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。
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.
随着小卫星应用领域的日益广阔和小卫星数量的不断增长，对小卫星轨道控制技术的要求也越来越高。
With the wide application of small satellite and its increasing quantity, the requirements for orbit control technology of the small satellite is becoming more strict.
届时地面控制人员将点燃助推器，把卫星送入预定轨道。
Ground controllers will then fire the booster, sending the satellite into its proper orbit.
印度在2008年将一颗卫星发射至月球轨道，不过在一年后，由于卫星通讯突然中断，科学家失去了对其控制而不得不将之抛弃。
India launched a satellite into moon orbit in 2008, but had to abandon it nearly a year later after communication links snapped and scientists lost control of it.
信息反馈校验指令控制方式普遍运用于同步轨道静止卫星的指令控制系统中。
The command remote control system with information feedback checking is commonly used in command control system of geostationary satellite.
本文研究如何用磁力矩器控制极地轨道上对地指向卫星的姿态。
This paper studies magnetic control of polar orbiting, nadir pointing satellite.
分析认为PPT是一种先进的小推力动力装置，特别适合于微小卫星的轨道转移、姿态控制、位置保持以及星座编队飞行。
It was showed that PPT was a kind of advanced propeller with small thrust, which was suitable to orbit transfer, attitude control, station keeping and formation flying for small and micro satellite.
针对卫星编队轨道构形在J2摄动干扰作用下被破坏的问题，给出了两种构形保持脉冲控制策略。
Two impulsive control strategys for formation keeping were put forward with regard to the problem that satellites formation could be destroyed under J2 perturbation.
基于多冲量轨道机动控制，研究应用微小推力发动机来实现卫星编队轨道机动控制的方法。
Based on the multi-impulse method of orbit maneuvers, the method to enable the whole satellite formation to maneuver with micro-propulsion thrusters was studied in this paper.
本文利用整体微分几何的方法研究了人造卫星的轨道控制和姿态控制问题。
The orbit control and attitude control problems of satellite have been studied in this thesis by use of global differential geometry method.
小卫星在实际运行中受到多种摄动力的作用，这会对其轨道造成不同程度的影响，因此在小卫星的轨道设计与控制中，摄动是必须考虑的重要因素。
Micro satellite is under the influence of perturbative forces which would affect its orbit, so it is important to consider these perturbations in micro satellite orbit design and control.
根据极地轨道地磁场变化的特性，利用卫星的姿态角和姿态角速率作为反馈信号，提出了一种采用磁力矩器的比例微分(PD)控制规律设计方法。
Taking into account properties of the geomagnetic field, a new PD magnetic control law using the feedback information of attitude Angle and attitude rate is developed.
其中半实物仿真节点是自行设计的。仿真节点根据卫星运行轨道通过控制以太网接口模拟卫星网络星际链路切换，改变网络拓扑结构。
The semi-physical node controls the interface of Ethernet according to the satellite orbit and simulates the handoff of ISL, and so changes the topology of satellite network.
根据相对轨道要素的变轨机动控制，进行编队飞行卫星群构型的初始化。
The configuration initialization of satellite formations is carried out based on orbit maneuver control...
针对这一难点，提出了一种卫星轨道快速计算的方法-提取轨道的控制点，结合透视裁剪体来判断轨道的可见性。
According to this difficulty, a kind of fast calculation method of satellite orbit-extract the orbits control points is put forward, and perspective frustum is combined to judge the orbits visibility.
根据卫星在轨运行数据，给出了卫星在轨运行的部分曲线和姿态控制、轨道控制的指标实现情况，对姿态控制分系统方案进行了在轨验证。
According to operation data of the satellite on orbit, some operation results and the specification conformity are presented. Furthermore, the control system scheme is demonstrated on orbit.
运用卫星低轨道两个主要环境力矩(重力梯度矩和地磁力矩)对圆轨道卫星三轴姿态进行被动控制。
In this paper, three-axis passive stabilization is realized by using two main environment torques (gravity gradient and geomagnetic torque) in low orbit.
其次，针对编队飞行卫星队形保持控制，以对地等张角绕飞编队为背景设计相对轨道模型预测控制算法。
Secondly, a model predictive control method is designed for the satellite formation keeping and formation of invariant angular to the ground as the background.
电动力绳系卫星的推力幅值较小且方向固定，完成轨道机动任务的周期长，其最优控制问题的求解比较困难。
Electrodynamic tethers with low thrust-to-weight ratios can only perform orbital transfers over a large number of revolutions, which poses a real challenge to short time scale optimal control methods.
应用卫星绝大部分都是近圆轨道的卫星 ，其中又有很多是需要进行轨道控制的。
Most of application satellites are running in near circular orbits, and many of them need to be controlled.
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。
The attitude control law is designed for the orbital maneuver with considering the output character of the attitude control thrusters.
本软件依据卫星轨道参数控制伺服跟踪系统，完成对卫星的实时跟踪。
This software can control servo tracking system basing on satellite orbit parameters and realize the real-time tracking of satellite.
本软件依据卫星轨道参数控制伺服跟踪系统，完成对卫星的实时跟踪。
This software can control servo tracking system basing on satellite orbit parameters and realize the real-time tracking of satellite.
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