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  lunar surface
     Following above analysis, the atmospheric Tip-Tilts are computed real time with the two programmes from the lunar surface images near the Apollo 15 retro-reflectors, and the long exposure images with and without the Tip-Tilt are compared and the two algorithms are compared again with the data.
     在此基础上,我们利用两个算法程序对Apollo15月面反射器附近的月貌图像进行了大气波前倾斜量的提取,达到了实时获得大气倾斜量的目的,同时进行了去除大气波前倾斜量的长曝光像和未去除大气波前倾斜量的长曝光像的比较,并利用实验数据再次比较了两种算法的优劣。
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     In this case the time interval of the earth tracking data should be no shorter than 75 seconds, the continuous tracking time should be no less than 30 day and night, and the interval of the sub lunar points on the lunar surface should be no larger than 110km.
     地面跟踪最好能以75s的时间间隔进行采样,数据连续提供时间应不少于30个昼夜,月球卫星星下点的月面轨迹间距不大于110km .
短句来源
     In this paper, some important progress and recent results in the field were presented comprehensively, including some main concepts (albedos, phase function, photometries of the whole lunar disk and regions), photometry models, measured results of spectral albedo, especially the analyzed and researched results of the whole lunar surface and regions obtained from the data of spacecraft Clemmentine data photometric parameters, distributions of temperature, FeO and TiO_2 contents on the lunar disk, maturity of lunar regolith, ejection from basins, pyroclastic deposits, as well as regional geology.
     本文综述一些重要进展和最新成果,包括一些主要概念(反照率,位相函数、全月面累积测光和区域测光)、测光模型、分光反照率测定结果,尤其是Clemmentine飞船资料的分析研究结果———光度参数、月面温度分布、FeO和TiO2分布、月壤成熟度、盆地抛出物、火山沉积物和区域地质.
短句来源
     To promote a global and thorough understanding about the moon, the scientific objectives of "rotation" exploration include mapping the three-dimension images of the global lunar surface, detecting the distributions and contents of 14 elements of the lunar surface materials, exploring the thickness of the lunar regolith and evaluating the resources of3He in lunar soils, exploring the influence of the solar activity on lunar space environments.
     为了全球性、整体性重新认识月球,绕月卫星探测的科学目标为获取全月面三维影像,探测14种有用元素的全球分布与丰度,探测月壤厚度并估算3He资源量以及太阳活动对空间环境的影响。
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     The Vision Navigation Based on Lunar Surface Control Point Registration
     基于月面特征点配准的视觉导航
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  “月面”译为未确定词的双语例句
     Image segmentation and recognition of lunar rover
     月面巡视探测器的图像分割及识别方法
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     Utilizing the periodical analysis of variance and the method of mean generation function,predictions are made of La Nina,EI Nino,sunspots and the monthly mean areal rainfall over the Songhua River,Nenjiang River,and the second Songhua River regions from 2004 to 2013.Hereby,the lowest water level predictions of Songhua River at Harbin from 2004 to 2013 are revised.
     利用方差周期方法、均生函数方法对2004~2013年拉尼娜、厄尔尼诺、太阳黑子及松花江、嫩江、第二松花江流域月面雨量进行预测,并以此预测对2004~2013年松花江干流(哈尔滨段)最低水位进行订正,得出预测结论。
短句来源
     Based on the total areal rainfall of the Songhua River,Nenjiang River, and the second Songhua River from July to November and the highest water level of the Songhua River mainstream of the previous year at Harbin,the lowest water levels of the Songhua River at Harbin from 2004 to 2013 are predicted.
     以松花江、嫩江、第二松花江流域7~11月面雨量总和及前一年松花江干流(哈尔滨段)最高水位为因子,预测2004~2013年松花江干流(哈尔滨段)最低水位。
短句来源
     The R-D method utilizes the spacecraft ephemeris data and Range-Doppler frequency information of the SAR echo data to produce an estimatign of the target position.
     距离-多普勒(R-D)定位法是利用卫星星历数据和雷达回波数据的距离-多普勒信息对SAR图像目标进行定位,因无须在视场中选参考点,这对月面目标定位具有重要意义。
短句来源
     COMPOSITION CHARACTERISTICS OF KREEP ROCKS AND UTILIZATION PROSPECT OF REE
     月面克里普岩成分特征及REE等资源开发利用前景
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  相似匹配句对
     MOON
    
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     The immortal explorer on the moon in the space
     在“永生”的太空探索者
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     A Preliminary Study on Simulation of Lunar Surface Terrain
     地形地貌环境模拟初步研究
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     and then digital terrain model can be generated.
     模型。
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     Red Moon
     《赤
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  lunar surface
Light Flashes Caused by Leonid Meteoroid Impacts on the Lunar Surface
      
It is likely that they were produced by the impacts of the stream particles on the lunar surface.
      
The basic material for investigations is the scanned cosmic spectrozonal images of the lunar surface transmitted by the first Russian geostationary artificial meteorological satellite GOMS.
      
Estimation of the Area of the Perpetually Shaded Lunar Surface
      
The calculations are based on data on the distribution of lunar craters derived from the diameter/depth ratio and on the assumption of the equilibrium distribution of the crater population in the circumpolar areas of the lunar surface.
      
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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.

在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。

An expression of the meniscus liquid surface which is in contact with a solid wall is derived. The principle that controls the behaviour of the meniscus surface by means of different shapes of the solid wall is proposed, and the controlled condition of the meniscus surface is also calculated. Finally it is applied to achieve stable buoyancy of a specified float.

本文导出液体弯月面的一种表示式,提出用器壁形状控制弯月面形状的原理,计算了弯月面受控条件。文章最后把这个原理应用到浮子上,实现了浮子的稳定漂浮。

 
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