木星系及行星际飞越探测的多次借力飞行轨道设计研究

根据我国木星系及行星际穿越探测任务规划,瞄准工程方案可行,对使用多次借力的地木转移轨道及行星飞越飞行轨道进行了深入研究分析。首先,对星际飞越目标进行了探讨,明确了满足任务约束的星际飞越目标;其次,对行星际飞行序列进行了优选,从探测器发射日期、发射双曲剩余速度的平方(C3)、深空机动、木星到达C3和总的任务时间角度,对比分析了多个星际飞行序列,给出了最优序列设计结果;最后,基于工程约束,对探测器的连续发射机会进行了优化设计,给出了探测器连续8天、11天和16天发射所需的发射C3和深空机动大小需求。研究结果表明:在2029—2032年期间,木星系及行星际穿越探测任务最优的深空飞行序列为地球-金星-地球-地球-木星-天王星,最优的发射日期集中在2029年10月份。     

先驱者10号重获新生

从1958年10月到1973年4月,美国航宇局为了探测月球、行星际空间和外行星,共发射了11颗先驱者号探测器,其中1972和1973年发射的先驱者10号和11号对木星和土星进行了探测,是最早探测这两颗行星的太空飞行器。先驱者10号是1972年3月2日发射的。它于1973年12月3日从距木星13万公里的地方飞过,进行了所谓的飞越式探测。由于只是路过,而不是进入木星轨道,所以该探测器此后仍一直不停地向前飞行着。目前它距太阳     

火星观察者探测器

火星观察者探测器美国火星观察者（ＭａｒｓＯｂ－ｓｅｒｖｅｒ）探测器于１９９２年９月２４日用大力神３号运载火箭从肯尼迪航天中心发射升空。这是美国自１９７５年发射两颗海盗号行星际探测器以来，首次对火星的飞行和探测。它将对火星的地貌和大气等进行普查，进而建...     

先驱者10号重获新生

从 1958年 10月到 1973年4月 ,美国航宇局为了探测月球、行星际空间和外行星 ,共发射了11颗先驱者号探测器 ,其中 1972和 1973年发射的先驱者 10号和11号对木星和土星进行了探测 ,是最早探测这两颗行星的太空飞行器。先驱者 10号是 1972年 3月2日发射的。它于 1973年 12月 3日从距木星 13万公里的地方飞过 ,进行了所谓的飞越式探测。由于只是路过 ,而不是进入木星轨道 ,所以该探测器此后仍一直不停地向前飞行着。目前它距太阳约 10 9.2亿公里 ,是日地间距离的近 74倍。尽管已离家非常遥远 ,而且“年事已高”,但该探测器仍一直在向我们提供着…     

首探冥王星的"新视野"

在太阳系边陲地带,有一颗70多年前才被发现的“小冰球”。它在苍茫的宇宙中绽放着暗红色的光芒。这就是冥王星。在太阳系的九大行星中,冥王星离太阳最远,探测难度极大,是至今人类惟一未用空间探测器“专访”过的太阳系行星,所以至今人类仍对其知之甚少。不过,美国1月19日用宇宙神5重型火箭从卡纳维拉尔角发射的冥王星探测器——新视野号将有望改变这一局面。这个总耗资7亿美元左右、钢琴般大小的探测器将高速行驶约50亿千米,最早可于2015年飞抵太阳系尽头,对冥王星及其卫星以及所谓的柯伊伯带开展首次近距离探测活动。该探测器将通过近距离飞越采集冥王星大气、地理环境和温度等数据,寻找关于太阳系起源和地球生命起源的线索。新视野号是美国航宇局“新边疆”空间探测计划中的首项中级别探测任务。它将使美国成为世界上第一个对太阳系的每颗行星都进行过考察的国家,是一次历史性的探测,是人类探索宇宙的又一座里程碑。     

面向太阳系边际探测的激光通信方案研究

针对我国太阳系边际探测任务需求,提出了利用激光链路进行对地高速信息传输的方案。梳理了深空激光通信的国外发展现状,分析了太阳系边际探测任务的激光链路特点和约束条件,给出了飞行激光终端和激光地面站的初步方案和主要参数,进行了链路预算和影响因素分析,并对我国未来太阳系边际探测任务激光通信的发展进行展望,为我国太阳系边际探测任务的激光通信论证与实施提供参考。     

苏联的火星载人探测任务

据《空间飞行》1990年2月报道,苏联可能在2015年执行火星载人探测任务。届时,将用能源号大型运载器把大块的部件送入轨道,由宇航员在轨道上组装成星际航天器。一旦星际航天器组装完毕,苏联航天飞机将把一个国际宇航员小组带到星际航天器上,这个航天器将在几年后到达火星。 苏联打算在1994年9月用质子号火箭发射其火星94探测器,这个探测器将携带高空探测气球。苏联还打算在2001年进行火星土壤采样返回地球的飞行。     

美探测器进入灶神星小行星轨道

在飞行超过27亿公里后,NASA“黎明”探测器7月15日进入绕灶神星小行星运行的轨道．成为绕太阳系小行星带中天体做轨道运行的首个人造探测器。灶神星直径约530公里．是小行星带中第二大的天体,也是太阳系中最亮的小行星,有许多秘密有待破解。“黎明”探测器耗资4．66亿美元．发射于2007年9月。灶神星是它此次探测任务的第一站。它将测绘灶神星表面。     

美国“黎明号”小行星探测器到达谷神星

<正>北京时间2015年3月6日20点39分,"黎明号"探测器经过近8年、49亿千米的飞行,抵达矮行星谷神星。继2011年探测岩石质灶神星后,"黎明号"将对冰质谷神星进行为期14个月的科学探测,以增进人类对太阳系起源与演化的了解。"黎明号"探测器是第一个环绕主小行星带天体的探测器和第一个在一次任务中先后环绕两个地外天体的探测器,也是第一个矮行星探测器。该任务是NASA第一次采用离子推进作为动     

NASA发射新的月球探测器

轨道科学公司的“人牛怪”5运载火箭9月6日深夜在NASA位于沃洛普斯岛上的沃洛普斯飞行设施发射了NASA的“月球大气与尘埃环境探测器”（LADEE）。这是“人牛怪”5火箭的首次发射，也是沃洛普斯飞行设施首次用来发射深空探测器。“人牛怪”5是“人牛怪”4的衍生型号，由退役弹道导弹改装而成，加装了一个上面级，以便能执行静地转移轨道和行星际发射任务。     

Exploring the solar system galactic frontier in extreme ultraviolet

The solar system galactic frontier—the region where the expanding solar wind meets the surrounding galactic medium—remains poorly explored. The sheer size of the essentially asymmetric heliosphere calls for remote techniques to probe the properties of its global time-varying three-dimensional boundary. The Interstellar Boundary Explorer (IBEX) mission (launch in 2008) will image the region between the termination shock and the heliopause, the heliospheric sheath, in fluxes of energetic neutral atoms. Global imaging in extreme ultraviolet (EUV) will likely be the next logical step in remote exploration of the galactic frontier from 1 AU. Imaging in EUV will establish directional and spectral properties of (1) the glow of singly charged helium (He⁺) ions in the interstellar and solar wind plasmas; (2) emissions of hot plasma in the Local Bubble; and (3) characteristic emissions of the solar wind. Global imaging with ultrahigh sensitivity and ultrahigh spectral resolution will map the heliopause and reveal the three-dimensional flow pattern of the solar wind, including the flow over the Sun's poles. This article presents the emerging concept of the experiment and space mission for heliosphere global imaging in EUV.     

Statistical properties of the fluxes of energetic ions and solar wind in the region of intersection of shock wave fronts in the distant heliosphere

The character of statistical distributions of the intensity of energetic charged particles, solar wind flux, and the interplanetary magnetic field strength is analyzed using the data obtained by the Voyager 1 and Voyager 2 spacecraft in the distant heliosphere. A comparison of the distributions in the region of crossings of shock wave fronts in 1991 and in 2004 is carried out, and their similarities and differences are discussed.     

The Voyager Interstellar Mission

The Voyager Interstellar Mission began on January 1, 1990, with the primary objective being to characterize the interplanetary medium beyond Neptune and to search for the transition region between the interplanetary medium and the interstellar medium. At the start of this mission, the two Voyager spacecraft had already been in flight for over twelve years, having successfully returned a wealth of scientific information about the planetary systems of Jupiter, Saturn, Uranus, and Neptune, and the interplanetary medium between Earth and Neptune. The two spacecraft have the potential to continue returning science data until around the year 2020. With this extended operating lifetime, there is a high likelihood of one of the two spacecraft penetrating the termination shock and possibly the heliopause boundary, and entering interstellar space before that time. This paper describes the Voyager Interstellar Mission--the mission objectives, the spacecraft and science payload, the mission operations system used to support operations, and the mission operations strategy being used to maximize science data return even in the event of certain potential spacecraft subsystem failures. The implementation of automated analysis tools to offset and enable reduced flight team staffing levels is also discussed.     

Interplanetary CubeSats system for space weather evaluations and technology demonstration

The paper deals with the mission analysis and conceptual design of an interplanetary 6U CubeSats system to be implemented in the L₁ Earth–Sun Lagrangian Point mission for solar observation and in-situ space weather measurements.     

Rapid assessment of radiobiological doses for terrestrial and interplanetary space missions

This paper presents the doses levels expected in orbits in chart form, covering the range 300-800 km of altitude and 0-90 degrees of inclination behind shieldings similar to the Hermes spacecraft and the EVA spacesuit matter distributions. These charts allow users to rapidly find the radiobiological dose received in the most critical organs of the human body either in normal situations or during a large solar event. Outside the magnetosphere, during interplanetary or lunar missions, when the dose received during crossing of the radiation belts become negligible, the dose is due to galactic cosmic rays (GCR) and solar flares. The correct radiobiological assessment of the components of this radiation field becomes a major problem. On the Moon a permanent ground-based station can be shielded by lunar materials against meteoroids and radiations. The radiobiological hazard, essentially linked to the solar flare risk during the transfer phase and the extra-station activities, may be solved by mission planning. For interplanetary flights the problem comes from both increased risk of solar events and from the continuous exposure to GCR. These energetic particles cannot be easily stopped by shieldings; cost considerations imply that more effective materials must be used. Impact on the vehicle design and the mission planning is important.     

Low-energy ion fluxes and magnetic field on the inner boundary of the heliosphere

A comparison of temporal profiles of low-energy ion intensity and magnetic field magnitude in different periods of solar activity in the outer heliosphere is carried out using the data of the Voyager 1 and Voyager 2 spacecraft. It is shown that temporal, spectral, and statistical characteristics of particle fluxes and magnetic field in the heliospheric regions before and after the terminal shock in 2002–2008 had similar dynamics in different hemispheres. This similarity allowed one to assume that, in the region of the inner heliospheric boundary, a quasistable spatial structure existed moving together with the terminal shock in accordance with the solar wind pressure, as well as, probably, under the action of the interstellar medium. It was revealed that the spatial dimensions of most details of this structure are less on Voyager 2, which, probably, is due to variation of the solar activity level, difference in latitude of spacecraft disposition, and also the influence of the interstellar magnetic field.     

Extrasolar solar-sail trajectories and dark matter

Hyper-thin, high-speed solar-photon sail space probes exploring the Sun?s Oort comet cloud could also be used to set an upper bound to the concentration of WIMPS (weakly interacting massive particles), one of the suggested (but unconfirmed) forms of dark matter within the vicinity of the solar system. Newton?s Shell Theorem would be applied to determine variations in apparent solar mass as the probe moves further out from the Sun. Application of this technique to the trajectories of Pioneer 10/11 reveals that the upper limit to WIMP concentration within ~60 AU of the Sun is ~0.2 Earth masses, as revealed in studies of the Pioneer Anomaly. If the published accuracy of the Pioneer acceleration measurements can be increased by an order of magnitude, probe trajectory measurements out to ~10,000 AU may confirm or falsify the hypothesis that WIMP mass within the solar vicinity is ~3X star mass. It is shown that a space-manufactured ~40-nm thick beryllium hollow-body solar sail deployed from a ~0.07 AU perihelion is a candidate spacecraft for such a mission. Possible science-team organization strategy for a ~100-year mission to ~10,000 AU is discussed.     

电动帆轨迹优化及其性能分析

电动帆是一种新兴的无推进剂损耗的推进方式,利用太阳风的动能冲力飞行。电动帆由数百根长而细的金属链所组成,这些金属链通过空间飞行器自旋展开,太阳能电子枪向外喷射电子,使金属链始终保持在高度的正电位,这些带电的金属链会排斥太阳风质子,利用太阳风的动能冲力推动空间飞行器驶向目标方向。针对电动帆轨迹优化问题,提出采用Gauss伪谱法进行轨迹优化,克服了间接法对协态变量初值敏感的缺点。考虑在太阳风暴等原因造成特征加速度改变的情况,基于Gauss伪谱法实现电动帆在线轨迹重新规划,提高电动帆对太阳风不确定性的适应能力。最后以太阳系外探测任务为例,对电动帆和太阳帆的性能进行对比,仿真结果表明电动帆在星际远航任务中所用时间较短。     

载人小行星探测的任务特点与实施途径探讨

介绍了载人小行星探测的发展现状,对目前美国基于"猎户座"飞船的载人小行星探测的概要方案进行了描述,包括探测器系统组成、运载火箭和飞行方案等内容。从速度增量、目标星引力等方面,分析了载人小行星探测的任务特点,并与载人火星探测、载人月球探测以及无人小行星探测的任务特点进行了比较。给出了载人小行星探测的实施途径建议,包括目标星选择、载人飞船系统设计等。讨论了其所涉及的推进、星际飞行安全保障、小行星表面行走等关键技术。研究结果可为我国开展载人深空探测提供参考。