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  本文關(guān)鍵詞： 低軌衛(wèi)星 星載GPS 非差動力學(xué)定軌 APOD GRACE　出處：《中國地質(zhì)大學(xué)(北京)》2017年碩士論文　論文類型：學(xué)位論文

【摘要】：低軌衛(wèi)星因為其軌道高度的特殊特點,是最適合承擔應(yīng)用與科學(xué)實驗的平臺與載體,這使得低軌衛(wèi)星具有重要的戰(zhàn)略意義和科研價值。低軌衛(wèi)星高精度軌道確定是保證其順利完成各項科學(xué)實驗任務(wù)的前提與基礎(chǔ),星載GPS因其成熟的技術(shù)和無可比擬的優(yōu)勢成為實現(xiàn)低軌衛(wèi)星精密定軌的重要手段。本文圍繞基于星載GPS的低軌衛(wèi)星非差動力學(xué)定軌展開研究,通過理論研究,軟件實現(xiàn)相關(guān)關(guān)鍵算法,并以星載GPS數(shù)據(jù)為例,分析低軌衛(wèi)星軌道特點、驗證本文理論和軟件數(shù)據(jù)處理精度,在此基礎(chǔ)上本文給出一些重要結(jié)論。本文的具體工作如下:(1)介紹了星載GPS的觀測量與觀測方程,重點給出了星載雙頻接收機無電離層組合觀測模型,并分析了其觀測誤差源和各項誤差的改正方法,從觀測模型的角度為接下來的定軌問題研究打好基礎(chǔ)。(2)從動力學(xué)信息和衛(wèi)星運動狀態(tài)信息兩方面入手詳細闡述了低軌衛(wèi)星動力學(xué)精密定軌的原理,給出了軌道求解的數(shù)學(xué)過程。針對最小二乘批處理方法中鐘差參數(shù)過多的問題,給出了鐘差約化理論模型的公式推導(dǎo)過程和軟件實現(xiàn)方法。(3)研究拉格朗日插值法和切比雪夫插值法對IGS精密星歷擬合精度的影響,實驗證明:采用13階拉格朗日插值或切比雪夫插值都可以達到低軌衛(wèi)星精密定軌對GPS衛(wèi)星位置的精度要求;同時,分析了線性插值和三次樣條插值對不同時間間隔的IGS精密鐘差的插值性能,實驗證明在相同情況下,線性插值法比三次樣條插值法的插值精度要高,而且在低軌衛(wèi)星精密定軌中可采用IGS的30秒精密鐘差進行插值,以求得所需時刻的GPS衛(wèi)星鐘差。(4)參與編寫、調(diào)試、完善并測試了一套基于非差動力學(xué)方法的低軌衛(wèi)星定軌軟件平臺,本文介紹了軟件的功能結(jié)構(gòu)和定軌流程;利用該軟件平臺分別對國產(chǎn)微納衛(wèi)星APOD和國際知名的重力衛(wèi)星GRACE進行了多天軌道的計算,并對定軌成果進行了精度驗證。結(jié)果表明:APOD衛(wèi)星偽距和相位觀測值的內(nèi)符合精度分別約為2m和2.5cm,符合該衛(wèi)星科研項目需要,基于軌道重疊弧段檢驗的精度水平優(yōu)于分米級;GRACE-A衛(wèi)星偽距和相位觀測值內(nèi)符合精度分別在0.9m和1.2cm,基于軌道重疊弧段檢驗的精度水平在7cm左右,與PSO標準軌道比較,其三維位置精度約為12cm。
[Abstract]:Because of its special characteristics of orbital altitude, Leo satellites are the most suitable platform and carrier for applications and scientific experiments. This makes the Leo satellite have important strategic significance and scientific research value. The high-precision orbit determination of the Leo satellite is the premise and foundation to ensure the successful completion of various scientific experimental missions. Spaceborne GPS, due to its mature technology and unparalleled advantages, has become an important means to achieve precise orbit determination of Leo satellites. This paper focuses on the study of non-differential dynamic orbit determination of Leo satellites based on spaceborne GPS. The key algorithms are realized by software. Taking spaceborne GPS data as an example, the characteristics of Leo satellite orbit are analyzed, and the theoretical and software data processing accuracy are verified. On this basis, some important conclusions are given. The main work of this paper is as follows: (1) the observations and equations of spaceborne GPS are introduced, and the ionospheric combined observation model of spaceborne dual-frequency receiver is given. The source of observation error and the correction method of each error are also analyzed. From the point of view of observation model, this paper lays a good foundation for the next research on orbit determination. (2) the principle of dynamic precise orbit determination of Leo satellite is described in detail from two aspects: dynamic information and satellite motion state information. The mathematical process of orbit solving is given. In order to solve the problem of excessive clock error parameters in the least square batch processing method, The formula derivation process and software implementation method of bell difference reduction theory model are given. The influence of Lagrange interpolation method and Chebyshev interpolation method on the precision of IGS precision ephemeris fitting is studied. The experimental results show that 13 order Lagrangian interpolation or Chebyshev interpolation can meet the precision requirements of precise orbit determination for GPS satellites. The interpolation performance of linear interpolation and cubic spline interpolation for IGS precision clock difference with different time intervals is analyzed. The experimental results show that the interpolation accuracy of linear interpolation method is higher than that of cubic spline interpolation method under the same condition. Moreover, the 30 seconds precise clock difference of IGS can be used to interpolate the precise orbit determination of the Leo satellite, so as to obtain the GPS satellite clock difference of the required time. A software platform for Leo satellite orbit determination based on non-differential dynamics method is developed and tested. The function structure and orbit determination flow of the software are introduced in this paper. The software platform is used to calculate the multi-day orbit of the domestic micro-nano satellite APOD and the internationally famous gravity satellite GRACE, respectively. The precision of orbit determination is verified. The results show that the internal coincidence of the pseudo-range and phase observation values of the 1: APOD satellite is about 2m and 2.5 cm respectively, which is in line with the need of the satellite scientific research project. The accuracy level of orbit overlap arc test is better than that of decimeter GRACE-A satellite pseudo-range and phase observation are 0.9m and 1.2cm respectively, and the accuracy level based on orbit overlap arc test is about 7cm, which is compared with PSO standard orbit. The 3D position accuracy is about 12 cm.
【學(xué)位授予單位】：中國地質(zhì)大學(xué)(北京)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2017
【分類號】：P228.4

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