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首页> 外文会议>Second International Conference on Safety amp; Protective Fabrics, Apr 26-28, 2000, Arlington, VA >THERMAL INSULATION PERFORMANCE OF TEXTILE STRUCTURES FOR SPACESUIT APPLICATION AT MARTIAN PRESSURE AND TEMPERATURE
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THERMAL INSULATION PERFORMANCE OF TEXTILE STRUCTURES FOR SPACESUIT APPLICATION AT MARTIAN PRESSURE AND TEMPERATURE

机译：马氏体压力和温度下用于空间应用的纺织结构的隔热性能

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摘要

Protection of astronauts from the extreme temperatures in the space environment has been provided in the past using multi-layer insulation in ultra-high vacuum environments of low earth orbit and the lunar surface. For planetary environments with residual gas atmospheres such as Mars with ambient pressures between 8 to 14 hPa (8 to 14 mbar), new protection techniques are required because of the dominating effect of the ambient gas on heat loss through the insulation. At Mars ambient pressure levels, the heat loss can be excessive at expected suit external temperatures of 172 K with state-of-the-art suit insulation, requiring an active heat source and its accompanying weight and volume penalties. Micro-fibers have been identified as one potential structure to reduce the heat losses, but existing fundamental data on fiber heat transfer at low pressure is lacking for integrated fabric structures. This baseline study presents insulation performance test data at different pressures and fabric loads for selected polyesters and aramids as a function of fiber density, fiber diameter, fabric density, and fabric construction. A set of trend data of thermal conductivity versus ambient pressure is presented for each fiber and fabric construction design to identify the design effects on thermal conductivity at various ambient pressures, and to select a fiber and fabric design for further development as a suit insulation. The trend data also shows the pressure level at which thermal conductivity approaches a minimum, below which no further improvement is possible for a given fiber and fabric design. The pressure levels and resulting thermal conductivities from the trend data can then be compared to the ambient pressure at a planetary surface, Mars for example, to determine if a particular fiber and fabric design has potential as a suit insulation.
机译：过去，在低地球轨道和月球表面的超高真空环境中使用多层绝缘材料，可以保护宇航员免受太空环境中的极端温度的伤害。对于具有残余气体气氛（例如火星）且环境压力介于8到14 hPa（8到14 mbar）之间的行星环境，由于周围气体对通过绝热层的热损失起主要作用，因此需要新的保护技术。在火星的环境压力水平下，如果采用先进的西服保温材料，则在预期的西服外部温度为172 K时，热量损失可能会过大，这需要有源热源及其伴随的重量和体积损失。微纤维被认为是减少热量损失的一种潜在结构，但是对于集成的织物结构来说，缺乏有关低压下纤维热传递的现有基础数据。这项基线研究提供了选定的聚酯和芳纶在不同压力和织物载荷下的绝缘性能测试数据，该数据是纤维密度，纤维直径，织物密度和织物结构的函数。为每种纤维和织物结构设计提供了一组热导率与环境压力的趋势数据，以识别设计在各种环境压力下对热导率的影响，并选择一种纤维和织物设计作为西装隔热材料进行进一步开发。趋势数据还显示了热导率接近最小值时的压力水平，对于给定的纤维和织物设计，该压力水平无法进一步改善。然后可以将趋势数据中的压力水平和由此产生的热导率与行星表面（例如火星）处的环境压力进行比较，以确定特定的纤维和织物设计是否具有用作隔热材料的潜力。

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