發(fā)布時間：2018-03-08 02:06

  本文選題：GRACE　切入點：精密定軌　出處：《中國地震局地震研究所》2013年碩士論文　論文類型：學(xué)位論文

【摘要】：低軌衛(wèi)星為地球科學(xué)帶來了革命性的發(fā)展階段，而精密的衛(wèi)星軌道則是衛(wèi)星應(yīng)用于其他科學(xué)研究的基礎(chǔ)。當(dāng)前低軌衛(wèi)星的廣泛應(yīng)用，為低軌衛(wèi)星精密定軌技術(shù)的發(fā)展提供了良好的外部環(huán)境。非差簡化動力學(xué)法作為低軌衛(wèi)星精密定軌的方法之一，充分利用衛(wèi)星的幾何和動力信息，在動力學(xué)模型和GPS觀測值幾何信息之間進(jìn)行選權(quán)平衡，削弱動力學(xué)模型誤差影響，定軌結(jié)果穩(wěn)定，精度高。固研究低軌衛(wèi)星的非差簡化動力學(xué)精密定軌具有一定的意義。 論文第一部分首先闡述了衛(wèi)星導(dǎo)航系統(tǒng)的發(fā)展及其目前國內(nèi)外星載GPS低軌衛(wèi)星精密定軌的研究現(xiàn)狀，，隨后介紹了衛(wèi)星精密定軌的基礎(chǔ)理論，包括時間系統(tǒng)、坐標(biāo)系統(tǒng)以及不同系統(tǒng)之間的轉(zhuǎn)換。闡述了衛(wèi)星無攝運動的二體問題，描述衛(wèi)星受攝運動，分析各種攝動力對衛(wèi)星軌道的影響量級及計算模型。同時介紹了低軌衛(wèi)星的幾何觀測模型，主要的誤差源及改正方法。 論文第二部分詳細(xì)介紹了簡化動力學(xué)法定軌的基本原理。以Bernese5.0軟件為平臺，設(shè)計了一套GRACE衛(wèi)星精密定軌流程，采用2011年年積日213~243共31天的GRACE衛(wèi)星星載GPS觀測數(shù)據(jù)，通過非差簡化動力學(xué)法解算GRACE_A衛(wèi)星與GRACE_B衛(wèi)星31天的簡化動力學(xué)軌道，并將結(jié)果與JPL發(fā)布的事后科學(xué)軌道進(jìn)行比較。結(jié)果顯示，GRACE_A衛(wèi)星在切向、法向和徑向上的中誤差分別為1.29cm、0.87cm和1.52cm；GRACE_B衛(wèi)星在切向、法向和徑向上的中誤差分別為1.32cm、0.94cm和1.61cm。兩者的3D-RMS值分別為2.17和2.28cm，精度都達(dá)到了厘米級。 論文最后部分簡要介紹了衛(wèi)星激光測距（SLR）的原理，采用2011年年積日213~243共31天SLR觀測數(shù)據(jù)，檢核GRACE_A衛(wèi)星與GRACE_B衛(wèi)星的軌道。結(jié)果顯示，每天反算的站心距與SLR解算的站心距差值中誤差均小于5cm，其中31天的平均中誤差分別2.5cm與2.6cm。
[Abstract]:Leo satellites have brought a revolutionary stage of development for Earth science, and precise satellite orbits are the basis for satellite applications in other scientific research. It provides a good external environment for the development of precision orbit determination technology for Leo satellites. As one of the methods of precise orbit determination for Leo satellites, the non-differential simplified dynamics method makes full use of the geometric and dynamic information of the satellites. The weight selection balance between the dynamic model and the geometric information of the GPS observation value is carried out, which weakens the influence of the dynamic model error, the orbit determination result is stable and the precision is high. In the first part of the thesis, the development of satellite navigation system and the current research status of satellite GPS Leo satellite precision orbit determination at home and abroad are described, and then the basic theory of satellite precision orbit determination, including time system, is introduced. The transformation of coordinate system and different systems. The two-body problem of satellite's nonperturbed motion is discussed, and the satellite's passive motion is described. The order of magnitude and calculation model of the influence of various perturbation forces on satellite orbit are analyzed. At the same time, the geometric observation model, main error source and correction method of Leo satellite are introduced. In the second part of the paper, the basic principle of simplified dynamical orbit is introduced in detail. A set of precise orbit determination process of GRACE satellite is designed on the platform of Bernese5.0 software. The spaceborne GPS observation data of GRACE satellite are used for 31 days. The simplified dynamic orbit of GRACE_A satellite and GRACE_B satellite for 31 days is calculated by using the non-differential simplified dynamics method, and the results are compared with the post-scientific orbit released by JPL. The results show that the GRACEA satellite is tangentially. The median errors in normal and radial directions are 1.29 cm / m 0.87 cm and 1.52 cm / g GRACEB respectively in tangential direction, 1.32 cm / 0 94 cm and 1.61 cm / m in radial direction, respectively. The 3D-RMS values of both are 2.17 and 2.28 cm respectively, and the accuracy reaches the centimeter level. In the last part of the paper, the principle of satellite laser rangefinder (SLR) is briefly introduced. The 31 days SLR observation data are used to check the orbit of GRACE_A satellite and GRACE_B satellite. The median error of the difference between SLR and SLR is less than 5 cm, and the average error of 31 days is 2.5 cm and 2.6 cm, respectively.
【學(xué)位授予單位】：中國地震局地震研究所
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2013
【分類號】：P228.4

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本文編號：1581922