共查询到18条相似文献,搜索用时 140 毫秒
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空间碎片防护研究最新进展 总被引:2,自引:0,他引:2
空间碎片对在轨航天器的安全运行构成了严重威胁,对航天器的撞击事件频繁发生。随着空间碎片环境的日趋恶化,航天器的防护变得越来越重要。文章从空间碎片环境模型、撞击风险评估、航天器部件损伤、防护材料与结构的超高速撞击试验、撞击试验数据库建设、超高速发射设备、在轨撞击感知、机构间超高速发射设备交叉校验等方面对国内外空间碎片防护研究的进展进行了总结,并在此基础上给出我国未来空间碎片防护研究的发展建议。 相似文献
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空间碎片撞击在轨感知技术研究综述 总被引:1,自引:2,他引:1
随着航天发射活动的日益频繁,空间碎片环境随之恶化。为了应对空间碎片的撞击威胁,人们提出了用空间碎片撞击在轨感知系统实时监测航天器在轨遭受空间碎片撞击的情况。文章在对国内外相关研究机构研究成果的调研基础上,介绍了国内外在空间碎片撞击在轨感知技术领域的研究现状,对各国基于超高速撞击声发射技术的空间碎片撞击在轨感知技术的发展状况进行了全面评述,重点介绍了国内的研究进展。最后基于国内航天事业需要,探讨了未来发展方向。 相似文献
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卫星在轨操作任务主要包括在轨燃料加注、在轨模块更换、在轨发射、在轨空间碎片清除等。值得指出的是,在轨操作可以针对己方航天器进行,也可以针对敌方航天器进行。能够通过在轨加注延长航天器寿命,也可以利用交会对接和空间机械手技术将敌方航天器拖离目标轨道,具有巨大的商业和军用潜力。 相似文献
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目前,人类已将6000多颗航天器送入太空,这些航天器在广泛服务社会的同时,在航天器发射和"寿终正寝"后将变成空间碎片(太空垃圾),这些太空幽灵正在威胁着在轨运行航天器的安全。十多年来,如何清除太空垃圾,如何减缓太空垃圾的威胁,一直是国际社会广泛关注的问题。"十五"以来,中国政府在发展航天技术的同时,高度重视"太空环保"问题,许多中国航天工作者在为减缓和对付太空垃圾而孜孜不倦地工作, 相似文献
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空间碎片观测综述 总被引:7,自引:0,他引:7
空间碎片又称轨道碎片,是指宇宙空间中除正常工作的飞行器外的所有人造物体,包括飞行着的各种残骸和碎片,大到废弃的卫星、运载火箭末级,小到固体火箭发动机燃烧后的氧化铝小颗粒或从航天器上剥落下来的漆片。这些人造物体长期运行在空间轨道上,并随着人类航天活动的扩展日益增多。据估计,目前地球空间轨道上空间碎片的数量在数十万至数百万之间,而地面能够观测到的在轨运行的人造物体却不到1万个。以2003年6月24日美国公布的资料为例,登录在案的在轨物体数目有9106个,其中真正有效的航天器为1003个,即89郾0%的在轨物体为空间碎片。空间碎片的存在严重地威胁着在轨运行航天器的安全,它们和航天器的碰撞能直接改变航天器的表面性能,造成表面器件损伤,导致航天器系统故障,对航天器的正常运行带来极大的危害。同时空间碎片的不断产生对有限的轨道资源也构成了严重威胁,尤其是当某一轨道高度的空间碎片密度达到一个临界值时,碎片之间的链式碰撞过程将会造成轨道资源的永久破坏。因此,为了安全、持续地开发和利用空间资源,就必须不断提高对空间碎片的跟踪监视技术,增强对空间碎片环境的分析预测能力,同时寻求控制空间碎片的有效措施。 相似文献
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介绍了国际机构间碎片协调委员会提出的关于地球静止轨道(GEO)空间碎片问题的研究结果和碎片处置的建议,主要内容包括:GEO与GEO环的概念、EGO上物体现状,EGO空间碎片处置的基本原则和8条具体处置措施建议。该建议已于2000年2月提交联合国和平利用外层空间委员会科技小组委员会第37届会议。 相似文献
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Visualizing Impact Probabilities of Space Debris 总被引:1,自引:0,他引:1
We present a new method to assess and visualize the collision risk due to space debris for an orbiting spacecraft. It is based on a parameter space derived from Öpik's studies of close approaches between small Solar System bodies and the planets. By means of this representation, many useful insights into the dynamics of the overall debris population with respect to a selected target can be obtained. The method can also be applied to estimate the increase in impact hazard (e.g., for the International Space Station) associated to fragmentation events occurring on a specific orbit. 相似文献
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A model for the evolution of the low Earth orbit man-made debris population is presented and the results of several test cases discussed. Debris sources include normal operations in space, explosions occurring on spacecraft in orbit, and collisions between objects in orbit; the stochastic occurrence of these deposition events is modeled using Monte Carlo techniques. A technique for discriminating between objects populating long-life vs rapid-decay orbits is discussed and applied to the analysis of debris contributions from collisions of comparable sized objects. In varying degrees, each of the cases presented indicate there is cause for concern for spacecraft and space operations from the 1990s onward-man-made debris will play a role which may vary from presenting a considerable hazard to certain operations or certain spacecraft to effectively prohibiting the use of certain spaceccraft or space operations. 相似文献
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By using electrodynamic drag to greatly increase the orbital decay rate, an electrodynamic space tether can remove spent or dysfunctional spacecraft from low Earth orbit (LEO) rapidly and safely. Moreover, the low mass requirements of such tether devices make them highly advantageous compared to conventional rocket-based de-orbit systems. However, a tether system is much more vulnerable to space debris impacts than a typical spacecraft and its design must be proved to be safe up to a certain confidence level before being adopted for potential applications. To assess space debris related concerns, in March 2001 a new task (Action Item 19.1) on the “Potential Benefits and Risks of Using Electrodynamic Tethers for End-of-life De-orbit of LEO Spacecraft” was defined by the Inter-Agency Space Debris Coordination Committee (IADC). Two tests were proposed to compute the fatal impact rate of meteoroids and orbital debris on space tethers in circular orbits, at different altitudes and inclinations, as a function of the tether diameter to assess the survival probability of an electrodynamic tether system during typical de-orbiting missions. IADC members from three agencies, the Italian Space Agency (ASI), the Japan Aerospace Exploration Agency (JAXA) and the US National Aeronautics and Space Administration (NASA), participated in the study and different computational approaches were specifically developed within the framework of the IADC task. This paper summarizes the content of the IADC AI 19.1 Final Report. In particular, it introduces the potential benefits and risks of using tethers in space, it describes the assumptions made in the study plan, it compares and discusses the results obtained by ASI, JAXA and NASA for the two tests proposed. Some general conclusions and recommendations are finally extrapolated from this massive and intensive piece of research. 相似文献
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