纳米CuCr2O4在HTPB复合推进剂中应用的安全性及燃烧机理

为提高纳米CuCr₂O₄(n-CuCr₂O₄)燃烧效能，阐明其促进HTPB复合推进剂燃烧的机理，研究了n-CuCr₂O₄分散方法，探讨了n-CuCr₂O₄对复合推进剂安全性和燃烧性能的影响。结果表明，癸二酸二异辛酯(DOS)可使n-CuCr₂O₄颗粒充分分散，颗粒粒径为50 nm。将DOS与乙酸乙酯混合作为分散液，n-CuCr₂O₄/分散液为12/100,超声分散30 min, n-CuCr₂O₄可以有效分散，使推进剂燃速提高1.5%。在含量均为2.5%时，含n-CuCr₂O₄推进剂的燃速虽然低于含卡托辛的，但是摩擦感度和撞击感度均降低。与微米CuCr₂O₄相比，n-CuCr₂     

AZO改性Y2O3-ZnO-Al2O3热控涂层性能分析

为解决铝合金表面液相等离子体电解氧化（PEO）涂层（Y₂O₃-ZnO-Al₂O₃）导电性差而导致的静电效应,对其进行表面改性处理。采用原子层沉积（ALD）技术在铝合金表面PEO涂层原位沉积铝掺杂氧化锌（AZO）导电薄膜以提高PEO涂层的导电性。对AZO改性PEO涂层的相组成和表面微观结构进行分析;对不同沉积温度下所得复合涂层的电阻率、载流子浓度和迁移率,以及沉积前后的热控性能、耐腐蚀性进行测量分析。结果表明:AZO导电薄膜均质连续致密地沉积在PEO涂层表面;当沉积温度为150 ℃时,AZO@Y₂O₃-ZnO-Al₂O₃复合涂层的电阻率为1.15×10-4 Ω·cm,载流子浓度为1.8×1020 cm-3,太阳吸收比为0.409,发射率为0.892,且抗电化学腐蚀性能良好,能够满足航天器热控涂层在空间环境应用的技术要求。     

基于深度学习的日间逐小时地表PM2.5浓度反演

以长三角地区作为研究区域,提出了使用深度学习算法来实现主被动遥感数据结合反演地表PM_2.5浓度的方法。基于MPL观测数据,使用雾霾层高度(HLH)替换了边界层高度(BLH)特征,对已有的基于气溶胶光学厚度(AOD)结合大气BLH来反演PM_2.5浓度的算法进行了改进。为提高数据覆盖率,对研究区域内的MAIAC AOD进行了填补与评估。利用多种机器学习算法实现了日间逐小时的PM_2.5浓度估算,模型验证相关性最高可达0.87。该方法能够为观测气候变化、应对大气污染提供有效帮助。     

基于同轴线的传输/反射法测量射频材料的电磁参数

射频功能材料电磁参数的测量对于微波电路设计和吸波隐身材料的研究具有重要意义。本文基于传输/反射法测量原理,利用矢量网络分析仪和同轴夹具组成的测试系统对聚氯乙烯、聚丙烯、聚甲醛、铁氧体及介电型吸波材料的电磁参数在10MHz4GHz频段内进行了测算。论证了Nicolson算法中的厚度谐振、多值性和相角跳变等问题,借助网络分析仪的扫频技术解决了多值性的问题,并对系统测量不确定度进行了分析。证明了厚度谐振问题对于高损耗型受试材料不会出现,因此传输/反射法尤其适于吸波材料的电磁参数测试。     

稀土Dy掺杂In2S3电子结构第一性原理计算研究

磁性离子取代半导体基质阳离子而形成的稀磁半导体材料因兼具磁性和半导体特性而受到广泛关注。硫化铟结构中存在大量空位利于客体离子掺杂,成为理想的主体材料。稀土离子因具有特殊的4f和4f5d能级以及电荷跃迁态结构,成为了合适的掺杂剂。本文采用基于密度泛函理论的第一性原理方法,对理想In₂S₃体系和稀土元素Dy掺杂体系的能带结构和态密度进行了详细计算和系统分析,为自旋电子器件的发展奠定了理论基础。     

基于OCO-2卫星遥感数据的三峡库区XCO2时空特征演变分析

定量分析三峡库区大气二氧化碳柱浓度混合比(XCO₂)演变趋势及空间分布,能有效探究水电工程对库区大气CO₂浓度的影响,对实现国家“双碳”目标,调节能源结构具有重要参考价值。文章选取轨道碳观测卫星-2(OCO-2)卫星观测数据,基于反距离权重(IDW)插值,利用曼-肯德尔(Mann-Kendall)法非参检验、森氏(Sen’s)斜率估计、空间自相关分析以及冷热点算法,分析研究区大气CO₂的演变趋势和空间特征。研究结果表明：1)2015～2020年,三峡库区各区县大气CO₂月均、年均浓度呈上升趋势,研究区整体呈显著增长趋势;冬季大气CO₂浓度最高,秋季最低,表现出明显的季节性周期变化。2)2015～2020年三峡库区大气CO₂具有较高空间相关性,且部分区域表现出冷热点聚集现象。3)三峡库区XCO₂与全国平均水平具有良好一致性,三峡工程的建设并未导致三峡库区CO₂浓度升高。     

基于Hydrolight模型的太湖SDGSAT-1卫星悬浮物浓度反演研究

利用卫星遥感反演水体中的悬浮物浓度对水质监测和保护具有重要意义,在悬浮物浓度反演过程中,如何避免或最大程度降低水体中叶绿素a、有色可溶性有机物(Colored Dissolved Organic Matter,CDOM)的干扰是当前的技术难点。文章针对可持续发展科学卫星1号(SDGSAT-1)MII传感器,利用Hydrolight辐射传输模型,从理论上挖掘只与悬浮物强相关的反演因子,以此构建适用于MII影像的太湖悬浮物浓度反演模型,通过水体的实测数据和遥感数据对模型应用效果进行验证。结果表明：反演因子R′(B₅/B₃)与悬浮物浓度为强相关,同时与叶绿素a、CDOM浓度弱相关;利用R′(B₅/B₃)作为反演因子构建的幂函数模型为最优反演模型;将幂函数模型分别应用于实测数据和2022年5月4日的太湖SDGSAT-1 MII数据,两次验证试验显示反演结果和现场测量结果具有较强一致性,模型适用性较好。该研究可为SDGSAT-1卫星在湖泊水体悬浮物浓度监测、水资源评估与保护等提供一些技术参考。     

气体辐射与流场耦合对火星进入热环境影响

采用火星大气物理化学模型,求解带辐射源项的三维热化学非平衡N-S方程,对探路者号火星探测器进入过程中的高温流场和热环境进行了数值模拟,分析了气体辐射与非平衡流场耦合效应对流场和热流的影响。结果表明:1)探路者号火星探测器流场热化学非平衡效应显著,CO₂气体发生大规模离解,高度低至28.5 km仍存在热力学非平衡效应;2)热力学与化学非平衡效应的影响均与表面催化特性相关,完全催化热流要高于完全非催化热流50%以上;3)高温流场中的CO组分会产生较强的气体辐射加热,辐射热流与对流热流的比值为15%～45%,靠近肩部区域比值最大;4)气体辐射对非平衡流场的冷却效应使激波脱体距离减小;与非耦合方法相比,采用耦合方法得到的辐射热流降低约12%～25%。     

TiO2光催化薄膜在空间污染防护 应用中的探索

文章采用溶胶凝胶法在JGS1石英玻璃上制备了TiO₂薄膜,并对其晶体结构与光催化性能之间的关系进行了研究,探讨了紫外光辐照下TiO₂薄膜对大分子链硅油光催化效果。结果表明:经500 ℃热处理后的TiO₂薄膜为锐钛矿结构,具有较高的光催化活性;在253 nm紫外光辐照下,TiO₂薄膜对大分子链硅油表现出较好的光催化降解效果。该研究将为空间环境下飞行器光学表面污染净化材料的开发提供有益参考。     

The O/OREOS mission: first science data from the Space Environment Survivability of Living Organisms (SESLO) payload

We report the first telemetered spaceflight science results from the orbiting Space Environment Survivability of Living Organisms (SESLO) experiment, executed by one of the two 10?cm cube-format payloads aboard the 5.5?kg Organism/Organic Exposure to Orbital Stresses (O/OREOS) free-flying nanosatellite. The O/OREOS spacecraft was launched successfully to a 72° inclination, 650?km Earth orbit on 19 November 2010. This satellite provides access to the radiation environment of space in relatively weak regions of Earth's protective magnetosphere as it passes close to the north and south magnetic poles; the total dose rate is about 15 times that in the orbit of the International Space Station. The SESLO experiment measures the long-term survival, germination, and growth responses, including metabolic activity, of Bacillus subtilis spores exposed to the microgravity, ionizing radiation, and heavy-ion bombardment of its high-inclination orbit. Six microwells containing wild-type (168) and six more containing radiation-sensitive mutant (WN1087) strains of dried B. subtilis spores were rehydrated with nutrient medium after 14 days in space to allow the spores to germinate and grow. Similarly, the same distribution of organisms in a different set of microwells was rehydrated with nutrient medium after 97 days in space. The nutrient medium included the redox dye Alamar blue, which changes color in response to cellular metabolic activity. Three-color transmitted intensity measurements of all microwells were telemetered to Earth within days of each of the 48?h growth experiments. We report here on the evaluation and interpretation of these spaceflight data in comparison to delayed-synchronous laboratory ground control experiments.     

Survival of spores of the UV-resistant Bacillus subtilis strain MW01 after exposure to low-earth orbit and simulated martian conditions: data from the space experiment ADAPT on EXPOSE-E

In the space experiment "Molecular adaptation strategies of microorganisms to different space and planetary UV climate conditions" (ADAPT), bacterial endospores of the highly UV-resistant Bacillus subtilis strain MW01 were exposed to low-Earth orbit (LEO) and simulated martian surface conditions for 559 days on board the European Space Agency's exposure facility EXPOSE-E, mounted outside the International Space Station. The survival of B. subtilis MW01 spores from both assays (LEO and simulated martian conditions) was determined by a colony-formation assay after retrieval. It was clearly shown that solar extraterrestrial UV radiation (λ≥110?nm) as well as the martian UV spectrum (λ≥200?nm) was the most deleterious factor applied; in some samples only a few spore survivors were recovered from B. subtilis MW01 spores exposed in monolayers. However, if shielded from solar irradiation, about 8% of MW01 spores survived in LEO conditions, and 100% survived in simulated martian conditions, compared to the laboratory controls. The results demonstrate the effect of shielding against the high inactivation potential of extraterrestrial solar UV radiation, which limits the chances of survival of even the highly UV-resistant strain of B. subtilis MW01 in the harsh environments of outer space and the martian surface.     

Survival and germinability of Bacillus subtilis spores exposed to simulated Mars solar radiation: implications for life detection and planetary protection

Bacterial spores have been considered as microbial life that could survive interplanetary transport by natural impact processes or human spaceflight activity. Deposition of terrestrial microbes or their biosignature molecules onto the surface of Mars could negatively impact life detection experiments and planetary protection measures. Simulated Mars solar radiation, particularly the ultraviolet component, has been shown to reduce spore viability, but its effect on spore germination and resulting production of biosignature molecules has not been explored. We examined the survival and germinability of Bacillus subtilis spores exposed to simulated martian conditions that include solar radiation. Spores of B. subtilis that contain luciferase resulting from expression of an sspB-luxAB gene fusion were deposited on aluminum coupons to simulate deposition on spacecraft surfaces and exposed to simulated Mars atmosphere and solar radiation. The equivalent of 42 min of simulated Mars solar radiation exposure reduced spore viability by nearly 3 logs, while germination-induced bioluminescence, a measure of germination metabolism, was reduced by less than 1 log. The data indicate that spores can retain the potential to initiate germination-associated metabolic processes and produce biological signature molecules after being rendered nonviable by exposure to Mars solar radiation.     

Liquid rocket engines for large thrust: Present and future

The possibility of an increase in economy and rise in efficiency of liquid-propellant rocket engines of launch vehicles and flight vehicles is considered. The characteristics of liquid-propellant rocket engines, made in the Soviet Union, U.S.A., France, Japan, China and other countries, and working on the following fuels: O₂, +H₂, O₂ + kerosene, N₂O₄ + H₂N-N(CH₃)₂, HNO₃ + dimethylhydrazine, etc. are recalled. Ways of further improvement of liquid-propellant rocket engines are outlined and the problems, arising during their realization, are discussed.     

Recurrent isolation of hydrogen peroxide-resistant spores of Bacillus pumilus from a spacecraft assembly facility

While the microbial diversity of a spacecraft assembly facility at the Jet Propulsion Laboratory (Pasadena, CA) was being monitored, H2O2-resistant bacterial strains were repeatedly isolated from various surface locations. H2O2 is a possible sterilant for spacecraft hardware because it is a low-temperature process and compatible with various modern-day spacecraft materials, electronics, and components. Both conventional biochemical testing and molecular analyses identified these strains as Bacillus pumilus. This Bacillus species was found in both unclassified (entrance floors, anteroom, and air-lock) and classified (floors, cabinet tops, and air) locations. Both vegetative cells and spores of several B. pumilus isolates were exposed to 5% liquid H2O2 for 60 min. Spores of each strain exhibited higher resistance than their respective vegetative cells to liquid H2O2. Results indicate that the H2O2 resistance observed in both vegetative cells and spores is strain-specific, as certain B. pumilus strains were two to three times more resistant than a standard Bacillus subtilis dosimetry strain. An example of this trend was observed when the type strain of B. pumilus, ATCC 7061, proved sensitive, whereas several environmental strains exhibited varying degrees of resistance, to H2O2. Repeated isolation of H2O2-resistant strains of B. pumilus in a clean-room is a concern because their persistence might potentially compromise life-detection missions, which have very strict cleanliness and sterility requirements for spacecraft hardware.     

Theoretical and experimental investigation of C60-propellant for ion propulsion

The large mass as well as the low first ionization potential and the large electron impact ionization cross-section make Buckminsterfullerene (C₆₀) potentially attractive as an ion engine propellant. To evaluate the advantages of C₆₀ it was necessary to calculate characteristic quantities like the thrust-beam-power ratio and the different efficiencies. It was found that, compared with xenon, the use of C₆₀ would significantly reduce the necessary beam power by 57 percent for the same power level, resulting in a reduction of power supply mass and thus in a higher payload capacity.

Calculations of the efficiencies show a clear increase in overall efficiency. Particularly, the mass efficiency and the electrical efficiency would increase significantly over that obtained with a xenon-fuelled ion engine. Together with the exceptionally high flexibility of the molecular structure of C₆₀, this results in a very low ablation in the grid system, and consequently in a longer lifetime.

One of the most severe problems in using C₆₀ as propellant for ion engines is the temperature sensitivity of C₆₀. High temperatures cause fragmentation of the C₆₀ molecule, low temperatures lead to resublimation of C₆₀ on the inner walls of the engine. Both would result in a decrease of the mass efficiency. Therefore, extensive experiments with a special ion source were carried out to determine the temperature behavior of an ion thruster.

This and the theoretical research yield in a temperature window (400–700°C) for systems operating with C₆₀.     

The biological effectiveness of HZE-particles of cosmic radiation studied in the Apollo 16 and 17 Biostack experiments

The Biostack experiments I and II were flown on board the Apollo 16 and 17 command modules in order to obtain information on the biological damage produced by the bombardment of heavy high-energy (HZE) particles of cosmic radiation during spaceflight. Such data are required for estimating radiation hazards in manned spaceflight. Seven biological systems in resting state (Bacillus subtilis spores, Colpoda cucullus cysts, Arabidopsis thaliana seeds, and eggs of Artemia salina, Tribolium castaneum and of Carausius morosus) were accommodated in the two Biostacks. By using a special sandwich construction of visual track detectors and layers of biological objects, identification of each hit biological object was achieved and the possible biological damage correlated with the physical features of the responsible HZE-particle. In the different systems the degree of damage depended on whether the hit cell was replaceable or not. A high sensitivity to HZE-particle bombardment was observed on Artemia salina eggs; 90% of the embryos, which were induced to develop from hit eggs, died at different developmental stages. Malformations of the abdomen or the extremities of the nauplius were frequently induced. In contrast, the growth of hit Vicia faba radiculae and the germination of hit Arabidopsis thaliana seeds and hit Bacillus subtilis spores were not influenced remarkably. But there was an increase in multicaulous plants and a reduction in the outgrowth of the bacterial spores. In addition, information was obtained on the fluence of the HZE-particles, on their spectrum of charge and energy loss, and on the absorption by the Apollo spacecraft and the Biostack material itself. This will help to improve knowledge concerning radiation conditions inside of spacecrafts, necessary to secure a maximum possible protection to the astronauts.     

A two-dimensional approach to multibody free dynamics in space environment

The equation of motion of a multibody system, described here as a chain of rigid bars and revolute joints orbiting around the Earth, is derived.

For each bar two translational and one rotational equilibrium equations are written. The forces acting on each body are the gravitational forces and the reaction forces (unknown) acting on it's end joints. The complete set of equilibrium equations consists of N_X differential equations, where N_X is the order of the state vector. The total number of unknowns is N_X+N_R where N_R=2N_J and N_J is the number of joints. The N_R additional equations, to make the system determinate, are provided by the nondifferential compatibility equations.

The resulting system is a set of differential algebraic equations (DAE) for which the well-known method of reducing the system to ordinary differential equations (ODE) is applied.

Since the internal forces are associated with the relative displacements between the bodies, which are small fractions of the distance of the multibody spacecraft from the center of the Earth, the task of obtaining these forces from inertial coordinates, from a numerical viewpoint, could be impossible. So the problem is reformulated in such a way that the equation of motion of the system, contains global quantities where no internal forces appear, and local equations where internal forces do appear. In the latter one, only quantities of the same order of the spacecraft dimensions are present. Numerical results complete the work.