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relative orbital element
相关语句
  相对轨道根数
     A concept of natural formation and a general RT design method are proposed based on the Relative Orbital Element Method and the relative motion equation in this paper. An example is given.
     基于相对轨道根数法,根据卫星相对运动方程,提出了“自然队形”的概念及队形设计的一般方法,并给出了具体的例子。
短句来源
     This paper investigates the J2 perturbation effect on the relative orbital configuration of satellites in formation flying using the relative orbital element method and a high accuracy numerical algorithm.
     利用相对轨道根数法研究J2摄动对卫星编队飞行的相对轨道构形的影响,并利用高精度的算法进行数值仿真。
短句来源
  相似匹配句对
     FINITE THRUST ORBITAL CONTROL IN RELATIVE MOTION
     相对运动有限推力轨道控制
短句来源
     Being relative to O.
     相对于O.
短句来源
     Orbital Chloroma
     眼眶绿色瘤
短句来源
     On Relative Topology
     关于相对拓扑
短句来源
     Orbital neurofibromas
     眼眶神经纤维瘤
短句来源
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  relative orbital element
A new method developed from orbital element description of single satellite, named relative orbital element method (ROEM), was introduced.
      


To overcome the restriction of Hill's equation, this paper presents the orbital elements method for describing the relative motion of satellite formation flying. Theoretical conditions are derived for long term formation flying that includes the relationship between the relative distances and velocities and the relative orbital elements. The analysis proves that the orbital periods of formatted satellites must be equal. Simulation of the relative trajectories with...

To overcome the restriction of Hill's equation, this paper presents the orbital elements method for describing the relative motion of satellite formation flying. Theoretical conditions are derived for long term formation flying that includes the relationship between the relative distances and velocities and the relative orbital elements. The analysis proves that the orbital periods of formatted satellites must be equal. Simulation of the relative trajectories with various orbital elements and a qualitative theoretical analysis illustrate the advantages of the orbital elements method. The proposed method can be used for large eccentricity elliptical orbits and can be applied for orbit design of spacecraft formation flying. The results show that satellites formatted using closed orbital elements will remain in their orbits with little active control. The theoretical results show that the application of Hill's equation is restricted to short time formation flying in circular orbits.

为了克服 Hill方程的局限性 ,利用轨道根数描述卫星编队飞行 ,从理论上给出了长期编队所需的条件 ,包括相对位置和相对速度的关系 ,以及和各卫星相对轨道根数之间的关系 ;理论上证明了要长期近距离编队卫星轨道周期必须相同。仿真了各种不同轨道根数下的相对运动轨迹 ,与定性的理论分析进行比较 ,说明了轨道根数描述方法的优越性。方法可适用任意偏心率的椭圆轨道 ,将为飞行器编队飞行的轨道设计提供理论参考。不考虑摄动时轨道根数接近的飞行器不需主动控制而可长期保持近距离编队飞行

Satellites flying in formation can significantly improve the satellite capabilities. This paper analyzes the relative trajectories of satellite formation flying using the orbital elements method, which avoids approximations to provide accurate results. The relative motions are classified for various orbital elements. Comparisons are made between coplanar and noncoplanar relative trajectories, small and large eccentricity elliptical trajectories, etc. The results...

Satellites flying in formation can significantly improve the satellite capabilities. This paper analyzes the relative trajectories of satellite formation flying using the orbital elements method, which avoids approximations to provide accurate results. The relative motions are classified for various orbital elements. Comparisons are made between coplanar and noncoplanar relative trajectories, small and large eccentricity elliptical trajectories, etc. The results show that the semimajor axis of each satellite should be equal in formation flying, and the relative orbit configuration depends on the relative orbital elements, illustrating the methodology for the design of satellite formation flying missions. 

卫星编队飞行具有广阔的应用前景,为此应用轨道根数研究卫星编队飞行的相对运动,得到了精确的相对运动轨迹。对轨道共面、轨道不共面,小偏心率椭圆轨道(包括圆轨道)、大偏心率椭圆轨道等情况进行了对比,对各种可能出现的轨道构形进行了归类。研究表明:卫星编队的条件是轨道半长轴相等,相对轨道构形依赖于中心卫星与伴随卫星的相对轨道根数,而与中心卫星的轨道根数无关。这些结论为编队飞行的任务设计提供了理论依据。

Recently the research of Satellite Formation Flying (SFF) has increased significantly. The characteristic and potential advantage of SFF is that several following-satellites along with the leader-satellite in close vicinity make up a special formation to accomplish certain mission. The Relative Trajectory (RT) is defined as the geometric pattern consisting of the centroid of each satellite, and the RT design is to find out those orbit elements of each satellite according to the geometric pattern...

Recently the research of Satellite Formation Flying (SFF) has increased significantly. The characteristic and potential advantage of SFF is that several following-satellites along with the leader-satellite in close vicinity make up a special formation to accomplish certain mission. The Relative Trajectory (RT) is defined as the geometric pattern consisting of the centroid of each satellite, and the RT design is to find out those orbit elements of each satellite according to the geometric pattern of the RT (the orbit elements of leader-satellite can be determined by performing mission first). A concept of natural formation and a general RT design method are proposed based on the Relative Orbital Element Method and the relative motion equation in this paper. An example is given.

目前关于卫星编队飞行的研究有显著的增加。多颗从属卫星(从星)在近距离内与主卫星(主星)组成特定的队形以完成相应的任务,是卫星编队飞行的特点及潜在优势。卫星在编队飞行时,其队形定义为以各颗卫星质心为顶点所构成的几何形状,而队形设计则是根据队形的几何形状求出各卫星的轨道根数(其中主星的轨道根数可以根据任务的要求事先确定)。基于相对轨道根数法,根据卫星相对运动方程,提出了“自然队形”的概念及队形设计的一般方法,并给出了具体的例子。

 
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