Summarized: Succession development of sedimentary systems, structure controlling deposition centre, deposition space migration significantly, frequent changes of water depth.

As a hot spot on the research of space navigation in recent years, X-ray Pulsar-based Navigation ( XPNAV) can offer abundant navigation information, such as position, velocity, attitude and time etc. for the spacecrafts in near-Earth orbit, deep space and interplanetary space.

X射线脉冲星导航（X-ray Pulsar-based Navigation，XPNAV）是近几年空间导航领域研究的热点，可为近地轨道、深空及星际空间飞行的航天器提供位置、速度、姿态和时间等全面的导航信息。

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A new method for measuring near-earth orbit ballistic parameters of multi, faint, small and dim targets is proposed on the basis of analysis and demonstration of sensor selection for multi-target detection, target extraction and data processing.

在对多目标探测所用传感器的选择、目标提取和数据处理等三方面技术问题进行分析论证的基础上，提出了一种新的多、弱、小、暗目标近地弹道参数测量方法。

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In this paper we did research on the heat flow, temperature, structural changes, and their influencing factors of parabolic satellite antenna in near-earth orbit, which provides future theoretical references for antenna thermal and structural design.

本文以抛物面型星载天线为研究对象，分析其在近地轨运行时的外热流、温度场和结构场的变化情况和影响因素，为天线的热设计和结构设计提供理论依据。

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Space debris will make available space in the outer space more and more crowded. In particular, the pollution of near-earth orbit space will increase the accident rate in the outer space.

空间碎片会使外空可利用空间越来越拥挤，尤其对于近地轨道空间的污染，会加大外空事故率。

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The property can offer position, velocity, and accurate time navigation information for the spacecrafts in near-earth orbit, geostationary orbit, elliptic orbit or interplanetary orbit.

这一特性使其能够为近地轨道、地球同步轨道、大椭圆地球轨道、地月轨道及星际空间飞行的航天器提供位置、速度和时间等丰富的导航信息。

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The space experiments are carried out in the chinese sixteenth scientific and technological exploration satellite. The satellite was flew around the near-earth orbit about 15 days.

空间实验是在我国第16颗科学探测与技术试验卫星上进行的，卫星在近地轨道运行15天。

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The main consideration is the orbital control precision of orbit maneuver. Finally, through the whole orbital dynamics simulation, based on the high target orbit rendezvous mission, the verification of the orbital maneuver strategy is feasible.

最后本文通过全轨道动力学仿真，验证了基于高轨目标交会飞行任务的轨道机动策略是可行的。

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This paper provides a new optimal control method for orbital maintenance and maneuver, which begins with the kinetics equation of spacecraft and is based on the linear discrete optimal control theory, establishes the relative optimal control model and gives its solution.

从航天器的轨道运动学方程出发，运用线性离散系统最优控制理论，提出了一种用于航天器轨道维持与轨道机动的最优控制方法，建立了相关的最优控制模型并给出了求解该模型的算法。

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Finally, this paper tried to start a new research field that named as Rendezvous Area and Space Control Body, by introducing these concept, visualization for large scale orbital maneuver was able to show directly.

最后，论文尝试性的提出并研究了点对面的机动及追踪器控制体的概念，给出了高度直观的大范围轨道机动可及范围，从面的覆盖的概念上分析得到了最佳机动时限。

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Hydrogen and oxygen orbital maneuver thruster, based on gas-dynamic resonance ignition, is a new liquid rocket propulsion technology, and is especially applicable to space station.

基于气动谐振点火技术的氢/氧变轨发动机是一项新型的液体火箭推进技术，尤其适用于空间站应用。

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When the satellite takes orbital maneuver, the control force may stimulate the vibration of the flexible appendages and, therefore, affects the attitude of the satellite.

卫星轨道控制期间，轨道控制推力会激振挠性太阳帆板，从而也影响卫星的姿态。

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According to the requirements of our Earth observation satellite's orbital maneuver mission, this paper designs and implements the software module and primary program for orbital maneuver.

针对我国对地观测小卫星的轨道机动任务要求，该文设计了轨道机动的软件模块和主要程序。

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A new intelligent planning algorithm which is used for fixed-time, point-to-point, multi-impulse orbital maneuver in the two-body problem is proposed in this paper.

针对二体轨道模型，设计了一种时间固定点对点多冲量轨道机动的智能规划算法。

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Orbital maneuver is the primary condition for satellite autonomy, and it is the basis of phase keeping, phase maneuver and rendezvous.

卫星轨道机动是卫星自治的首要条件，它是相位保持、相位机动、交会对接的基础。

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The attitude control law is designed for the orbital maneuver with considering the output character of the attitude control thrusters.

根据姿态控制推力器的输出特性，设计了轨道控制期间卫星姿态控制方案。

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This paper systematically analysis the orbital maneuver strategy of high target orbit rendezvous mission on each flight phase.

本文系统分析了高轨目标交会飞行任务的轨道机动策略，对各飞行阶段进行了研究分析。

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Close Approach of Walker Constellation Without Orbital Maneuver

单个航天器对Walker星座中多卫星的近距离接近

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Close Approach of Multiple Satellites of a Constellation for a Single Spacecraft without Orbital Maneuver

无需变轨实现单航天器对星座中多卫星的近距离接近

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It provides a basic orbital maneuver arithmetic for aerospace tests and correlative simulations.

仿真结果合理，满足要求，为航天试验及相关仿真工作提供了一个基础的轨道机动算法。

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Application of orbital maneuver technique in aerospace

机动变轨技术在空间领域的应用

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