Preliminary characterization of carbon dioxide transfer in a hollow fiber membrane module as a possible solution for gas–liquid transfer in microgravity conditions

In microgravity, one of the major challenge encountered in biological life support systems (BLSS) is the gas–liquid transfer with, for instance, the necessity to provide CO₂ (carbon source, pH control) and to recover the evolved O₂ in photobioreactors used as atmosphere bioregenerative systems.     

某型无人机导轨起飞装置气液压能源系统的应用

介绍了以气囊式蓄能器和液压缸为主构成的某型无人机导轨发射装置的气液压能源系统，并对气囊式蓄能器和液压缸的动态参数特性及其匹配关系进行了理论分析计算和动态特性试验。计算和试验结果表明，该气液压能源系统所确定的气液压能转换成机械能后能够满足无人机起飞所需的动力，并在某型无人机导轨发射装置中得到了工程应用。     

1.5级涡轮前后轮缘密封封严流动特性研究

为了研究前后腔轮缘密封封严特性和封严出流与主流的交互作用,对转静叶片之间带有前后封严腔的1.5级涡轮进行了三维定常数值模拟,研究了不同封严流量下前后封严腔出口处流场分布并采用附加变量法对比分析了前后腔轮缘密封效率。结果表明：前封严腔主流燃气入侵位置主要受到来自上游导叶尾迹的影响,后封严腔主流燃气入侵位置主要受到下游导叶前缘位势场影响;封严出流影响了20%叶高以下的主流区域,增大了轮毂二次流强度;采用相同封严流量下时前封严腔的封严效率较后腔更低且有着更大的封严效率波动。     

弹射动力系统燃气发生器流热固耦合数值研究

为了判断弹射动力系统燃气发生器工作的安全性,需要预示工作过程中燃气发生器壳体的力学响应。基于软件CFX和ANSYS,建立了燃气发生器复合结构流热固耦合仿真模型。对燃气发生器内流场和结构温度场进行流热耦合计算,并将壳体温度场计算结果与试验数据进行对比,再将算得的燃气压强分布与结构温度场分布导入ANSYS以计算结构的力学响应。计算结果表明,燃气发生器工作过程中,直筒段最高温度点位于直筒段与后封头连接的绝热层缝隙处,后封头最高温度点位于后封头与喉衬配合部位的上游端。结构最高温度值仅354K,说明热防护良好;直筒段和后封头壳体主体区域应力安全系数>3,满足设计要求,而在法兰附近圆角过渡处外壁存在应力集中,最大应力处安全系数降为1.13,燃气发生器壳体仍处于安全状态,但存在安全裕度显著降低的风险。     

国外GAP推进剂研制现状

综述了缩水甘油叠氮聚醚(GAP)及其推进剂的热、力学及弹道性能,GAP推进剂有较高的燃速和能量,但其燃速压强指数和温度敏感系数偏高。GAP推进剂的力学性能较差,改性GAP和支化GAP更具吸引力。GAP推进剂可用于燃气发生剂、微烟推进剂、高能推进剂及改性双基推进剂。     

Comparative study of productivity of the Rosetta target Comet 67P/Churyumov-Gerasimenko

In an attempt to evaluate correlations between several properties of comets we report the results of a cometary research involving a criterious analysis of gas and dust mass production rates in Comets 67P/Churyumov-Gerasimenko (main target of Rosetta Mission), 1P/Halley, Hyakutake (C/1996 B2), and 46P/Wirtanen and make a comparison between them.     

火星进入气体辐射加热研究进展

针对飞行器进入火星大气时气体辐射加热对防热设计带来不确定性，在简述火星探测和气体辐射研究的发展历程的基础上，对火星进入气体辐射加热研究的进展进行综述。首先，针对火星大气环境描述了气体辐射加热的概念和问题由来。其次，重点综述了近年来火星进入气体辐射加热基础模型的数值和试验研究进展，其中包括：热化学非平衡气体动力学、气体辐射特性和辐射传输的计算模型与方法等数值研究；地面测试设备、试验技术和模拟火星大气环境的气体辐射测量与验证等试验研究。再次，综述了流动辐射耦合和后体气体辐射加热等火星进入器设计方面开展的研究。最后，对未来火星进入气体辐射加热研究进行了展望，提出了研究建议。     

Low Velocity Collisions and the Growth of Planetesimals

The physics of low velocity collisions (5 m/s to 40 m/s) between basalt bodies ranging in size from 1 m to 10 km is studied in an effort to investigate the early phases of planetesimal accretions. To assess the importance of the internal structure of planetesimals on the outcome of the collisions, we model them either as solid spheres or as rubble piles with a filling factor of 0.5. The collisions are simulated using a three dimensional Smooth Particle Hydrodynamics (SPH) code that incorporates the combined effects of material strength and a brittle fragmentation model. This approach allows the determination not only of the mass of the largest fragments surviving the collisions but also their dynamical characteristics. We find that low velocity collisions are for equal incoming kinetic energy per gram of target material considerably more efficient in destroying and dispersing bodies than their high velocity counterparts. Furthermore, planetesimals modeled as rubble piles are found to be characterized by a disruption threshold about 5 times smaller than solid bodies. Both results are a consequence of a more efficient momentum transfer between projectile and fragments in collisions involving bodies of comparable sizes. Size and shape dependent gas drag is shown to provide relative collision velocities between similar meter-sized objects well in excess of the critical disruption threshold of either rubble piles or solid bodies. Unless accretion can proceed avoiding collisions between bodies of similar masses, the relative weakness of bodies in this size range creates a serious bottleneck for planetesimal growth. This revised version was published online in June 2006 with corrections to the Cover Date.     

Experimental comparison between aircraft fuel tank inerting processes using NEA and MIG

Fuel tank inerting technologies are able to reduce the fire risk by injection of inert gas into the ullage or fuel, the former called ullage washing and the latter fuel scrubbing. The Green On-Board Inert Gas Generation System (GOBIGGS) is a novel technology based on flameless catalytic combustion, and owning to its simple structure and high inerting efficiency, it has received a lot of attentions. The inert gas in the GOBIGGS is mainly comprised of CO₂, N₂, and O₂ (hereinafter, Mixed Inert Gas (MIG)), while that in the On-Board Inert Gas Generation System (OBIGGS), which is one of the most widely used fuel tank inerting technologies, is Nitrogen-Enriched Air (NEA). The solubility of CO₂ is nearly 20 times higher than that of N₂ in jet fuels, so the inerting capability and performance are definitely disparate if the inert gas is selected as NEA or MIG. An inerting test bench was constructed to compare the inerting capabilities between NEA and MIG. Experimental results reveal that, if ullage washing is adopted, the variations of oxygen concentrations on the ullage and in the fuel are nearly identical no matter the inert gas is NEA or MIG. However, the ullage and dissolved oxygen concentrations of MIG scrubbing are always higher than those of NEA scrubbing.     

Cometary Deuterium

Deuterium fractionations in cometary ices provide important clues to the origin and evolution of comets. Mass spectrometers aboard spaceprobe Giotto revealed the first accurate D/H ratios in the water of Comet 1P/Halley. Ground-based observations of HDO in Comets C/1996 B2 (Hyakutake) and C/1995 O1 (Hale-Bopp), the detection of DCN in Comet Hale-Bopp, and upper limits for several other D-bearing molecules complement our limited sample of D/H measurements. On the basis of this data set all Oort cloud comets seem to exhibit a similar ratio in H₂O, enriched by about a factor of two relative to terrestrial water and approximately one order of magnitude relative to the protosolar value. Oort cloud comets, and by inference also classical short-period comets derived from the Kuiper Belt cannot be the only source for the Earth's oceans. The cometary O/C ratio and dynamical reasons make it difficult to defend an early influx of icy planetesimals from the Jupiter zone to the early Earth. D/H measurements of OH groups in phyllosilicate rich meteorites suggest a mixture of cometary water and water adsorbed from the nebula by the rocky grains that formed the bulk of the Earth may be responsible for the terrestrial D/H. The D/H ratio in cometary HCN is 7 times higher than the value in cometary H₂O. Species-dependent D-fractionations occur at low temperatures and low gas densities via ion-molecule or grain-surface reactions and cannot be explained by a pure solar nebula chemistry. It is plausible that cometary volatiles preserved the interstellar D fractionation. The observed D abundances set a lower limit to the formation temperature of (30 ± 10) K. Similar numbers can be derived from the ortho-to-para ratio in cometary water, from the absence of neon in cometary ices and the presence of S₂. Noble gases on Earth and Mars, and the relative abundance of cometary hydrocarbons place the comet formation temperature near 50 K. So far all cometary D/H measurements refer to bulk compositions, and it is conceivable that significant departures from the mean value could occur at the grain-size level. Strong isotope effects as a result of coma chemistry can be excluded for molecules H₂O and HCN. A comparison of the cometary ratio with values found in the atmospheres of the outer planets is consistent with the long-held idea that the gas planets formed around icy cores with a high cometary D/H ratio and subsequently accumulated significant amounts of H₂ from the solar nebula with a low protosolar D/H. This revised version was published online in June 2006 with corrections to the Cover Date.