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   orbit fitting 在 自然地理学和测绘学 分类中 的翻译结果: 查询用时:0.051秒
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orbit fitting
相关语句
  轨道拟合
    Based on the orbit integration and orbit fitting method,the characters of the influence of the gravity model with different precision on the movement of low earth orbit satellites was studied. The way and the effect of reducing the influence of gravity model error to CHAMP and GRACE satellites orbits by liner and periodical empirical acceleration model and so-called "pseudo-stochastic pulses" mode were also analyzed.
    分析了不同重力场对低轨卫星运动影响的特征,并基于CHAMP卫星和GRACE卫星的真实轨道,利用轨道积分和轨道拟合的方法,研究了线性分段加速度、周期性分段加速度以及虚拟随机脉冲加速度在精密定轨中对重力场模型误差的补偿效果。
短句来源
    Some significant comparisons are made between the 15-parameter method of GPS broadcast ephemeris and the designed 25-parameter method, the results show that the designed 25 parameters method has a higher precision for LEO satellite orbit fitting under the same condition.
    同时对GPS广播星历15参数法与设计的25参数法进行了拟合对比,结果表明,同样条件下25参数法应用于低轨卫星轨道拟合时精度较高。
短句来源
  轨道拟合
    Based on the orbit integration and orbit fitting method,the characters of the influence of the gravity model with different precision on the movement of low earth orbit satellites was studied. The way and the effect of reducing the influence of gravity model error to CHAMP and GRACE satellites orbits by liner and periodical empirical acceleration model and so-called "pseudo-stochastic pulses" mode were also analyzed.
    分析了不同重力场对低轨卫星运动影响的特征,并基于CHAMP卫星和GRACE卫星的真实轨道,利用轨道积分和轨道拟合的方法,研究了线性分段加速度、周期性分段加速度以及虚拟随机脉冲加速度在精密定轨中对重力场模型误差的补偿效果。
短句来源
    Some significant comparisons are made between the 15-parameter method of GPS broadcast ephemeris and the designed 25-parameter method, the results show that the designed 25 parameters method has a higher precision for LEO satellite orbit fitting under the same condition.
    同时对GPS广播星历15参数法与设计的25参数法进行了拟合对比,结果表明,同样条件下25参数法应用于低轨卫星轨道拟合时精度较高。
短句来源
  “orbit fitting”译为未确定词的双语例句
    By analyzing the fitting precision of satellite prediction orbit determined by GLONASS(global navigation satellite system) broadcast ephemeris,it is pointed out that the simplified models of perturbation force,the choice of numerical integration methods and the neglect of the polar motion are main factors causing the orbit fitting error,among which the simplified models of perturbation force is the most effective one. Through integrating the equation of orbital motion of satellite for 30?
    通过分析由GLONASS(Global Navigation Satellite System)广播星历参数确定的卫星预报轨道的拟合精度,指出了摄动力模型的简化、积分器的选择,以及忽略了极移影响等因素是引起拟合误差的主要因素,其中摄动力模型的简化起最主要的作用.
短句来源
    min,it can be found that the orbit fitting error due to the simplified force model,the numerical integration method and the neglect of the polar motion are respectively 0.827? m,0.224? m and 0.025?
    通过对卫星轨道运动方程积分30 min,可知由摄动力模型的简化、积分器和忽略极移影响等因素引起的拟合误差分别为0.827 m,0.224 m和0.025 m.
短句来源
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  orbit fitting
Therefore, we have to solve first the identification problem, finding two or more TSAs belonging to the same physical object and an orbit fitting all the observations.
      
Based on the orbit integration and orbit fitting method, the influence of the characters of the gravity model, with different precisions, on the movement of low Earth orbit satellites was studied.
      
If however such a procedure is not of sufficient precision, then dynamic model-based orbit fitting would have to be applied.
      


The equation of satellite orbital motion was derived in the conventional terrestrial coordinate system.By analyzing the fitting precision of satellite prediction orbit determined by GLONASS(global navigation satellite system) broadcast ephemeris,it is pointed out that the simplified models of perturbation force,the choice of numerical integration methods and the neglect of the polar motion are main factors causing the orbit fitting error,among which the simplified models of perturbation force is the most...

The equation of satellite orbital motion was derived in the conventional terrestrial coordinate system.By analyzing the fitting precision of satellite prediction orbit determined by GLONASS(global navigation satellite system) broadcast ephemeris,it is pointed out that the simplified models of perturbation force,the choice of numerical integration methods and the neglect of the polar motion are main factors causing the orbit fitting error,among which the simplified models of perturbation force is the most effective one.Through integrating the equation of orbital motion of satellite for 30?min,it can be found that the orbit fitting error due to the simplified force model,the numerical integration method and the neglect of the polar motion are respectively 0.827?m,0.224?m and 0.025?m.Therefore controlling the precision loss of orbital prediction cased by the simplification of models of perturbation force,especially by the truncation of high order terms of Earth gravitational perturbation and simplification of models of Sun and lunar gravitational fields can improve the fitting precision of prediction orbit.

推导了协议地球坐标系下的卫星运动方程.通过分析由GLONASS(Global Navigation Satellite System)广播星历参数确定的卫星预报轨道的拟合精度,指出了摄动力模型的简化、积分器的选择,以及忽略了极移影响等因素是引起拟合误差的主要因素,其中摄动力模型的简化起最主要的作用.通过对卫星轨道运动方程积分30 min,可知由摄动力模型的简化、积分器和忽略极移影响等因素引起的拟合误差分别为0.827 m,0.224 m和0.025 m.要提高预报轨道拟合的精度,关键是要对摄动力简化特别是地球引力摄动高阶项的截断以及日月引力场简化造成的轨道预报精度损失加以控制.

Based on the orbit integration and orbit fitting method,the characters of the influence of the gravity model with different precision on the movement of low earth orbit satellites was studied.The way and the effect of reducing the influence of gravity model error to CHAMP and GRACE satellites orbits by liner and periodical empirical acceleration model and so-called "pseudo-stochastic pulses" mode were also analyzed.

分析了不同重力场对低轨卫星运动影响的特征,并基于CHAMP卫星和GRACE卫星的真实轨道,利用轨道积分和轨道拟合的方法,研究了线性分段加速度、周期性分段加速度以及虚拟随机脉冲加速度在精密定轨中对重力场模型误差的补偿效果。

It gives perturbative force model which is adopted by orbit fitting and orbit prediction at length and dicusses the process of orbit fitting and orbit prediction.First,high precise osculating orbit parameters is attained by fitting orbit;then,it extrapolates the 7-days orbit;at last compares the 7-days orbit with the IGS final orbit in order to get the precision of orbit prediction of GPS satellites.For every satellite,the error of along track...

It gives perturbative force model which is adopted by orbit fitting and orbit prediction at length and dicusses the process of orbit fitting and orbit prediction.First,high precise osculating orbit parameters is attained by fitting orbit;then,it extrapolates the 7-days orbit;at last compares the 7-days orbit with the IGS final orbit in order to get the precision of orbit prediction of GPS satellites.For every satellite,the error of along track direction is distinct,but the error of radial and out of plane direction are not distinct;the precision of orbit prediction of eclipsing satellites is much lower than the common satellites;the error of orbit prediction of eclipsing satellites is especially large.

列出了轨道拟合和轨道外推所用的摄动力模型,讨论了轨道拟合和轨道积分的过程。利用轨道拟合的方法拟合出高精度的初始轨道参数,在此基础上外推7天的轨道,将结果与IGS提供的最终星历比较,得出GPS轨道的外推精度:每颗卫星都是切向误差最显著,径向和法向的误差不明显;星蚀卫星的轨道外推精度明显低于一般卫星;问题卫星的轨道外推误差特别大。

 
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