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orbital    
相关语句
  轨道
    ORBITAL IMPROVEMENT OF MINOR PLANETS (215) (323) (416) AND (432)
    小行星(215)、(323)、(416)和(432)的轨道改进
短句来源
    LONG-TERM PERIOD CHANGES AND PHOTOMETRIC ORBITAL SOLUTION OF RZ DRACONIS
    天龙座食双星RZ周期的长期变化及其测光轨道
短句来源
    The Variations of the Light Curves and the Orbital Period of the Close Binary 44i Boo
    密近双星44i Boo的光变起伏及轨道周期的变化
短句来源
    Orbital Radius of the Test Particles in the Equatorial Plane of the CM Field
    试验粒子在CM场赤道平面的轨道半径
短句来源
    THE ORBITAL VARIATIONS OF BALLOON SATELLITES 1990-81B AND 1990-81C AND DETERMINATION OF AIR DENSITY
    气球卫星1990—81B和1990-81C的轨道变化和高层大气密度的测定
短句来源
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  轨道的
    the results show that tidal friction diminishes the total energy of binaries systems with shorter orbital periods.
    计算结果表明 ,潮汐作用使轨道周期较小的Ba星系统的能量减小 ,所以系统轨道的半长轴和轨道偏心率减小 ;
短句来源
    This paper improved these methods based on the requirements 0There are two methods for conventional orbital control: one is algebra method which deals with the problems by optimization based on orbit geometry characteristics The first method is applied when we adopt impulsive control, but in the multiobjective cases the method has its limitation.
    传统的轨道控制一般基于两种方法,一种是代数优化方法,这种方法与卫星的轨道几何特性相结合进行分析,将轨道的几何特性和优化指标用代数方程的形式表示出来进行求解,这种方法主要用于冲量式控制。 但在多指标的要求下,这种方法难以求得最优解;
短句来源
    The differences in orbital morphologies due to different potentials is slighting, however, given a certain potential, for clusters that have perigalactic distance smaller than 1 kpc, some orbits may exhibit a chaotic behavior.
    不同的引力势模型对球状星团轨道的具体形态影响不大,在给定的引力势模型下,当某些星团的运动轨道穿越距银心1kpc附近的区域时会出现“混沌”现象:
短句来源
    The orbital perturbations of a spacecraft with the monochromatic gravitational plane waves are discussed here.
    本文讨论了单色平面引力波对宇宙飞船轨道的影响。
短句来源
    With the phase plane analysis method, we obtain the general relativity motion equation in the gravitational field of the extreme charged black hole, and we plot the picture of the orbital phase plane and analyze the orbital stability.
    运用相平面分析法 ,通过求解广义相对论运动方程 ,得到了在极端荷电黑洞引力场中运动的天体的轨道方程 ,同时作出了轨道相平面图并分析了其轨道的稳定性
短句来源
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  orbital
We also construct the ideal of definition of such an orbital variety up to taking the radical.
      
The hydrophobic parameter, dipole element, frontier molecular orbital energy gap and hydration energy of these hydrocarbons were calculated with the PM3 semi-empirical quantum chemistry method.
      
Penicillium expansum, a Resident Fungal Strain of the Orbital Complex Mir, Producing Xanthocyllin X and Questiomycin A
      
It was demonstrated that the fungus Penicillium expansum 2-7, a resident strain of the orbital complex Mir, which became dominant at the end of a long-term space flight, formed biologically active secondary metabolites (antibiotics).
      
These elements can find use in the problems of departure and transfer to the parking orbit, as well as in the problems of orbital transfers.
      
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For use in cosmogonical investigations,a detailed calculation of the angular momenta of various bodies in the solar system is made,making use of latest data. A_(1P) denotes the orbital angular momentum of a planet about the center of mass of the sun- planet system,A_(1⊙) denotes the orbital angular momentum of the sun about the same center of mass.A_(1P)+A_(1⊙)=A_1.These three quantities are calculated according to formulae (2),(3),(4), and the results are given in Table 1.In this table A_(1P) includes...

For use in cosmogonical investigations,a detailed calculation of the angular momenta of various bodies in the solar system is made,making use of latest data. A_(1P) denotes the orbital angular momentum of a planet about the center of mass of the sun- planet system,A_(1⊙) denotes the orbital angular momentum of the sun about the same center of mass.A_(1P)+A_(1⊙)=A_1.These three quantities are calculated according to formulae (2),(3),(4), and the results are given in Table 1.In this table A_(1P) includes the orbital angular momentum of the planet's satelfites about the center of mass of the sun-planet system.

任何有关太阳系起源的学说都必须能够说明太阳系角动量分布的特殊性,这种特殊性首先由傅歇于1884年指出来.拉普拉斯的星云假说未能说明这种特殊性.本世纪开始以来,先后提出的各种学说都注意到这个问题,但是都未能满意地说明它.最近十多年来,有关行星和卫星的各种数据有了相当多的增添和改进,恒星和行星内部结构的研究有了很大的进展,使得有可能得出太阳和各个行星的自转角动量的较可靠的数值.本工作的目的就是利用最新的数据来计算太阳系各天体的角动量,为太阳系起源问题的研究提供资料.

The general perturbations on this minor planet by the action of JUPITER and SATURN were computed by Bohlin's method and the orbital corrections were made by Tietjen method. Finally,after the orbital corrections were made by means of Eckert's method,the following average residuls have been obtained:|Δα|=196 and |Δδ|=218.

1°.利用波林(Bohlin)方法计算这颗小行星受木星和土星的普遍摄动并利用惕仁(Tie-tjen)方法作轨道改进.2°.取上面获得结果为第一近似值,再用爱克(Eckert)方法作轨道改进获得平均残差|Δα|=1~s.96,|Δδ|=21″.8.

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 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。

 
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