本文選題：全球?qū)Ш叫l(wèi)星系統(tǒng)　切入點：彈體自旋　出處：《電子科技大學》2014年碩士論文

【摘要】：隨著各國全球?qū)Ш叫l(wèi)星系統(tǒng)(GNSS)的不斷建設(shè)與發(fā)展,衛(wèi)星導航所能提供的性能越發(fā)優(yōu)異。各類制導彈藥開始普遍部署衛(wèi)星導航接收機作為其主要制導手段。導彈在其整個飛行過程中,常常伴隨著彈體的自旋。彈體自旋狀態(tài)對現(xiàn)有GNSS接收機技術(shù)所帶來的挑戰(zhàn),是一個很吸引人的研究領(lǐng)域。本課題系統(tǒng)地研究了彈體自旋狀態(tài)特性對傳統(tǒng)衛(wèi)星導航同步技術(shù)的影響,并針對性地改進了自旋彈載接收機的衛(wèi)星信號跟蹤環(huán)路設(shè)計。論文主要研究內(nèi)容分為五部分:1.研究了衛(wèi)星制導彈藥的彈體自旋狀態(tài)特性以及現(xiàn)有彈載GNSS接收機的設(shè)計模式。分析表明彈體自旋對其衛(wèi)星制導性能造成影響的主要原因為彈載天線相位中心與自旋轉(zhuǎn)軸幾何中心的偏差。2.建立了彈載GNSS接收天線坐標系,系統(tǒng)地研究了彈體自旋狀態(tài)下接收的導航衛(wèi)星信號所受影響。推導了彈體自旋狀態(tài)下接收衛(wèi)星信號的多普勒頻移,載波相位和本地中頻信號變化規(guī)律,建立了隨彈體旋轉(zhuǎn)的GNSS接收機中頻衛(wèi)星信號模型。3.研究了傳統(tǒng)GNSS接收機衛(wèi)星信號同步技術(shù)在彈體自旋場景下的適應性。通過仿真分別給出了傳統(tǒng)接收機信號同步算法對衛(wèi)星信號進行捕獲或跟蹤時,發(fā)生失敗的彈體臨界自旋轉(zhuǎn)速。仿真結(jié)果表明傳統(tǒng)跟蹤環(huán)路無法在彈體高自旋轉(zhuǎn)速下進行信號跟蹤。4.提出了一種新的載波跟蹤環(huán)路——旋轉(zhuǎn)跟蹤環(huán)路,以應對彈體自旋下接收機衛(wèi)星信號跟蹤所面臨的挑戰(zhàn)。完成了該環(huán)路旋轉(zhuǎn)鑒別器,旋轉(zhuǎn)濾波器和旋轉(zhuǎn)NCO(數(shù)控振蕩器)的詳細設(shè)計。該環(huán)路大量復用傳統(tǒng)載波跟蹤環(huán)路結(jié)構(gòu),無需依賴其他傳感器硬件,成功實現(xiàn)了彈體自旋轉(zhuǎn)速的準確測量。利用轉(zhuǎn)速信息輔助,新環(huán)路能夠在傳統(tǒng)環(huán)路無法適應的彈體高自旋轉(zhuǎn)速下成功進行信號跟蹤,覆蓋整個0~20r/s的彈體自旋轉(zhuǎn)速和0~5r/s2的彈體自旋加速度范圍。同時,與傳統(tǒng)環(huán)路相比,旋轉(zhuǎn)跟蹤環(huán)路的載波相位估計誤差更小,具備更優(yōu)異的性能。5.設(shè)計開發(fā)了一套基于Matlab GUI的彈體自旋下的衛(wèi)星導航性能仿真軟件,為后續(xù)自旋彈載接收機衛(wèi)星導航技術(shù)的設(shè)計與性能分析提供可視化軟件工具。
[Abstract]:With the continuous construction and development of GNSS, The performance that satellite navigation can provide is more and more excellent. All kinds of guided ammunition begin to widely deploy satellite navigation receiver as its main guidance means. Often accompanied by the spin of the projectile. The spin state of the projectile poses a challenge to the existing GNSS receiver technology. This paper systematically studies the influence of the spin state characteristics of the projectile on the traditional satellite navigation synchronization technology. The design of the satellite signal tracking loop of the Spin-borne receiver is improved. The main contents of this paper are divided into five parts: 1. The spin state characteristics of the projectile and the existing GNSS receiver are studied. Design pattern. The analysis shows that the main reason for the influence of projectile spin on the guidance performance of the satellite is the deviation between the phase center of the projectile antenna and the geometric center of the spin axis. The coordinate system of the receiving antenna for the missile borne GNSS is established. The influence of satellite signals received in the spin state of the projectile is systematically studied. The Doppler frequency shift, carrier phase and local if signal variation of the received satellite signal in the spin state of the missile body are derived, and the variation of the Doppler frequency shift, the carrier phase and the local intermediate frequency signal are derived. The if satellite signal model of GNSS receiver rotated with the projectile is established. The adaptability of the traditional GNSS receiver satellite signal synchronization technology to the spin scene of the projectile is studied. The signal synchronization of the traditional receiver is given by simulation. Algorithm to capture or track satellite signals, The simulation results show that the traditional tracking loop can not track the signal at the high spin speed of the projectile. 4. A new carrier tracking loop-rotation tracking loop is proposed. The detailed design of the loop rotary discriminator, rotary filter and rotary NCO (numerical controlled oscillator) is completed in order to meet the challenge of satellite signal tracking in the spin-down receiver of the projectile. The loop is widely multiplexed with the traditional carrier tracking loop structure. Without relying on the hardware of other sensors, the accurate measurement of the spin speed of the projectile is successfully realized. With the help of the rotational speed information, the new loop can successfully track the signal at the high spin speed of the projectile which the traditional loop can not adapt to. The spin rotation speed of the whole 0~20r/s and the spin acceleration range of the 0~5r/s2 projectile are covered. At the same time, the carrier phase estimation error of the rotation tracking loop is smaller than that of the traditional loop. 5. A simulation software of satellite navigation performance based on Matlab GUI is designed and developed, which provides a visual software tool for the design and performance analysis of satellite navigation technology of spin-borne receiver.
【學位授予單位】：電子科技大學
【學位級別】：碩士
【學位授予年份】：2014
【分類號】：TN967.1;TJ765

【參考文獻】

相關(guān)期刊論文 前3條

1 申強;王猛;李東光;;旋轉(zhuǎn)條件GPS接收信號頻率和相位變化分析[J];北京理工大學學報;2009年01期

2 陳金平,周建華,趙薇薇;衛(wèi)星導航系統(tǒng)性能要求的概念分析[J];無線電工程;2005年01期

3 王忠,黃順吉;天線相位中心移動對GPS觀測量的影響[J];系統(tǒng)工程與電子技術(shù);1999年03期

相關(guān)博士學位論文 前2條

1 張晶泊;GNSS軟件接收機高動態(tài)載波跟蹤環(huán)路關(guān)鍵技術(shù)研究[D];大連海事大學;2012年

2 左啟耀;高動態(tài)GPS信號跟蹤算法研究[D];中國科學院研究生院（空間科學與應用研究中心）;2008年

相關(guān)碩士學位論文 前1條

1 楊明軒;高動態(tài)GPS信號的快速捕獲與跟蹤方法研究[D];電子科技大學;2008年

，

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