航天器变密度多层绝热变工况漏热特性研究

航天器的热控技术在空间应用中至关重要。以探月需求为背景,基于逐层计算法建立了航天器多层绝热材料性能仿真模型,并通过实验进行了验证。对用内热外冷模型变密度填充方式改善多层绝热性能的机制和改善幅度进行了研究。结果表明变密度多层绝热相对于均匀密度多层绝热的漏热量可以减少37.3%。分析了冷边界温度、热边界温度和真空度等因素对绝热性能的影响。     

液氢用低温复合多层绝热材料的传热特性研究

基于液氢高效储运对低温绝热的需求,将液氢温区复合多层绝热材料(包含泡沫材料与多层绝热材料)作为研究对象,通过Layer-by-Layer模型构建复合多层绝热材料层间温度分布数值模型,分析了热通量随热边界温度、真空度与总层数变化规律。结果表明,热通量随着热边界温度的升高而增大,靠近冷边界区域的多层绝热材料承担了主要的绝热功能。随后对不同组合模式改变真空度下传热特性进行分析,发现相较于多层绝热材料,添加泡沫材料热通量减少20.76%。此外,复合多层绝热材料中多层绝热材料总层数的增加可以有效抑制热通量增加,综合考虑性能成本,在总层数为50层时抑制效果达到最佳,此时热通量为0.537 7 W/m²。     

空间燃料贮箱变密度多层绝热结构传热性能研究

为了探究变密度多层绝热结构VDMLI层间结构布置对绝热性能的影响,对火箭低温推进剂储罐外的VDMLI结构建立了传热数学模型,并开展了变工况分析,揭示了不同影响因素,包括热边界温度、层数、层密度等对VDMLI绝热性能的影响。研究发现,热边界温度对VDMLI绝热性能以及温度分布有主要影响;层数在40—60即可满足漏热量要求并且整个绝热结构的质量较轻;变密度结构(VDMLI)比定密度(MLI)具有更轻的重量和较好的绝热效果,从内由外依次是低、中、高密度区,且最优变密度分配比例为低密度区层数占总层数的20%,高密度区约占40%,中密度区占33%—36%。研究内容为VDMLI的实际布置提供了可靠的理论支持。     

低温推进剂贮箱绝热性能实验研究

针对低温推进剂长时间在轨贮存的要求,搭建了绝热系统地面验证测试装置。本测试装置通过维持高真空及恒壁面温度条件,可以较好地模拟在轨条件;通过贮箱颈管处设置的温度补偿器,有效的屏蔽掉颈管导热漏热。测试装置可实时监测系统中的真空度及壁面温度变化,可对贮箱蒸发排出气体流量和绝热系统不同位置的温度分布进行测量。针对10 mm硬质聚氨酯泡沫和30层多层绝热的复合绝热系统,在真空度2×10-3Pa,冷热壁面温度分别为96 K和313 K条件下,测得液氮日蒸发率为0.210%,折算液氧日蒸发率为0.156%。     

液氢箱蒸气冷却屏/仲-正转化复合结构绝热性能预测

为探析蒸气冷却屏中仲-正转化释冷对于液氢贮箱绝热性能的提升效果，建立了设置仲-正绝热转化室的VD-MLI/VCS二维模型。对复合绝热结构的传热规律和绝热性能开展了多角度分析。研究发现：仲-正转化室布置在VCS管长50%处时绝热效能最佳，贮箱漏热为0.101 W·m^-2，相比不设置仲-正转化室减少了7.17%；绝热设计中，调整VCS位置能最多减少54.17%漏热损失，相比调整仲-正转化室位置效果更显著；沿冷蒸气流动方向，漏热量先升高、再降低，随后再次升高；增加仲-正转化室可提升VCS出口侧的绝热效果，使贮箱各处绝热性能更加均匀。该研究为液氢贮箱的复合绝热结构设计提供更加准确的理论依据和技术支撑。     

干式量热器测量隔热结构热性能实验研究

设计搭建一套基于两级G-M制冷机的圆筒形干式量热器装置,首先分析铜制和铝制量热杆对装置误差的影响,其次对3组不同的隔热结构进行热性能实验测试,并研究不同的边界温度对隔热结构热性能的影响。实验结果表明,铝制量热杆测量误差更小;在高真空环境下,隔热泡沫对复合结构的绝热性能影响不大,MLI或者VDMLI起主要绝热作用;分别改变冷边界温度和热边界温度对隔热结构热性能的影响不同,热边界温度一定,冷边界温度由20 K增大到100 K时,通过隔热结构的热流密度略有减小;冷边界温度一定,热边界温度由300 K增大到350 K时,通过隔热结构的热流密度急剧增大。     

低温贮箱SOFI/VD-MLI结构传热分析

针对聚氨酯泡沫与变密度多层组合绝热(SOFI/VD-MLI)结构传热特性分析,确定了满足地面及空间阶段液氮、液氧、液态甲烷贮箱漏热量要求的SOFI/VD-MLI组合绝热结构最小厚度为117mm,其中SOFI为77 mm,VD-MLI为40 mm。分析表明,在满足漏热量要求时,SOFI/VD-MLI组合绝热结构中SOFI厚度大于VD-MLI厚度;随着冷端温度降低,SOFI厚度明显增加,VD-MLI厚度基本保持不变,且空间阶段热端温度223 K对应的SOFI厚度变化量明显大于空间阶段热端温度323 K;随着空间阶段热端温度升高,SOFI厚度逐渐减小,VD-MLI厚度逐渐增加,但SOFI/VD-MLI组合绝热结构总厚度基本维持不变。同时,从质量经济性角度对贮箱SOFI/VD-MLI组合绝热结构进行分析,结果表明,满足地面及空间阶段液氮、液氧、液态甲烷贮箱漏热量要求的SOFI/VD-MLI组合绝热结构单位面积质量为5.022 kg,且单位面积质量受SOFI厚度影响较大,VD-MLI厚度影响较小。     

低温推进剂贮箱气冷屏复合绝热结构综合优化设计

气冷屏复合绝热(VSC)结构可以有效减少低温推进剂蒸发损耗。目前尚缺乏对气冷屏复合绝热结构的综合优化设计,现有的研究方法不能准确反映出漏热量与多层变密度材料导热性能及冷屏屏位之间的关系。为此,考虑多层变密度材料导热系数随冷屏位置的变化,对复合绝热结构进行综合优化设计,研究冷屏位置和多层变密度结构的相互影响规律,分析了最佳层密度与最佳屏位。结果表明,加入气冷屏后,降低中密度区层密度,增加高密度区层密度可以进一步减少漏热量。对于不同的层密度组合,存在一个最佳屏温,当冷屏处于该温度时漏热量最小。     

低温推进剂贮箱大面积冷屏热分析及成本优化

运载火箭低温贮箱采用大面积冷屏与多层隔热材料组成的复合结构可以有效减少低温推进剂蒸发损耗,延长低温推进剂在轨贮存时间。通过建立多层隔热材料耦合90 K大面积冷屏的传热模型,获得了引入大面积冷屏后对多层隔热材料层间温度分布及热流密度影响的变化规律,对比了采用冷屏技术和直接对液氢采用主动制冷两种方式,同等条件下采用冷屏在主动制冷系统重量和功耗方面可分别节省60%和64%。研究了低温推进剂不同在轨贮存时间和冷屏安装在多层隔热材料中不同位置时热管理系统重量和功耗成本,以成本最小为目标获得了90 K冷屏布局最优化设计方法。     

低温贮箱聚氨酯泡沫塑料分层绝热模型与机理分析

讨论和建立了低温贮箱的聚氨酯泡沫塑料低温分层绝热模型，在机理分析的基础上给出了分层绝热的最佳层数计算公式。所提出的最佳层数与实验结果完全吻合，为低温贮箱的绝热施工提出了新工艺。     

变密度多层绝热的理论分析

讨论了一种新型的多层绝热结构,针对径向内外侧不同层间辐射阻断的强弱比例特征、材料重量、以及结构强度,对多层材料的布置进行了优化设计.主要分析多层绝热的绝热性能随层密度分布的变化规律,寻找特定条件下最优化层密度的分布方式,并研究了最优化层密度分布方式与绝热系统各参数之间的关系.     

Cryogenic propellant liquefaction and storage for a precursor to a human Mars mission

An analysis of cryogenic liquefaction and storage methods for in-situ produced propellants (oxygen and methane) on Mars is presented. The application is to a subscale precursor sample return mission, intended to demonstrate critical cryogenic technologies prior to a human mission. A heat transfer analysis is included, resulting in predicted cryogenic tank surface temperatures and heat leak values for different conditions. Insulation thickness is traded off against cryocooler capacity to find optimum combinations for various insulation configurations, including multilayer insulation and microspheres. Microsphere insulation is shown to have promise, and further development is recommended.     

Wrapped multilayer insulation design and testing

New vehicles need improved cryogenic propellant storage and transfer capabilities for long duration missions. Multilayer insulation (MLI) for cryogenic propellant feedlines is much less effective than MLI tank insulation, with heat leak into spiral wrapped MLI on pipes 3–10 times higher than conventional tank MLI. Better insulation for cryogenic feed lines is an important enabling technology that could help NASA reach cryogenic propellant storage and transfer requirements. Improved insulation for Ground Support Equipment could reduce cryogen losses during launch vehicle loading. Wrapped-MLI (WMLI) is a high performance multilayer insulation using innovative discrete spacer technology specifically designed for cryogenic transfer lines and Vacuum Jacketed Pipe (VJP) to reduce heat flux.The poor performance of traditional MLI wrapped on feed lines is due in part to compression of the MLI layers, with increased interlayer contact and heat conduction. WMLI uses discrete spacers that maintain precise layer spacing, with a unique design to reduce heat leak. A Triple Orthogonal Disk spacer was engineered to minimize contact area/length ratio and reduce solid heat conduction for use in concentric MLI configurations.A new insulation, WMLI, was developed and tested. Novel polymer spacers were designed, analyzed and fabricated; different installation techniques were examined; and rapid prototype nested shell components to speed installation on real world piping were designed and tested. Prototypes were installed on tubing set test fixtures and heat flux measured via calorimetry. WMLI offered superior performance to traditional MLI installed on cryogenic pipe, with 2.2 W/m² heat flux compared to 26.6 W/m² for traditional spiral wrapped MLI (5 layers, 77–295 K). WMLI as inner insulation in VJP can offer heat leaks as low as 0.09 W/m, compared to industry standard products with 0.31 W/m. WMLI could enable improved spacecraft cryogenic feedlines and industrial hot/cold transfer lines.     

Study on the heat transfer of high-vacuum-multilayer-insulation tank after sudden, catastrophic loss of insulating vacuum

One of the worst accidents that may occur in a high-vacuum-multilayer-insulation (HVMLI) cryogenic tank is a sudden, catastrophic loss of insulating vacuum (SCLIV). There is no doubt that the gases leaking into the insulation jacket have some influence on the heat transfer process of it. However, this issue has not been thoroughly studied so far. In this paper, a test rig was built up and experiments were conducted using a SCLIV cryogenic tank and with nitrogen, helium and air as the working medium, respectively. The venting rates of the tank and temperature in the insulation jacket were measured respectively after the three different gases leaking into the jacket. A heat transfer model describing the heat transfer process of a SCLIV tank was also presented. The calculated results using this model were compared against the experimental data. It is found that the heat transfer performance of the HVMLI cryogenic tank after SCLIV is strong relevant to the type of gas leaking into the insulation jacket.     

有效导热系数对低温容器日蒸发率的影响

低温容器是气体液化分离加工工业中的重要设备，绝热设计是低温容器设计的重要组成部分，它直接影响低温容器的日蒸发率。在不同的绝热材料和一定漏热温差的条件下，给出了普通绝热和真空粉末绝热型低温容器的日蒸发率与热材料的有效导热系数以及绝热层厚度之间的关系曲线。为简化设计和比较低温容器的特性提供方法和依据。     

Passive ZBO storage of liquid hydrogen and liquid oxygen applied to space science mission concepts

Liquid hydrogen and oxygen cryogenic propulsion and storage were recently considered for application to Titan Explorer and Comet Nuclear Sample Return space science mission investigations. These missions would require up to 11 years of cryogenic storage. We modeled and designed cryogenic propellant storage concepts for these missions. By isolating the propellant tank’s view to deep space, we were able to achieve zero boil-off for both liquid hydrogen and oxygen propellant storage without cryocoolers. Several shades were incorporated to protect the tanks from the sun and spacecraft bus, and to protect the hydrogen tank from the warmer oxygen tank. This had a dramatic effect on the surface temperatures of the propellant tank insulation. These passive storage concepts for deep space missions substantially improved this application of cryogenic propulsion. It is projected that for missions requiring larger propellant tank sizes, the results would be even more dramatic.     

Launch ascent testing of a representative Altair ascent stage methane tank

In order to support long duration cryogenic propellant storage, the NASA is investigating the long duration storage properties of liquid methane. The Methane Lunar Surface Thermal Control (MLSTC) testing is using a tank of the approximate dimensions of the Altair lunar ascent propellant tanks. The tank was insulated with multilayer insulation and placed inside of a vacuum chamber to simulate the various environments that would be encountered during launch and travel from the earth to the lunar surface, including long duration stays on the lunar surface. One of these environments to be studied is the launch and ascent environment; while all the effects of this mission phase cannot be simulated at the same time, an effort was made to simulate as many as possible. Boil-off testing included ambient pressure ground hold testing followed by a rapid depressurization of the vacuum chamber during which the liquid methane tank was allowed to come to steady state condition in the high vacuum environment. The data gathered from the series of tests fit with-in pre-test predictions and yielded much needed test data for rapid depressurization using liquid methane.     

高真空多层绝热低温容器完全真空丧失后传热及绝热夹层内温度分布规律实验

在搭建了高真空多层绝热低温容器完全真空丧失传热研究实验台的基础上,分别利用干燥氮气、二氧化碳、氧气、氦气及空气为破空介质,进行了高真空多层绝热低温容器发生完全真空丧失事故后的传热实验研究.实验中通过流量计和温度采集系统测得了高真空多层绝热低温容器在发生完全真空丧失事故后的排放率和绝热夹层内的温度分布规律.实验结果表明,...     

20000m~3双层金属低温液体贮罐的设计

介绍20000m3双层金属低温液体贮罐的主要设计参数、外形结构和设计程序,阐述了内罐、保冷措施、外罐以及阀门和仪表等的设计方案和特点。     

大型低温液体贮罐日蒸发率攻关及测试总结

针对林德公司对大型低温液体贮罐日蒸发率的高要求,联合国内制造商进行技术攻关,选择质量符合要求的保温材料,根据国产保温材料的参数修改贮罐的设计参数。按照国内相关规范对2000m3液氧贮罐进行日蒸发率实际测试,其结果达到林德公司的标准。