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卫星超高速撞击解体碎片特性的试验研究 总被引:1,自引:0,他引:1
为了研究超高速撞击下卫星解体碎片的分布特性,在弹道靶上开展了三次模拟卫星的超高速撞击试验。发射铝合金钝锥弹丸以3.2km/s~4.2km/s的速度撞击模拟卫星,对解体碎片进行回收、测量和统计分析,结果表明:碎片累积数量与碎片特征尺寸/特征质量在对数坐标系中基本呈直线关系,且碎片尺寸分布和质量分布在形式上和规律上具有高度相似性。通过数据拟合得到了碎片尺寸和质量分布的具体函数形式,分析了碎片质量分布与尺寸分布之间的内在关系。将试验结果与NASA标准解体模型进行了比较,讨论了两者的差别及其原因。
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为了实现对航天器在轨解体事件及其碎片分布特性的快速分析,中国空气动力研究与发展中心(CARDC)开发了SFA(Spacecraft Fragmentation Analysis)软件。该软件主要基于CSBM航天器解体模型开发形成,同时集成了NASA的标准解体模型。SFA软件具有解体程度分析、解体碎片生成、碎片分布统计等功能,并可以实时显示计算结果、绘制统计曲线。文章着重介绍了SFA软件2.0版的功能模块、主要算法、界面及使用方法等,并针对Iridium 33-Cosmos 2251碰撞、Solwind P78航天器解体等在轨事件进行了分析。 相似文献
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Area-to-mass ratios for orbital debris tracked by the U.S. Space Command were calculated from observed changes in apogee and perigee altitude due to atmospheric drag. The area-to-masses observed for the orbital debris were similar to those found for debris from laboratory breakups, and suggest that much of the debris is composed of crumpled thin plates or of insulation material with low effective density. Areas for the debris objects were derived from radar cross-section data. Object masses were calculated from the ratio of the RCS-derived area to the area-to-mass ratio. Analysis of the distributions of fragment masses from the breakups suggests that in many cases, only a portion of the initial object breaks up into small fragments. 相似文献
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利用等离子体加速器发射超高速
微小空间碎片的研究 总被引:2,自引:0,他引:2
文章介绍了国内外微小空间碎片超高速撞击地面模拟实验研究的现状,描述了国内等离子体微小空间碎片加速器的研制进展和初步实验结果,分析了该加速器在空间碎片防护研究工作中的应用。在初步调试阶段,在系统设计满负荷储能6%和35%的条件下,分别将100 ?m和200 ?m的玻璃微粒加速至5.5 km/s和9.3 km/s。利用该加速器可以模拟研究10~1 000 ?m的微小空间碎片对卫星功能材料的撞击损伤特性,可以加速模拟研究卫星关键部件或分系统在大量微小空间碎片撞击下的失效机理和失效模式,为卫星防护微小空间碎片的设计提供技术支持。该加速器还能为国内发展星载空间微小碎片探测仪器的设计和标定提供模拟实验条件。 相似文献
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The solutions adopted for the disposal of the upper stages used to put in orbit the first satellites of the new European (Galileo) and Chinese (Beidou) navigation constellations were analyzed. The orbit evolution of the rocket bodies was modeled for 200 years, taking into account all relevant perturbations, and the chosen disposal options were evaluated in terms of their long-term consequences for the debris environment. The results obtained, when applicable, were also discussed in the context of the eccentricity instability problem, pointed out in previous studies. In addition, the long-term evolution of the fragments resulting from a Beidou rocket body breakup, and of simulated high area-to-mass ratio objects released in the disposal orbits of the first two Galileo upper stages, was investigated.Eight out of ten Beidou upper stages were found to have an orbital lifetime <25 years and the other two resulted in a dwell time of approximately 6 years below 2000 km. It was also found that the perigee heights of the two upper stages used to deploy the first Galileo test spacecraft will remain more than 169 km above the constellation nominal altitude, never crossing the existing or planned navigation systems. In spite of an inclination resonance possibly leading to the exponential growth of the eccentricity over several decades, the optimal choice of the disposal orbital elements was able to prevent such an outcome, by maintaining the orbit nearly circular. Therefore, the upper stage disposal strategies used so far for Beidou and Galileo have generally been quite successful in averting the long-term interference of such rocket bodies with the navigation constellations, provided that accidental breakups are prevented. 相似文献
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Each time a debris particle or a meteoroid strikes a satellite in orbit, a great amount of secondary particles is ejected in the neighborhood of the impact site. This phenomenon is important in particular for brittle materials, such as those used for solar arrays or thermal control paint. The secondary particles that do not impact other parts of the spacecraft are added to the primary debris population and hence increase the small debris particle flux. We describe an ejecta production model that gives the size and the velocity distribution of ejected particles as a function of primary impact parameters. The model has been used to explain the discrepancy between measurements and modeling of impact crater distribution on the solar arrays of the EuReCa spacecraft. 相似文献
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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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《Acta Astronautica》2014,93(1):285-297
The effects of on-orbit fragmentation events on localized debris congestion in each of the longitude slots of the geosynchronous orbit (GEO) regime are evaluated by simulating explosions and collisions of uncontrolled rocket bodies in multiple orbit configurations, including libration about one or both of the gravitational wells located at 75°E and 105°W. Fragmentation distributions are generated with the NASA Standard Breakup Model, which samples fragment area-to-mass ratio and delta-velocity as a function of effective diameter. Simulation results indicate that the long-term severity and consequence of a GEO fragmentation event is strongly dependent upon parent body longitude at the epoch of fragmentation, which can spawn bi-annual “fragment storms” in high-risk longitude slots, driven by lower-energy fragments that have been captured and have started librating around the nearby gravitational well. 相似文献
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Autonomous navigation of spacecrafts is a difficult task, however, which is a must in future deep space exploration. With multiple spacecrafts flying in space, this aim can be achieved by formation flying spacecraft (FFS) utilizing inverse time difference of arrival (ITDOA) and inverse difference Doppler (IDD) methods, which can locate the position of earth-station from one-way uplink signals in the FFS coordinate, and by way of conversion of coordinates, the position of FFS is achieved in earth-centered earth-fixed (ECEF) coordinate. The ability of neural network (NN) filter in navigation to extract position of spacecrafts from random measuring noise of signal arrival time and Doppler shift is studied with different radius of FFS and surveying parameters. The NN filter used by spacecraft group is new way of unidirectional autonomous navigation and is of high precision of hybrid navigation. 相似文献
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《Acta Astronautica》2009,64(11-12):1312-1317
This paper attempts to search the lost fragments from the near-synchronous US TitanIIIC transtage explosion of February 21, 1992, known as the second major fragmentation of a TitanIIIC transtage. This breakup was accidentally observed by the Maui GEODSS sensor, and then a total of 23 objects were reported from the breakup, no orbital data on any fragments has been generated by the SSN. In order to evaluate the debris cloud orbital evolution, we demonstrate the actual US TitanIIIC transtage explosion by using breakup model and orbit propagator. The perturbing accelerations, considered in this analysis are the non-spherical part of the Earth's gravitational attraction, the gravitational attraction due to the Sun and Moon, and the solar radiation pressure effects. Finally, we will present a search strategy based on distribution of the right ascension of the ascending node about the catalogued objects and the debris particles from the US TitanIIIC transtage explosion. 相似文献
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This paper attempts to search the lost fragments from the near-synchronous US TitanIIIC transtage explosion of February 21, 1992, known as the second major fragmentation of a TitanIIIC transtage. This breakup was accidentally observed by the Maui GEODSS sensor, and then a total of 23 objects were reported from the breakup, no orbital data on any fragments has been generated by the SSN. In order to evaluate the debris cloud orbital evolution, we demonstrate the actual US TitanIIIC transtage explosion by using breakup model and orbit propagator. The perturbing accelerations, considered in this analysis are the non-spherical part of the Earth's gravitational attraction, the gravitational attraction due to the Sun and Moon, and the solar radiation pressure effects. Finally, we will present a search strategy based on distribution of the right ascension of the ascending node about the catalogued objects and the debris particles from the US TitanIIIC transtage explosion. 相似文献
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Synergistic use of debris environment models for flexible, very-long term projections 总被引:1,自引:0,他引:1
Long-term debris environment projections are of great importance for assessing the necessity and effectiveness of debris mitigation measures. Two types of models have been developed to predict these environments. Environment evolution models like the EVOLVE code are using detailed mission model data to input spacecraft, upper stages, and operational debris into specific orbits at specific times; debris from fragmentations are placed in orbits defined by the state vector of the fragmenting object(s) and the breakup model. The second type, typified by the CHAIN program, uses a particle-in-box model that bins the environment in size and altitude rather than following the orbit evolution of individual debris fragments. A 3-Step approach using both the EVOLVE and CHAIN model in a synergistic way was used to increase the reliability of long term environment projections. EVOLVE historical projections 1957–1995 could be validated by comparison to measurements. The comparison of 100 year projection runs of EVOLVE and CHAIN for different traffic scenarios showed a good agreement. In this paper, for the first time, CHAIN projections up to 10,000 years, based on validated boundary conditions derived by EVOLVE are presented, indicating clearly the need of early implementation of effective mitigation measures to prevent exponential population growth by collisional cascading effects. 相似文献
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CAST激光驱动微小飞片及其超高速撞击效应研究进展 总被引:3,自引:2,他引:1
激光驱动飞片技术(LDFT)在模拟微米级空间碎片对航天器的超高速撞击效应方面具有独特的优势。文章全面介绍了北京卫星环境工程研究所在激光驱动飞片技术与微米级空间碎片超高速撞击效应地面模拟研究中取得的若干进展,包括激光驱动飞片的理论计算、超高速飞片的稳定发射技术、超高速飞片速度瞬态测量技术、航天器外露表面的超高速撞击特性、超高速撞击累积损伤评价方法,以及微米级空间碎片超高速撞击防护技术探索等研究。同时,展望了激光驱动飞片技术以及微米级空间碎片累积撞击实验研究的发展方向。 相似文献
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Knowledge of the observable properties of orbital debris is necessary to validate debris models for both the low Earth orbit (LEO) and the geosynchronous Earth orbit (GEO). Current methods determine the size and mass of orbital debris based on knowledge or assumption of the material type of the piece. Improvement in the knowledge of material is the goal of the research described herein. The process of using spectral absorption features to determine the material type is explored. A review of the optical measurements of orbital debris as well as current research in the area is discussed. Reflectances of common spacecraft materials are compared. The need for, and advances made possible by obtaining real data are explored. The prospects of the venture are investigated. 相似文献