升华器

多孔板水升华器在恒热流条件下的试验研究

Experimental Investigation on Porous Plate Water Sublimator under Constant Heat Flux

多孔板水升华器试验研究

An Experimental Investigation on Porous Plate Water Sublimator

水升华器用多孔板的物理特性研究

A Study on Physical Characteristics of Porous Plates for Water Sublimator

水升华器散热系统分析

Analysis of water sublimator heat rejection systems

憎水涂层多孔板对水升华器散热性能影响的实验研究

Experimental Research on the Effects of Hydrophobic Coating Porous Plates on Heat Dissipation of Water Sublimator

结论采用粉末烧结技术研制的多孔板的特性满足水升华器的性能要求。

Conclusion Porous plates developed by making use of sintered powder technology could meet requirements of performance of water sublimator .

目的探讨水升华器的关键部件&多孔板的研制方法，并对多孔板的主要物理特性参数进行研究。

Some operation modes of the porous plate water sublimator used in an EVA space suit thermal control system are discussed .

在该系统中，采用可调喷嘴、升华器、高、低压流量调节阀代替原系统中的蒸发器，并对该系统进行了理论循环分析。

In this system , an adjustable nozzle , sublimator , high-pressure regulating valve and low-pressure regulating valve are used to replace the conventional evaporator .

目的探讨水升华器用憎水涂层多孔板的实现方法，并对所研制的憎水涂层多孔板进行实验研究。

Objective To investigate the development method of hydrophobic coating porous plates for water sublimator and carry out an experimental study on hydrophobic coating porous plates .

方法在对水升华器用多孔板技术指标进行分析的基础上，利用粉末烧结技术，使用不同的材料，研制出了多孔板。

Method Technical parameters of porous plates used in water sublimator were analyzed . On the basis of this , porous plates made of different materials were developed by making use of sintered powder technology .

在对多孔板多孔结构进行简化假设的基础上，建立了相关的数学模型，来预测水升华器的工作模式和换热器表面的温度。

Based on some assumptions of porous plate structure , relevant mathematics models are established , which can be used to predict the operation mode of the sublimator and surface temperature of the heat exchanger .

研究结果表明，金属氢化物热泵能够满足宇航员出舱活动中的散热要求，其体积与水升华器相当，质量损失小，并且能够通过控制反应床的压力调节出口水温，可控性良好。

The numerical calculations show that a metal hydride pump system with comparable size as water sublimator and less mass loss can satisfy the cooling requirement of the astronaut during EVA process , and the temperature can be regulated by controlling the pressure of the hydride bed .