發(fā)布時(shí)間：2018-03-29 03:26

  本文選題：全球?qū)Ш叫l(wèi)星系統(tǒng)　切入點(diǎn)：彈體自旋　出處：《電子科技大學(xué)》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(dǎo)航所能提供的性能越發(fā)優(yōu)異。各類制導(dǎo)彈藥開始普遍部署衛(wèi)星導(dǎo)航接收機(jī)作為其主要制導(dǎo)手段。導(dǎo)彈在其整個(gè)飛行過程中,常常伴隨著彈體的自旋。彈體自旋狀態(tài)對(duì)現(xiàn)有GNSS接收機(jī)技術(shù)所帶來的挑戰(zhàn),是一個(gè)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(duì)傳統(tǒng)衛(wèi)星導(dǎo)航同步技術(shù)的影響,并針對(duì)性地改進(jìn)了自旋彈載接收機(jī)的衛(wèi)星信號(hào)跟蹤環(huán)路設(shè)計(jì)。論文主要研究?jī)?nèi)容分為五部分:1.研究了衛(wèi)星制導(dǎo)彈藥的彈體自旋狀態(tài)特性以及現(xiàn)有彈載GNSS接收機(jī)的設(shè)計(jì)模式。分析表明彈體自旋對(duì)其衛(wèi)星制導(dǎo)性能造成影響的主要原因?yàn)閺椵d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(biāo)系,系統(tǒng)地研究了彈體自旋狀態(tài)下接收的導(dǎo)航衛(wèi)星信號(hào)所受影響。推導(dǎo)了彈體自旋狀態(tài)下接收衛(wèi)星信號(hào)的多普勒頻移,載波相位和本地中頻信號(hào)變化規(guī)律,建立了隨彈體旋轉(zhuǎn)的GNSS接收機(jī)中頻衛(wèi)星信號(hào)模型。3.研究了傳統(tǒng)GNSS接收機(jī)衛(wèi)星信號(hào)同步技術(shù)在彈體自旋場(chǎng)景下的適應(yīng)性。通過仿真分別給出了傳統(tǒng)接收機(jī)信號(hào)同步算法對(duì)衛(wèi)星信號(hào)進(jìn)行捕獲或跟蹤時(shí),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(jìn)行信號(hào)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(yīng)對(duì)彈體自旋下接收機(jī)衛(wèi)星信號(hào)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(xì)設(shè)計(jì)。該環(huán)路大量復(fù)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(shí)現(xiàn)了彈體自旋轉(zhuǎn)速的準(zhǔn)確測(cè)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(yīng)的彈體高自旋轉(zhuǎn)速下成功進(jìn)行信號(hào)跟蹤,覆蓋整個(gè)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(shí),與傳統(tǒng)環(huán)路相比,旋轉(zhuǎn)跟蹤環(huán)路的載波相位估計(jì)誤差更小,具備更優(yōu)異的性能。5.設(shè)計(jì)開發(fā)了一套基于Matlab GUI的彈體自旋下的衛(wèi)星導(dǎo)航性能仿真軟件,為后續(xù)自旋彈載接收機(jī)衛(wèi)星導(dǎo)航技術(shù)的設(shè)計(jì)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(xué)位授予單位】：電子科技大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2014
【分類號(hào)】：TN967.1;TJ765

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