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月球     
相关语句
  moon
     By description of how to compute lunar irradiance in detail then obtained extraterrestrial moon surface irradiance in the range of 0.250μm~1.500μm.
     通过对月球辐照度计算原理进行了详细的描述并计算得到了波长在0.250μm~1.500μm范围内的月球表面辐照度,并给出了一个宽波段遥感器的微光动态范围。
短句来源
     The background radiation includes radiation of the sun、the moon and the sea etc.
     背景辐射有:太阳辐射、天地背景辐射、月球辐射、地球及月球太阳辐射、海面背景辐射等.
短句来源
     For example, to the moon spacecraft, the terms J 3, J 5, J 7 and J 9 should not be neglectable either, and the orbit obliquity also works relatively.
     不仅仅是一个J3项 ,例如月球轨道器 ,J3,J5,J7和J9均有不可忽视的影响 ,而且与轨道倾角有一定的关系。
短句来源
     The SLR derived secular change in the Moon's mean motion caused by the total tidal dissipation is -24.78 arc sec/century 2,agreeing very well with the result ((-24.9±1.0) arc sec/century 2) from the analysis of the lunar laser ranging data.
     SLR确定的总的潮汐耗散引起的月球平均运动的长期变化为 -2 4.78″/世纪 2 ,与激光测月结果 ((-2 4.9± 1.0 )″/世纪 2 )非常一致。
短句来源
     Transformation and Transmission for Sunlight Wave on the Moon Surface in the 21th Century
     21世纪月球表面太阳光波的转换与传输
短句来源
更多       
  lunar
     築oth DE200/LE200 and DE245/LE245 provide users with accurate lunar and planetaryephemerides.
     DE200/LE200和DE245/LE245都是行星和月球的精密历表。
短句来源
     Lunar magnetism and its evolution
     月球磁场与月球演化
短句来源
     THE DESIGN AND REALIZATION OF THE LUNAR RESOURCE DATABASE BASED ON 3-LAYER B/S STRUCTURE
     基于3层B/S结构的月球资源数据库系统的设计与实现
短句来源
     Finally, the gravity anomaly of the nearside is obtained, and is compared with the latest lunar gravitational model LP165. It showsthat the standard deviation in the domain -75° ~ 75° is ±27.354 mgal, and75° ~ 85°,-85° —75° is ±61.965 mgal, which verifies the feasibility and reliability of this method.
     最后将计算结果和现今最高阶次的月球重力场模型LP165进行了比较和分析,得出标准差在纬度-75°~75°范围内为±27.354mGal,75°~85°,-85°~-75°范围内为±61.965mGal的精度,从而验证了该解算方法的可行性和可靠性。
短句来源
     Lunar robot information fusion based on D-S evidence theory
     基于D-S证据理论的月球探测机器人的信息融合
短句来源
更多       
  the moon
     The background radiation includes radiation of the sun、the moon and the sea etc.
     背景辐射有:太阳辐射、天地背景辐射、月球辐射、地球及月球太阳辐射、海面背景辐射等.
短句来源
     For example, to the moon spacecraft, the terms J 3, J 5, J 7 and J 9 should not be neglectable either, and the orbit obliquity also works relatively.
     不仅仅是一个J3项 ,例如月球轨道器 ,J3,J5,J7和J9均有不可忽视的影响 ,而且与轨道倾角有一定的关系。
短句来源
     The SLR derived secular change in the Moon's mean motion caused by the total tidal dissipation is -24.78 arc sec/century 2,agreeing very well with the result ((-24.9±1.0) arc sec/century 2) from the analysis of the lunar laser ranging data.
     SLR确定的总的潮汐耗散引起的月球平均运动的长期变化为 -2 4.78″/世纪 2 ,与激光测月结果 ((-2 4.9± 1.0 )″/世纪 2 )非常一致。
短句来源
     Transformation and Transmission for Sunlight Wave on the Moon Surface in the 21th Century
     21世纪月球表面太阳光波的转换与传输
短句来源
     This ejection lasts 0 05~0 15 Ma and the mass of ejected material is 1 2~2 5 M 0 ( M 0 is the present mass of the moon) which condenses quickly and generates debris disk gradually. Near the Roche limit the moon is produced from debris disk.
     抛射过程持续了 0 0 5~ 0 15Ma ,抛射出的物质质量为 1 2~ 2 5M0 (M0 是现在的月球质量 ) ,这些物质碎片相互碰撞聚集逐渐在Roche极限附近形成月球
短句来源
更多       
  lunar topography
     Status and Trend of Development of Lunar Topography Surveying
     月球遥感立体测绘技术的发展
短句来源
     Development of Lunar Topography Surveying and Its Key Techniques
     月球测图技术发展及其关键技术分析
短句来源
     Lunar topography surveying and lunar geodesy are introduced in the paper.
     主要介绍月球地形测绘和月球大地测量的情况。
短句来源
     Finally,considering the point that our national "Chang'e 1" will be launched with a laser altimetry on it,the idea and its flow chart to determinate lunar gravity field model with the stronger correlation as a restriction between lunar topography and gravity field is proposed.
     结合我国即将发射的“嫦娥卫星”装备有激光测高计这一特点,提出将月球表面地形与月球重力场之间的强相关性作为约束来确定我国自主重力场模型的设想。
短句来源

 

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      moon
    The role of benthopelagic and holoplanktonic organisms in relation to the time of the day, season, and phase of the moon was determined.
          
    Initially, only the USA and USSR sent missions to the Moon and planets.
          
    Observation of the Moon Shadow in Cosmic Ray Muons
          
    The effect of cosmic ray shadowing by the Moon is observed by recording the single muon component with the Baksan underground scintillation telescope (BUST).
          
    A statistically significant (three standard deviations) deficit of muon intensity in the Moon's direction is discovered.
          
    更多          
      lunar
    Detection of ultrahigh-energy cosmic rays and neutrinos by radio method using artificial lunar satellites
          
    An estimate of the feasibility of the ultrahigh-energy cosmic ray and neutrino detection using a lunar satellite-borne radio receiver is presented.
          
    At the same time the lunar radio detector provides a means of searching for ultrahigh-energy neutrinos with a high sensitivity combined with a very large target effective mass.
          
    Optimizing Instrumental Neutron Activation Analysis of Extraterrestrial Materials: Fragments of Lunar Rocks, Meteorites, Chondru
          
    It was shown that, along with geothermal brines (oceanic water), the most promising natural materials to be tested for SHEs are some volcanic (fumarole, griffon) products, lunar rocks, and asteroids.
          
    更多          
      the moon
    The role of benthopelagic and holoplanktonic organisms in relation to the time of the day, season, and phase of the moon was determined.
          
    Initially, only the USA and USSR sent missions to the Moon and planets.
          
    Observation of the Moon Shadow in Cosmic Ray Muons
          
    The effect of cosmic ray shadowing by the Moon is observed by recording the single muon component with the Baksan underground scintillation telescope (BUST).
          
    A statistically significant (three standard deviations) deficit of muon intensity in the Moon's direction is discovered.
          
    更多          
      其他


    This paper continues previous work and completes the design of the rocket's orbits which can hit the moon. In this paper, the relations between the initial conditions and the positions on the moon's sphere of influence are imperoved, based on the double two-body problem. Further, the effects of other disturbing factors (solar and planetary gravitation, drag of atmosphere etc,) on successfully hitting the moon, except lunar gravitation and first order terms of the terrestrial field of gravitation are discussed....

    This paper continues previous work and completes the design of the rocket's orbits which can hit the moon. In this paper, the relations between the initial conditions and the positions on the moon's sphere of influence are imperoved, based on the double two-body problem. Further, the effects of other disturbing factors (solar and planetary gravitation, drag of atmosphere etc,) on successfully hitting the moon, except lunar gravitation and first order terms of the terrestrial field of gravitation are discussed. The results show that these factors can be neglected. In the last part, the deflections which are produced by the errors of initial values are studied, from which,the allowable maximum errors of the initial values are calculated.

    本文继續从前的工作,把击中月球的火箭軌道設計完成。在这里进一步完善了以双二体問題为基础的进口位置和初始条件之間的关系。然后討論了除地球引力場一阶項和月球摄动以外的其它因素对击中月球的影响,討論証明这些因素是可以忽略的。最后研究了初始数据的誤差对击中月球产生的偏差,从而估計出各初始数据可容許的最大誤差。

    This paper discusses the problem of distribution of points on the moon's surface intersected by the orbits of several kinds of lunar rocket, based on the planar and space double two-body problem. First we obtained the ingress-region on the moon's sphere of influence in which the orbits with different initial veloceties can hit the moon vertically, slantingly and tangentially. Then we get the distribution of hitting points on moon's surfaceof these orbits; hence we determine the forbbiden regions on the moon's...

    This paper discusses the problem of distribution of points on the moon's surface intersected by the orbits of several kinds of lunar rocket, based on the planar and space double two-body problem. First we obtained the ingress-region on the moon's sphere of influence in which the orbits with different initial veloceties can hit the moon vertically, slantingly and tangentially. Then we get the distribution of hitting points on moon's surfaceof these orbits; hence we determine the forbbiden regions on the moon's surface of hitting orbits with different initial velocities. The result of calculation shows that: the magnitude of forbbiden region mainly depends upon the magnitude of initial velocity, when the initial velocity increases, then the magnitude of forbbided region increases monotonically; in the case of ascending orbits, the position of forbbiden region is at the posterior part (opposite to the direction of lunar motion) of the invisible half of the moon's surface; in the case of descending orbits, the position of forbbiden region is at the posterior part of the visible half of the moon's surface. Consequently, the anterior part of the invisible half of the moon can be hitten by ascending orbit; and every point on the moon's surface can be hitten by an ascending or descending orbit with specified initial velocity.

    本文以平面和空間的双二体問題为基础,研究了几种类型的击中月球火箭的軌道在击中月球时同月面交点的分布問題。得到了几种不同初始速度能垂直击中,傾斜击中以及切向击中月球的軌道在月球作用范圍边界上的进口范圍。然后得出这些軌道在月面上击中点的分布情况;从而得出不同初始速度的軌道在月面上击中的禁区。从計算結果可看出:禁区大小主要同初始发射速度有关,速度愈大則禁区也愈大;禁区位置对上升軌道而言,在月球背面的后部(同月球运动反方向的部份),对下降軌道而言,在月球正面的后部;因此,用上升軌道也可以击中月球背面的一部份(前部),用适当的初始速度和軌道类型(上升或下降),可以击中月面上任何一点。

    The purpose of this investigation is to study the possibility and condition for a lunar probe to hit or to fly over, at close range, any given region on the surface of the moon. We limit the ballistic speed of the vehicle to 11.2 km/sec and require that the height at the last burn out point should be about a few hundred kilometres. Six definite regions on the surface of the moon are considered as the objectives of these flights. Four regions lie on the great circle where the orbital plane of the moon cuts the...

    The purpose of this investigation is to study the possibility and condition for a lunar probe to hit or to fly over, at close range, any given region on the surface of the moon. We limit the ballistic speed of the vehicle to 11.2 km/sec and require that the height at the last burn out point should be about a few hundred kilometres. Six definite regions on the surface of the moon are considered as the objectives of these flights. Four regions lie on the great circle where the orbital plane of the moon cuts the lunar surface. They are designated as the "near", "remote", "east", and "west" points. For these points, only trajectories in the orbital plane of the moon have been considered. The other two regions, namely, the poles of the aforesaid great circle, are called the "north" and "south" points respectively. In the preliminary survey of the possible trajectories, the approximate method of assuming the earth-moon space as divided into two by a sphere of action of radius 66000 km around the moon has been employed. The trajectory may then be considered to consist of several sections, each one of which is determined by the laws of two-body problem. From considerations on the permissible angular momentum of the orbit, it has been possible to derive limiting values for the velocity of hitting and the angle of incidence in the case of impact trajectories. For reconnaissance trajectories, we try to find out the allowable perilunar distance and velocity as well as how close may the perilunar point of the trajectory be brought to the surface of the moon. From preliminary investigation by the approximate method of sphere of action, we have come to the following conclusions: A. For impact trajectories: 1) To hit either the near or the remote point, the vehicle must be approaching the moon from the east side. With velocity of impact somewhere in the range 160—180km/min, the probe may hit these points at an angle of incidence of 30° or greater. 2) Vertical impact is possible only at the east point with the velocity of hitting at slightly less than 160 km/min. 3) The west point may be hit by a lunar probe, but only at grazing incidence. 4) The trajectories for hitting the north and the south points could be mirror images of each other. These points may be hit at an angle of incidence of about 60°, at a speed of less than 160 km/min. B. For reconnaissance trajectories: 1) Over the near and the remote points, there is a whole series of symmetrical orbits in which the vehicle would be sure to return to the neighbourhood of the earth. When the perilunar velocity is about 100 km/min, the distance of close approach to the centre of the moon may be no more than 5000 km. We can make the trajectory come in contact with the surface of the moon, if we allow the perilunar velocity to be increased to 160 km/min. 2) With perilunar distance over 30000 km, it is possible for the vehicle to fly horizontally over the east point of the moon. Such reconnaissance flight is possible over the west point, but the vehicle has to be so low that the orbit becomes identical with the impact trajectory grazing the west point. 3) When the perilunar point of the orbit may be permitted to deviate about 45° from the zenith of the east or the west point, we can still have reconnaissance trajectories that will bring the vehicle back to the neighbourhood of the earth. 4) When we consider only trajectories whose motion inside the sphere of action is in a plane perpendicular to the earth-moon direction, we could have symmetrical orbits with horizontal flight over the north or the south point at a distance of about 24000 km from the centre of the moon. With permissible values at the moon for different definite points, the path of the vehicle is traced backward in time to verify if it did pass by the vicinity of the earth with reasonable speed. If so, the position and velocity of the vehicle near the earth are taken as the initial values at the last burn out point, and the impact or reconnaissance trajectory is computed once again. In such computations the attractions of both the moon and the earth are taken into account by the method of numerical integration. The trajectories thus obtained are listed in Tables 5, 6, and 7.

    月球表面上考虑了六个定点,它们是自道面内的近、远、东、西四点和此外的南北两点。为了要找到可以实现用火箭击中和航测这六点的轨道,我们以在月面定点上可以容许的初值为轨道出发点,倒推出火箭在地球附近时的位置和速度。月面定点上的初值是依据火箭大约在地面上200公里高空以第二宇宙速度发射的假定选取的。所用方法是按作用范围和简单的角动量和能量守恒的原理来考虑的。计算结果表明,火箭从地面上以通常的高度和速度发射能够击中这六个定点:东点可以垂直击中,西点只能切向击中。航测这六个定点,都可以找到有去有回的轨道,航测远、近、南、北四点还可以有对称的轨道。航测远、近点可以和月面接近到任意距离,航测其他各点,距离便要远些,约为二、三万公里。

     
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