查询词典 hyperbolic orbit

Firstly, This paper processes geometry filtration based on character of orbit's apogee and perigee after orbit model is analyzed and based. Secondly Space Debris is separated into two kinds, coplanar and not coplanar according as location interrelation of target and debris. In Dynamic filtration's processing, considering prediction time limit and orbit perturbation, secular effects which have increaser effect is considered so that some need catching danger time point is appeased, some law about time when target and debris pass intersectant line each other is inferred, when debris and object are in different plane and some similar law also is inferred otherwise. The time list is arithmetical progression. These laws can improve calculation efficiency remarkably; Lastly orbit predict is a course approaching least distance. Danger time point in the last step become beginning time point from which debris and object's position and velocity are calculated by SXP4 Model which is an analytic model.By result, determine that relative movement trend is closer or apart, farther calculate the interval apart from time when predictive least relative distance occurs. Least relative distance and time when least distance occurs is calculated finally. It is a fast approach course adopting varied interval.

本文在分析、建立轨道摄动计算模型的基础上，首先采用基于轨道远、近地点特征对大量编目在册的空间碎片进行初步几何静态筛选，然后根据碎片与目标轨道面的相对位置特点把碎片分为异面与准共面两种情况以进行动态筛选，在筛选过程中考虑到预报时限长度和轨道摄动影响，引入了轨道摄动中具有积累效应的长期项以满足危险时间点的捕捉要求，利用了长期项摄动变化线性的特点导出了碎片与目标异面情况下各自过交线的时间序列成准等差数列的规律性和准共面情况下类似的规律性，从而显著地提高了前期轨道筛选的计算效率；最后对剩余危险碎片和目标飞行器利用SXP4轨道预报模型在前期轨道筛选的基础上以各个危险探测时间点为预报的时间起点，并根据预报计算结果，分析目标和碎片在该时间点的运动趋势是相互远离还是相互接近，推出预计最小相对距离发生时刻相对此刻的时间长度，得到其随时间变化的局部最小相对距离以及危险距离发生的时刻和相对速度，这是一个采用变时间步长、快速逼近最小相对距离的过程。

In this dissertation, the design and optimization of lunar probe orbit has been studied by using the theory and method of spacecraft orbital dynamics, aiming at to launch polar moon satellite from the earth parking orbit, and considering synthetically the problems about the launcher energy, flying time, launch window and orbit navigation. The flying conditions, program and orbit of the lunar probe are given.

本论文利用航天器轨道动力学理论和方法，以从地球停泊轨道入轨点出发发射月球极月卫星的轨道为对象，综合考虑运载能力、飞行时间、发射窗口、轨道导航等问题，进行月球探测器轨道设计与优化，给出月球探测器的飞行条件、程序及其轨道。

Stable and Unstable Orbit: An orbit is unstable if slight perturbations will cause the spacecraft moving on the orbit to leave the orbit and move far away.

稳定和不稳定轨道：不稳定的轨道上，如果稍有扰动将导致飞船在轨移动到离开轨道和移动远。

Afterwards, using the spherical tensor form of many-electron atom Hamilton and the irreducible tensor theory, the relativistic and fine-structure energy correction to the non-relativistic energy of Boron-like atoms in the ground and the first excited states have been further investigated. A theoretically analytic way has been given as to the calculation of all the radial integrations and spin summations, which concern interactions such as orbit-orbit, spin-orbit, spin-spin and spin-other-orbit. Therefore, the whole process of calculating the many- electron atom energy structures has been explicitly revealed and the results are relatively precise and satisfactory.

在此基础上，利用多电子原子哈密顿算符的球张量形式和不可约张量理论，进一步研究了类硼离子基态和第一激发态非相对论能级的相对论修正和精细结构，给出了轨道-轨道、自旋-轨道、自旋-自旋、自旋-其它轨道等相互作用所涉及的所有角向积分和自旋求和的解析计算方法，清晰地展示了多电子原子结构计算的过程，得到了较为精确的理论计算结果。

Increasing observation accuracyand reducing the error of the measuring ship will improve the accuracy of orbit determination during Translunar orbit phase,and the reduced dynamic method and improvement of lunar gravity accuracy will benefit the accuracy of orbit determination during Misson Orbit phase.

在奔月阶段，提高观测量精度和减小测量船的点位误差将有助于提高定轨精度，而在环月阶段，采用减缩动力学方法和提高月球重力场精度将有助于提高定轨精度。

Starting from the four concepts of orbit energy, energy class, shielding effect and infixing effect, the author uses the two commonly applied methods of caculation orbit energy to analyse and compare 4s orbit energy and 3d orbit energy.

本文从轨道能、能级、屏蔽效应和钻穿效应这四个概念入手，运用计算轨道常见能量的两种方法进行分析和比较轨道能与 3d轨道

When the disturbing potential of 1m2/s2 accuracy, or the approximate velocity of accuracy less 2mm/s in the formula of the rotation of the gravity potential is required, the satellite orbit data not satisfied the potential rotation computing demand are rejected from the GFZs Rapid Science Orbit and TUMs ReducedDynamic Orbit. If the disturbing potential is desired 05m2/s2 at satellite track, the satellite velocity required in formula of the rotation of the gravity potential should be recomputed or the GFZs Postprocessed Science Orbit is adopted.

当要求在卫星轨迹处获得1m2/s2精度的扰动位时，也即要求位旋转效应公式中卫星速度的近似精度小于2mm/s时，GFZ的快速科学轨道、TUM的约化动力法轨道只需要剔除那些速度精度不满足要求的卫星轨迹点；当要求在卫星轨迹处获得05m2/s2精度的扰动位时，应当重新估算上述轨道的速度信息，或采用精度更高的GFZ事后科学轨道。

Edit this paragraph the reasons for the color reaction of flame When the alkali metal and its salts in the ignition flame, the atoms absorb the energy of the electron from the orbit of low-energy transition to a higher energy orbit, but at a higher energy orbit is unstable electronic, it is fast transition back to a lower energy orbit, then the energy will be redundant form to emit light.

编辑本段焰色反应的原因当碱金属及其盐在火焰上灼烧时，原子中的电子吸收了能量，从能量较低的轨道跃迁到能量较高的轨道，但处于能量较高轨道上的电子是不稳定的，很快跃迁回能量较低的轨道，这时就将多余的能量以光的形式放出。

The following conclusions are drawn. 1 The orbit parameters that have relatively greater influence on the number and latitudinal distribution of annual occultation events are orbit inclination, orbit height, Right Ascension of Ascending Node and Argument of Perigee in turn. All four parameters have little impact on the longitudinal distribution of annual occultation events. 2 The orbit inclination of Transmitting Satellite and Receiving Satellite impacts both LEO－LEO occultation events number and their latitudinal distribution most. The number of occultation events reaches the maximum as the sum of the two inclination angles nears 180 degrees. The one that far away from 90 degrees of the two inclination angles determines the latitude range of the occultation events. 3 LEO－LEO occultation events number reaches a maximum when the heights of TS and RS are the same, and it reaches the maximum when the heights of TS and RS are 600 km . 4 The RAAN of TS and RS has a great influence on the LEO－LEO occultation number, but has little influence on occultation distribution.

结果指出：1对一年掩星事件数量及其纬度分布影响大的轨道参数依次是轨道倾角、轨道高度、升交点赤经和近地点角距；而这些参数对一年掩星事件的经度分布影响都不大；2发射卫星和接收卫星倾角之间的相互关系对掩星事件数量和纬度分布影响最大，两卫星倾角接近互补时掩星事件最多，两颗LEO卫星中与90°相差较大的倾角决定了LEO－LEO掩星事件的纬度分布范围；3发射卫星和接收卫星处于同一轨道高度时，LEO－LEO掩星事件数取得极大值，发射卫星和接收卫星都采用600 km的轨道高度，一年LEO－LEO掩星事件数最多；4 发射卫星和接收卫星升交点赤经的相互关系对LEO－LEO掩星事件数量影响很大，发射卫星和接收卫星升交点赤经之差为120°或240°时掩星事件数量最多，RAAN对掩星事件纬度和经度分布影响不大；5近地点角距对掩星事件数量和分布影响都不大。

The Saturn V would be necessary to take it to polar orbit, or sun-synchronous orbit (neither of which has yet been achieved by any manned spacecraft), and even to the geosynchronous orbit of Syncom 3, a communications satellite not quite in geostationary orbit.

土星五是要以它为极地轨道或太阳同步轨道(既不是至今尚未取得任何载人航天器)，甚至威胁到地球同步转移轨道的syncom3号通信卫星不甚静止轨道。

There are different types of personal loans available.

有许多不同类型的个人贷款优惠。

The above mentioned teaching model of spiral rising can be used to avoid rigidness in teaching.

上述螺旋式上升的教学模式，可以避免教学形成模式後的僵化现象。