在相同的试验条件下,轻质多层的当量辐射率相较于传统多层提高了约30%,质量降低了约35%;适当考虑不确定度,参数取值0.03合理,隔热性能较好,满足大多数航天器使用要求,可作为轻量化的隔热材料在宇航领域广泛推广应用。
As one of the important thermal control products for spacecraft,low-temperature multilayer insulation blankets are usually used for thermal insulation of the equipment inside the cabin and to reduce the radiation heat transfer between the spacecraft cabin panel,extravehicular equipment and external space.The Multilayer Insulation Blanket(MLI)accounts for a considerable proportion of the weight of the whole thermal control subsystem.With the development of large spacecraft towards high performance and high payload-mass ratio,the demand for weight reduction of thermal control products is increasingly prominent.A lightweight low-temperature multilayer insulation blanket is developed for the purpose of weight reduction using double-sided aluminized polyester convex film as the reflection barrier,while thermal insulation functions of both the reflection barrier and the separation layer have been taken into account.Thus the structure of the MLI is optimized.An experimental method is designed to conduct experimental research on the thermal insulation performance of the lightweight multilayer,and verified by simulation calculations,while the effectiveness can be proved further by in-orbit flight data.The results show that under the same experimental conditions,the equivalent emissivity of the lightweight multilayer increases by about 30%compared with the traditional multilayer,while the weight reduces by 35%.Appropriately considering uncertainty,the parameter value of 0.03 can be reasonable.The thermal insulation performance of the new lightweight multilayer blankets is fairly good and can meet requirements of most spacecraft.The lightweight multilayer blankets could be widely used in the aerospace field as lightweight heat insulation materials.
作者
李进
周晓云
赵啟伟
毛俊俊
LI Jin;ZHOU Xiaoyun;ZHAO Qiwei;MAO Junjun(National Key Laboratory of Spacecraft Thermal Control,Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)
出处
《航天器工程》
CSCD
北大核心
2024年第3期54-60,共7页
Spacecraft Engineering