共查询到20条相似文献,搜索用时 31 毫秒
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对于航天工程而言,无论是航天器的发射,卫星轨道设计,地面测控系统的跟踪、定轨和预报.还是卫星在轨运行过程中的轨道控制策略等,均需了解卫星轨道变化的规律。为此,本文对人造卫星(包括中心天体为快自转天体和慢自转天体两种引力源的绕飞轨道器)的轨道变化特征以及轨道寿命进行系统的综合分析。为各种应用提供简明信息。 相似文献
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要成功地发射一个深空探测器进入目标轨道,相应的运行过程基本上涉及3个阶段:近地停泊轨道运行段、转移轨道的过渡段和进入目标天体的绕飞段。它们各自的运行状态和相应的数学模型有所差别,特别是转移轨道段的运行特征与绕飞段的卫星轨道的典型特征之间的重大差别,在深空探测任务中受到广泛的重视,如平动点利用中的晕(Halo)轨道和引力加速的节能过渡等。然而,就太阳系而言,这些不同轨道之间有一共同的基本性态,那就是都可以用在牛顿万有引力定律制约下的开普勒轨道(或变化的开普勒轨道)来刻画。本文将针对上述不同运行段轨道对应的数学模型、研究方法和结果,结合我们所做的工作进行综述。 相似文献
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Recent advances in NASA's Deep Space Network station calibration methods have led to renewed interest in the use of differenced radio metric data types for interplanetary navigation, particularly differenced Doppler and range. An orbit determination error analysis is described which compares the performance of these differenced data types when used in concert with conventional two-way Doppler for precise navigation for high-earth orbiters. Three highly elliptical orbits were investigated, with apogee heights on the order of 20000, 70000, and 156000 km. The analysis assumes that each orbiter's downlink antennas has no ground footprint limitation in the near apogee regime. Results indicate that the most significant navigational accuracy improvements are seen for the lowest altitude orbit by using differenced Doppler measurements in conjunction with two-way Doppler. The results for the two higher-altitude orbits, although less dramatic, suggest accuracy improvements can also be achieved when differenced range measurements are combined with two-way Doppler 相似文献
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Vonbun F.O. Argentiero P.D. Schmid P.E. 《IEEE transactions on aerospace and electronic systems》1978,(6):834-842
The results are reported of the ATS-6/GEOS-3 and the ATS-6 NIMBUS-6 satellite-to-satellite orbit determination experiments. NASA intends to use the tracking data relay satellite system for operational orbit determination of NASA satellites. Hence, in the near future, satellite-to-satellite tracking data will be routinely processed to obtain orbits. The satellite-to-satellite tracking system used in the ATS-6/NIMBUS-6 and ATS-6/GEOS-3 experiments performed with a resolution of 1 to 2 m in range and less than 1 mm/s in range rate for a 10-s averaging. A Bayesian least squares estimation technique utilizing independent ranging to the synchronous relay satellite was determined to be the most effective procedure for estimating orbits from satellite-to-satellite tracking data. The use of this technique yields estimates of user satellite orbits which are comparable in accuracy to what is usually obtained from ground based systems. 相似文献
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小卫星星座自主定轨的论证与仿真 总被引:1,自引:0,他引:1
在建立星座自主定轨条件方程的基础上,对其求解的可行性进行了分析、论证和仿真计算。结果表明:在仅考虑一阶摄动理论的情况下,升交点赤经总是秩亏的,即使考虑更精密的摄动模型,其条件方程也近似病态。其它根数在很多情况下也有相关性。因此,为了最大限度地满足自主定轨的要求,在星座结构设计时应尽量考虑不同类型轨道的卫星。 相似文献
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小卫星编队飞行的相对运动学方程研究 总被引:6,自引:0,他引:6
以运动学方法为基础研究了编队卫星相对运动的一种更直接方法,利用不同天体力学特性,将相对位置和速度与相对轨道参数建立了联系,首先,详细推导了以运动学方法为基础的相对运动方程,据此可直接得出环绕卫星的轨道根数,其次,为有利于相对轨道分析和设计,对相对运动方程进行了简化,最后,通过例子验证了该方法的正确性,仿真结果表明该方法是有效可行的。 相似文献
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Liqian ZHAO Xiaogong HU Chengpan TANG Shanshi ZHOU Yueling CAO Qianxin WANG Ranran SU 《中国航空学报》2022,35(4):332-343
Precise Point Positioning(PPP) requires precise products, including high-accuracy satellite orbit and clock parameters. It is impossible to obtain an orbit solution that is sufficiently accurate for PPP services with a regional tracking network; therefore, satellite orbits are usually estimated by a global tracking network with a large number of ground stations. However, it is expensive to build globally distributed stations. Fortunately, BeiDou-3 satellites carry an InterSatellite Link(ISL) pay... 相似文献
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近年提出了利用地月系平动点建立深空导航星座的设想。在受太阳摄动的真实力模型下,地月系平动点是不稳定的,从而会导致导航星座必须通过控制才能定点在特定区域。针对此问题,引入一种特殊的平动点轨道,即动力学替代轨道。平动点轨道卫星星座可利用星间测距数据自主定轨,由于动力学替代轨道具有长期稳定性,整个自主定轨过程不需要来自地面的测控支持,且定轨精度可达到观测精度。研究结果表明,观测资料的长短、导航卫星垂直白道面的运动分量都将影响到导航星间的自主定轨精度。该研究成果可以应用在以后的地月系导航星座中。 相似文献
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Considerable experience accumulated during the past decade in strategies for processing GPS data from ground-based geodetic
receivers. First experience on the use of GPS observations from spaceborne receivers for orbit determination of satellites
on low altitude orbits was gained with the launch of TOPEX/POSEIDON ten years ago. The launch of the CHAMP satellite in July
2000 stimulated a number of activities worldwide on improving the strategies and algorithms for orbit determination for Low
Earth Orbiters (LEOs) using the GPS.
Similar strategies as for ground-based receivers are applied to data from spaceborne GPS receivers to determine high precision
orbits. Zero- and double-differencing techniques are applied to obtain kinematic and/or reduced-dynamic orbits with an accuracy
which is today at the decimeter level. Further developments in modeling and processing strategies will continuously improve
the quality of GPS-derived LEO orbits in the near future. A significant improvement can be expected from fixing double-difference
phase ambiguities to integer numbers. Particular studies focus on the impact of a combined processing of LEO and GPS orbits
on the quality of orbits and the reference frame realization.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
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A radar waveform design technique which utilizes Lagrange's method of multipliers to control temporal sidelobes and to reduce Doppler sidelobes is described. This classical method of constrained optimization is applied to the problem of synthesizing a radar wave-form where mismatch loss is the objective function to be minimized. The associated constraints are taken from expressions for the composite temporal sidelobes of the cross-correlation response and the peak correlation response where sets of code words are used to modulate a series of radar pulses. The resulting code sets and receiver reference sets are called group-complementary and produce a trench parallel to or on the range axis of the cross-ambiguity surface. 相似文献
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双星导航系统的建立,为我国实现自主的卫星天基测控技术提供了可能。同时由于其全天候、全天时、相对定轨精度高等特点可望成为一种低、中轨卫星精密定轨的有效手段。但由于双星系统中静止卫星数目仅有两颗,要得到低、中轨卫星的三维定位信息,还需要额外的第三维观测量。本文根据双星系统的现状,结合国内对低、中轨卫星精密定轨的要求,提出了一种基于双星系统的卫星几何学精密定轨的方法,概述了其基本原理及其组成,给出了卫星定轨的方法和数学模型,同时根据数据仿真分析了该定轨系统的定轨精度,为下一步工程实现提供了理论基础。 相似文献
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对航天器多普勒测速平均误差进行了分析,详细推导了圆轨道和椭圆轨道时该误差的计算公式,计算了不同采样周期和轨道高度时的误差大小。经过分析指出,该项误差对于高轨航天器影响较小,对于低轨航天器可以通过缩短采样周期或利用3个点或多个点的连续测量数据进行修正。 相似文献
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卫星轨道误差的相关性 总被引:1,自引:0,他引:1
卫星的轨道误差是卫星测控中需加以约定的重要指标之一,其常用的表示方法主要有Kepler轨道根数形式和RTN投影形式。本文推导了RTN形式的卫星位置、速度误差与Kepler根数误差间的关系,给出了近圆轨道中RTN形式位置、速度误差间的定量关系,分析了RTN形式位置误差约束下Kepler根数误差的相关性,并分别给出了验证算例。该结果可用于分析确定卫星轨道误差指标,使其彼此匹配。 相似文献