本文關(guān)鍵詞： 衛(wèi)星導(dǎo)航信號模擬器 GPS 控制軟件　出處：《中北大學(xué)》2015年碩士論文　論文類型：學(xué)位論文

【摘要】：衛(wèi)星導(dǎo)航信號模擬器通過載體運動軌跡的設(shè)定能夠精確模擬出載體在所設(shè)定場景下收到的衛(wèi)星導(dǎo)航信號。衛(wèi)星導(dǎo)航信號模擬器可以對各式接收機的性能進行全面測試，其中包括捕獲、跟蹤和測量精度等。伴隨著導(dǎo)航信號模擬器的飛速發(fā)展，模擬器控制軟件的重要性日益突顯。本文以半實物閉環(huán)仿真系統(tǒng)中的衛(wèi)星導(dǎo)航信號模擬器為應(yīng)用背景，對模擬器控制軟件的總體架構(gòu)、載體運動軌跡數(shù)學(xué)模型及功能開發(fā)等多方面展開了詳細的研究。 首先從模擬器控制軟件的功能設(shè)計、非功能設(shè)計、架構(gòu)設(shè)計及工作流程幾個方面介紹控制軟件系統(tǒng)。通過組模塊框架圖，概述了控制軟件各個模塊的功能。 而后定義了與載體運動相關(guān)的三種常用坐標系如地心地固坐標系、大地坐標系和發(fā)射坐標系，并推導(dǎo)了相互之間的轉(zhuǎn)換矩陣。將載體運動軌跡在簡單場景和復(fù)雜場景下進行了分類，給出了這兩種運動情景下軌跡生成的數(shù)學(xué)模型，并在Matlab中仿真驗證了數(shù)學(xué)模型的正確性。 然后研究了衛(wèi)星星歷的各項參數(shù)，利用擬合和插值兩種算法提出軌道外推衛(wèi)星位置的計算方法，及導(dǎo)航衛(wèi)星的可見性計算方法，，得出了可見星的位置及速度。并且將時鐘、歷書、衛(wèi)星星歷以及些誤差參數(shù)合成導(dǎo)航電文。 最后給出了衛(wèi)星信號模擬過程中的誤差模型，并針對復(fù)雜場景下火箭彈的運動軌跡做了導(dǎo)航信號仿真試驗，通過對比控制軟件生成的軌跡數(shù)據(jù)與接收機接收的實際導(dǎo)航信號，結(jié)果表明衛(wèi)星導(dǎo)航信號模擬器控制軟件滿足了半實物閉環(huán)仿真系統(tǒng)中對衛(wèi)星導(dǎo)航信號的要求。
[Abstract]:The satellite navigation signal simulator can accurately simulate the satellite navigation signal received by the carrier in the set scene by setting the trajectory of the carrier. The satellite navigation signal simulator can comprehensively test the performance of various receivers. With the rapid development of navigation signal simulator, the importance of simulator control software is becoming more and more important. This paper takes the satellite navigation signal simulator in the loop loop simulation system as the application background. The overall structure of the simulator control software, the mathematical model of the carrier trajectory and the function development are studied in detail. Firstly, the control software system is introduced from the aspects of function design, non-functional design, architecture design and workflow of the simulator control software, and the functions of each module of the control software are summarized through the frame diagram of the group module. Then three kinds of commonly used coordinate systems related to the motion of the carrier, such as geocentric coordinate system, geodetic coordinate system and launch coordinate system, are defined. In this paper, the transformation matrix is derived, the carrier trajectory is classified in simple and complex scenes, and the mathematical models of trajectory generation in these two scenarios are given. The correctness of the mathematical model is verified by simulation in Matlab. Then, the parameters of satellite ephemeris are studied. The calculation method of orbit extrapolation satellite position and the visibility calculation method of navigation satellite are proposed by using fitting and interpolation algorithms, and the position and velocity of visible satellite are obtained. Almanac, satellite ephemeris and some error parameters combined with navigation messages. Finally, the error model of satellite signal simulation is given, and the navigation signal simulation test is done for the moving trajectory of rocket in complex scene. The trajectory data generated by the control software and the actual navigation signal received by the receiver are compared with each other. The results show that the control software of satellite navigation signal simulator can meet the requirement of satellite navigation signal in closed loop simulation system.
【學(xué)位授予單位】：中北大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：TN96.1

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