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首页> 外文会议>11th annual international energy conversion engineering conference >Numerical Analysis for Multi-layer Insulation (MLI) Effect on Spacecraft Thermal Control System
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Numerical Analysis for Multi-layer Insulation (MLI) Effect on Spacecraft Thermal Control System

机译：多层绝缘对航天器热控制系统影响的数值分析

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摘要

The thermal control system (TCS) is an integral part of spacecraft. Its purpose is to maintain all the components of a spacecraft within their respective temperature limits. Considering orbital position and attitude of spacecraft, different sources of thermal energy acting on a spacecraft; solar radiation, Albedo, earth emitted infrared, and heat generated by onboard equipment. Therefore, the thermal control system is different for every spacecraft. In general, there are two types of TCS, passive and active. Multi-layer insulation (MLI) is considered as a passive type. MLI closely spaced layers of aluminized Mylar or Kapton alternated with a course net material. Insulation reduces the rate of heat flow per unit area between two boundary surfaces and prevents a large heat influx. SC model in Low Earth Orbit (LEO) is created by thermal desktop program, in order to launch a parametric study to check design of thermal control elements ( Radiators , Heaters , MLI ) by calculating the temperature field along the equipment panel and verify that the maximum and minimum temperature of the lower sheet of the panel is within the design range of temperature from 0℃ up to 35℃ .Verifying the optimum selection of the power of heaters and the correct distribution of them along the panel zones is performed.
机译：热控制系统（TCS）是航天器的组成部分。其目的是将航天器的所有组件保持在各自的温度范围内。考虑到航天器的轨道位置和姿态，作用于航天器的不同热能来源；太阳辐射，反照率，地球发射的红外线以及船上设备产生的热量。因此，每个航天器的热控制系统都不同。通常，TCS有两种类型，被动和主动。多层绝缘（MLI）被认为是无源类型。 MLI紧密间隔的镀铝聚酯薄膜或Kapton层与球网材料交替排列。隔热降低了两个边界表面之间的每单位面积的热流速率，并防止了大量的热流入。低地球轨道（LEO）中的SC模型是通过热桌面程序创建的，目的是启动参数研究，以通过计算设备面板上的温度场来检查热控制元件（散热器，加热器，MLI）的设计，并验证面板下层板的最高和最低温度在0℃至35℃的设计温度范围内。验证加热器功率的最佳选择以及它们在面板区域的正确分布。

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