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火星尘埃与探测 总被引:2,自引:0,他引:2
火星表面尘埃与太阳辐射、热辐射的相互作用直接影响火星大气的结构、热平衡和动力学过程,并会产生改变火星表面反照率和火星地貌的长期效应.火星尘埃环境还对登陆于火星表面的着陆器能源系统和光学载荷等系统构成影响.为此需开展火星大气尘埃的直接就位探测.在介绍了火星的尘埃特性与主要探测方法基础上,提出了采用微质量计技术开展火星表面尘埃就位探测的综合探测器方案.探测器包含3种传感器.尘埃累积传感器通过设置其敏感晶体表面朝上,可以探测火星表面尘埃的沉积质量与速率;荷电尘埃传感器通过加置不同极性的偏置电压,可以探测荷正电尘埃和荷负电尘埃的累积特性;磁尘传感器通过在敏感晶体后加设小型永久磁铁,可以探测磁性尘埃的累积特性.传感器感测质量范围为10-11~10-4g.火星尘埃综合探测器可应用于未来的火星着陆探测计划. 相似文献
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《国际太空》2004,(2)
星尘号彗星探测器2004年1月2日与怀尔德-2彗星相会 它与该彗星核的最近距离为240km,两者相对速度为2.2×104km/h。它将把收集的尘埃微粒于2006年带回地球进行研究。 (小号) ·最新消息· 勇气号1月4日在火星着陆 □□2004年1月4日,美国勇气号火星探测器在火星表面的古谢夫环形山地区着陆,并很快发回了高清晰度的照片。在着陆过程中,它是完全依靠自主控制。勇气号先是在距火星表面120km高,以1.9×104km/h的速度冲入火星大气层;4min后,它距火星表面10km左右,速度减为1600km/h,此时打开直径10m以上的降落伞;当离火星表面不到8.6km时,其速度降… 相似文献
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在经历了6.8×108km航行之后,美国东部时间2008年5月25日19:53,美国凤凰号(Phoenix)火星探测器在火星北极成功着陆,着陆地点设在纬度同地球格陵兰或阿拉斯加洲北部相当的广阔浅谷.成功着陆后,质量350kg的凤凰号在原地等候了15min,等着陆时掀起的尘埃落定后,展开了太阳电池翼,并于2h后传回第1批图片,其中1张显示探测器1条"腿"站立在火星表面,另1张显示太阳电池翼已经展开,以及几张火星北极表面的清晰图片.5月27日,传回了它记录的第1份火星天气报告. 相似文献
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火星着陆区选择是火星着陆及巡视任务的重要工作之一,着陆区选择需要兼顾科学目标和工程约束,考虑高风险的任务特点,火星着陆任务的工程约束更为重要。工程约束涉及着陆区表面特征、任务轨道、大气等。表面特征包括地理高程、斜坡及地形起伏、岩石分布、尘土厚度、光照、热约束情况。这些因素将影响探测器进入、下降和着陆(EDL)过程的安全性和火星车移动能力。首先针对这些工程约束进行了排序与筛选;然后建立了基于模糊算法的分析模型,通过模糊推理得到各着陆区域的评价指标,从而进行着陆区选择;最后基于ExoMars2020任务的备选着陆区进行了方法验证。 相似文献
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火星着陆自主导航方案研究进展 总被引:2,自引:6,他引:2
火星着陆导航技术是火星着陆过程的核心技术之一。围绕火星着陆环境特点与导航技术遇到的挑战,分析了目前火星着陆过程的导航能力和自主导航的发展趋势,并针对火星着陆过程的特殊性和导航需求,概述了火星着陆过程各阶段自主导航方案的研究现状与进展。进而从导航方案设计与配置、导航模型建立与仿真、导航方案性能分析等方面,对自主导航方案的最新研究进展进行了分析,并在火星着陆全过程自主导航方案综合仿真的基础上,获得了满足火星定点着陆要求的各阶段交接点应满足的导航精度。最后,基于目前技术现状和发展趋势,提出了构建"递进式三阶段"火星着陆自主导航方案的设想,可为未来火星着陆自主导航方案的设计与论证提供参考。 相似文献
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月尘环境效应及地面模拟技术 总被引:1,自引:0,他引:1
介绍了月球尘的特点及其对探月活动的影响。在分析月球尘环境及其对月面探测器污染、磨损、阻塞、静电效应的基础上,对月球尘环境模拟技术、月球尘扬尘及其运动学和动力学规律、月球尘效应防护及试验评价方法等研究方向和重点提出了一些初步看法。针对研究内容的需求,梳理出一台完整的月球尘地面模拟试验设备应具备真空、温度、太阳风、太阳紫外、月球尘、月面电场、月面磁场等环境因素。在此基础上,设计了一种月球尘地面模拟试验装置方案,并对月球尘环境效应试验方法进行了初步讨论。为月球探测后期任务条件保障建设及相关研究工作提供参考。 相似文献
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《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》1999,23(11):1907-1910
Two small satellites of Mars, Phobos and Deimos, can be dust sources around Mars. Orbits of circummartian dust particles are controlled by solar radiation pressure as well as Martian oblateness. Their orbital eccentricity and inclination can be enhanced greatly by the orbital resonance. Particles from Phobos would form a thin dust ring where dust radius is dominant in 20–200μm. On the other hand, particles from Deimos would form an extended dust torus. Collisions of ring particles on Phobos and Deimos may be the most important dust source. The upper limit of dust production from this self-sustaining mechanism can be estimated from the erosion rate of Phobos. Japanese Mars mission NOZOMI (PLANET-B) could discover dust ring/torus through direct detection by MDC (Mars Dust Counter). 相似文献
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P. Palumbo R. Battaglia J. R. Brucato L. Colangeli V. Della Corte F. Esposito G. Ferrini E. Mazzotta Epifani V. Mennella E. Palomba A. Panizza A. Rotundi 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2004,33(12):2252-2257
Among the main directions identified for future Martian exploration, the study of the properties of dust dispersed in the atmosphere, its cycle and the impact on climate are considered of primary relevance. Dust storms, dust devils and the dust “cycle” have been identified and studied by past remote and in situ experiments, but little quantitative information is available on these processes, so far. The airborne dust contributes to the determination of the dynamic and thermodynamic evolution of the atmosphere, including the large-scale circulation processes and its impact on the climate of Mars. Moreover, aeolian erosion, redistribution of dust on the surface and weathering processes are mostly known only qualitatively. In order to improve our knowledge of the airborne dust evolution and other atmospheric processes, it is mandatory to measure the amount, mass-size distribution and dynamical properties of solid particles in the Martian atmosphere as a function of time. In this context, there is clearly a need for the implementation of experiments dedicated to study directly atmospheric dust. The Martian atmospheric grain observer (MAGO) experiment is aimed at providing direct quantitative measurements of mass and size distributions of dust particles, a goal that has never been fully achieved so far. The instrument design combines three types of sensors to monitor in situ the dust mass flux (micro balance system, MBS) and single grain properties (grain detection system, GDS + impact sensor, IS). Technical solutions and science capabilities are discussed in this paper. 相似文献
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Necmi Cihan Orger Kazuhiro Toyoda Hirokazu Masui Mengu Cho 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(10):3270-3288
The charged dust particles can be mobilized electrostatically by the repulsion between the adjacent grains and the surface electric field due to the incoming electron current and the charge accumulation within the micro-cavities. In this study, the experimental results of the initial vertical launching velocities and the maximum dust heights are compared with the estimated values for the lofted spherical dust grains by the patch surface charging equations. Silica particles with the sizes between <6 and 45?µm in radius are loaded on a graphite plate, and they are exposed to the electron beam with 450?eV energy under 4?×?10?3?Pa vacuum chamber pressure. During the first set of the experiments, the dust samples are tested without an initial compression process and an additional horizontal electric field. Second, the dust samples are compressed by two different weights in order to increase the packing density under approximately 780.7?Pa and 3780?Pa. Finally, the dust grains are placed between the two parallel aluminum plates to apply approximately 2000?V/m and 4800?V/m horizontal electric field. A high-speed camera is used to record the transportation of the dust grains together with a microscopic telescope, and the results point out that the patch surface dust-charging model estimations are in agreement with the first experiments. On the other hand, the dust particles from the compressed samples are lofted with higher velocities than the estimations, and the number of the dust lofting observations decreases significantly, which demonstrates the importance of the micro-cavities and the increased charging requirement to overcome the contact forces. When the horizontal electric field is present, the initial vertical launching velocities are measured to be lower than the other experiments, which can be attributed to the decreased charging requirement for the dust lofting as a result of inter-particle collisions and rolling motion. According to the experimental results, the electrostatic dust transportation can be controlled not only by the ambient plasma and the solar irradiation on the airless planetary bodies, but also by the surface properties such as the contact surfaces between the dust grains, the number of the micro-cavities related to the packing density, and the presence of the horizontal electric field contributing to the external forces by other particle motions. 相似文献
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月球受光面上月尘静电浮扬特性分析 总被引:1,自引:1,他引:0
基于单粒子轨道理论及空间尘埃等离子体充电方程,建立了月球受光面上尘埃微粒的静态荷电模型.基于光电子能量Maxiwellian分布假设,确定了月面垂直空间电场强度和光电子鞘层内带电粒子密度的函数表达式.利用牛顿运动定律和静电场力表达式,构建了月球受光面上尘埃微粒的静电浮扬动力学模型,并进行月尘静态浮扬特性的数值计算.研究结果显示:太阳高度角与颗粒粒径是控制月尘静电浮扬发生及动力学特性的两个基本参量;月尘静电浮扬发生在月球的黎明和黄昏;随着粒径的减少,月尘颗粒的最大浮扬高度不断增加. 相似文献