本文選題：高超音速目標(biāo)跟蹤　切入點(diǎn)：高斯和濾波　出處：《江南大學(xué)》2017年碩士論文　論文類型：學(xué)位論文

【摘要】：無源定位跟蹤技術(shù)是現(xiàn)代電子戰(zhàn)的重心之一,其通過截獲地面、海上、空中和太空等各類輻射源發(fā)射的電磁波信號(hào),測(cè)量信號(hào)的特征參數(shù),從而實(shí)現(xiàn)輻射源的定位過程。其中,臨近空間是一個(gè)蓄勢(shì)開發(fā)的重要戰(zhàn)略空間,特別是臨近空間飛行器(即高超音速飛行器)。其具有較高的速度,并能對(duì)全球任一地點(diǎn)出現(xiàn)的事件在短時(shí)間內(nèi)做出反應(yīng);具有突防能力強(qiáng)、生存力高等優(yōu)點(diǎn),因此,高超音速飛行器的出現(xiàn)給對(duì)空預(yù)警、防御提出了新的挑戰(zhàn)。針對(duì)高超音速飛行器的無源定位問題,論文考慮使用兩顆位于地球同步軌道的高軌衛(wèi)星,獲取高超音速目標(biāo)信號(hào)到達(dá)雙星的時(shí)間差(Time Difference of Arrival,TDOA)和頻率差(Frequency Difference of Arrival,FDOA),實(shí)現(xiàn)處于等高程巡航狀態(tài)的高超音速目標(biāo)的無源跟蹤。主要研究工作如下:首先,論文針對(duì)高超音速巡航目標(biāo)在WGS-84橢球下的非線性運(yùn)動(dòng)特征,考慮將三維空間場(chǎng)景轉(zhuǎn)換成二維運(yùn)動(dòng)狀態(tài)模型,并建立其離散時(shí)間運(yùn)動(dòng)狀態(tài)方程。隨后,根據(jù)目標(biāo)運(yùn)動(dòng)方程和量測(cè)方程,推導(dǎo)出高速目標(biāo)定位跟蹤精度的克拉美羅下線(Cramer Rao Lower Bound,CRLB),并通過實(shí)驗(yàn)仿真研究不同因素對(duì)CRLB的影響。計(jì)算機(jī)仿真結(jié)果表明:頻差觀測(cè)噪聲的取值對(duì)目標(biāo)狀態(tài)估計(jì)的CRLB無顯著影響;而時(shí)差觀測(cè)量、運(yùn)動(dòng)速度和運(yùn)動(dòng)方向?qū)RLB影響較大。其次,論文提出基于高斯混合模型替代擴(kuò)展卡爾曼濾波(GMM-Alternative Extennded kalman Filter,GMM-AEKF)的高超音速目標(biāo)跟蹤算法。算法基于二分法的思想,引入時(shí)差觀測(cè)量的均勻GMM表示,以進(jìn)一步提升算法的估計(jì)性能,同時(shí)研究了AEKF實(shí)現(xiàn)頻差狀態(tài)更新對(duì)目標(biāo)軌跡收斂速度的影響。此外,算法基于Kullback-Leibler散度(KL Divergence)原理,給出了有效抑制高斯分量指數(shù)增長(zhǎng)的管理方法,保持算法的計(jì)算復(fù)雜度基本恒定。最后,論文通過蒙特卡洛仿真實(shí)驗(yàn)對(duì)比分析了GMM-AEKF、GMM-EKF和GS-5CKF三種算法的跟蹤性能。仿真實(shí)驗(yàn)表明:論文提出的GMM-AEKF算法,在目標(biāo)位置和速度估計(jì)精度上具有收斂較快的優(yōu)勢(shì),顯示出GMM-AEKF在跟蹤高超音速目標(biāo)問題中的適用性。此外,論文還分析了多種因素對(duì)GMM-AEKF算法跟蹤性能的影響。
[Abstract]:Passive location and tracking technology is one of the center of gravity of modern electronic warfare. It detects the characteristic parameters of the signal by intercepting electromagnetic wave signals from various kinds of emitter sources such as ground, sea, air and space, so as to realize the localization process of emitter. Near-space is an important strategic space for potential development, especially for the near space vehicle (i.e. hypersonic vehicle), which has high speed and can respond to events occurring anywhere in the world in a short time. It has the advantages of strong penetration ability and high survivability. Therefore, the appearance of hypersonic aircraft poses a new challenge to air warning and defense. The paper considers the use of two high-orbit satellites in geosynchronous orbit, The time difference between hypersonic target signals and the frequency difference Difference of ArrivalTDOAA and the frequency difference frequency Difference of Arrival-FDOAA are obtained to achieve passive tracking of hypersonic target in the condition of constant altitude cruising. The main research work is as follows: first of all, In this paper, considering the nonlinear motion characteristics of hypersonic cruise target under WGS-84 ellipsoid, the three-dimensional space scene is transformed into a two-dimensional motion state model, and its discrete-time motion state equation is established. According to the target motion equation and the measurement equation, The Cramer Rao Lower Boundary CRLB of high speed target positioning and tracking accuracy is deduced, and the influence of different factors on CRLB is studied by experimental simulation. The computer simulation results show that the frequency difference observation noise has no significant effect on the CRLB of target state estimation. Secondly, a hypersonic target tracking algorithm based on Gao Si hybrid model instead of extended Kalman filter (GMM-alternative Extennded kalman filter) is proposed. The algorithm is based on the idea of dichotomy. The uniform GMM representation of time-difference observations is introduced to further improve the estimation performance of the algorithm. The influence of frequency difference state updating by AEKF on the convergence rate of target trajectory is also studied. In addition, the algorithm is based on the principle of Kullback-Leibler divergence and KL divergence. This paper presents a management method to effectively suppress the growth of Gao Si component exponent, keeping the computational complexity of the algorithm basically constant. Finally, The tracking performance of GMM-AEKFU GMM-EKF and GMM-EKF is analyzed by Monte Carlo simulation experiment. The simulation results show that the proposed GMM-AEKF algorithm has the advantage of fast convergence in the accuracy of target position and velocity estimation. The applicability of GMM-AEKF in tracking hypersonic target is demonstrated. In addition, the influence of many factors on the tracking performance of GMM-AEKF algorithm is analyzed.
【學(xué)位授予單位】：江南大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2017
【分類號(hào)】：TN95;TN713

【參考文獻(xiàn)】

相關(guān)期刊論文 前9條

1 李曦;楊樂;郭福成;劉洋;張敏;;高軌雙星輻射源跟蹤的高斯和-容積Kalman濾波算法[J];國(guó)防科技大學(xué)學(xué)報(bào);2016年02期

2 林肖輝;王玉林;;高低軌衛(wèi)星聯(lián)合定位研究[J];無線電通信技術(shù);2014年06期

3 ;A Linear-correction Least-squares Approach for Geolocation Using FDOA Measurements Only[J];Chinese Journal of Aeronautics;2012年05期

4 石磊;郭寶龍;劉彥明;趙蕾;;臨近空間高速飛行器綜合信道模型研究[J];宇航學(xué)報(bào);2011年07期

5 李瑩;;基于飛行仿真平臺(tái)的相關(guān)坐標(biāo)變換模型[J];沈陽(yáng)航空工業(yè)學(xué)院學(xué)報(bào);2008年04期

6 李怡勇;李智;沈懷榮;;臨近空間飛行器發(fā)展與應(yīng)用分析[J];裝備指揮技術(shù)學(xué)院學(xué)報(bào);2008年02期

7 楊亞政;李松年;楊嘉陵;;高超音速飛行器及其關(guān)鍵技術(shù)簡(jiǎn)論[J];力學(xué)進(jìn)展;2007年04期

8 李強(qiáng);郭福成;周一宇;;單星對(duì)衛(wèi)星的僅測(cè)角被動(dòng)定軌跟蹤方法研究[J];國(guó)防科技大學(xué)學(xué)報(bào);2007年02期

9 趙高明,鐘鏑;曲線擬合等步長(zhǎng)快速離散化算法[J];計(jì)算機(jī)工程與科學(xué);1991年04期

相關(guān)碩士學(xué)位論文 前2條

1 李曦;雙站無源目標(biāo)跟蹤算法研究[D];江南大學(xué);2016年

2 江利中;基于編隊(duì)飛行小衛(wèi)星群的TDOA和FDOA定位與跟蹤算法研究[D];西安電子科技大學(xué);2011年

，

本文編號(hào)：1570379