本文選題：等離子體鞘套　切入點(diǎn)：高超聲速流體　出處：《西安電子科技大學(xué)》2016年博士論文　論文類型：學(xué)位論文

【摘要】：自飛行歷史上第一次達(dá)到高超聲速,人類對(duì)高超聲速飛行的研究便開始進(jìn)入到不斷的深入和發(fā)展之中。各種航空飛行器在再入過程中達(dá)到的高超聲速,各航空大國積極投入研究的臨近空間高超聲速飛行器,在帶來先進(jìn)性的同時(shí),也帶來了不可忽視的問題。在高超聲速飛行中產(chǎn)生的高溫效應(yīng),使飛行器繞流流場中的氣體產(chǎn)生了離解、電離等一系列化學(xué)反應(yīng),使流場形成一團(tuán)電離氣體,稱為等離子體鞘套。等離子體鞘套與電磁波之間的相互作用對(duì)飛行器與地面的通訊以及雷達(dá)對(duì)飛行器的探測識(shí)別作用造成了不可小覷的影響。等離子體鞘套的存在甚至造成通訊黑障現(xiàn)象,對(duì)飛行任務(wù)的安全性乃至成功與否帶來隱患。針對(duì)這一現(xiàn)象,研究者們從等離子體鞘套的流場分布特性入手,在等離子體鞘套的形成機(jī)理、組成結(jié)構(gòu)以及數(shù)值仿真方法等方面進(jìn)行了大量的研究工作,并在此基礎(chǔ)上進(jìn)行了大量的電磁波與等離子體鞘套相互作用的研究,以解決等離子體鞘套對(duì)高超聲速飛行帶來的種種問題。本文以有限體積方法為基礎(chǔ),建立基于多塊近似結(jié)構(gòu)網(wǎng)格的計(jì)算網(wǎng)格,通過求解積分形式的流體控制方程-納維斯托克斯方程對(duì)飛行器繞流流場進(jìn)行數(shù)值仿真,采用隱式LU-SGS時(shí)間推進(jìn)方法進(jìn)行三維粘性流動(dòng)計(jì)算,形成計(jì)算程序。程序中包含多種基于迎風(fēng)方式的對(duì)流通量差分格式,以AUSM類格式為主,并通過Reminne問題將幾種通量分裂差分格式進(jìn)行對(duì)比分析。通過計(jì)算程序進(jìn)行包覆飛行器流場的數(shù)值仿真模擬,將采用量熱氣體模型計(jì)算得到的流場與采用熱化學(xué)非平衡計(jì)算得到的流場進(jìn)行對(duì)比,總結(jié)兩模型對(duì)流場仿真結(jié)果的影響。在以上有限體積計(jì)算流體力學(xué)方法的熱完全氣體流場仿真程序的基礎(chǔ)上,引入熱動(dòng)力學(xué)模型和化學(xué)動(dòng)力學(xué)模型,使其能夠進(jìn)行熱非平衡、化學(xué)非平衡流場的數(shù)值仿真計(jì)算。采用雙溫度模型以及不同的七組元化學(xué)反應(yīng)動(dòng)力學(xué)模型,對(duì)熱力學(xué)非平衡以及化學(xué)非平衡繞流流場進(jìn)行求解,形成對(duì)高超聲速熱化學(xué)非平衡流場的計(jì)算程序,計(jì)算采用不同化學(xué)反應(yīng)模型得到的流場分布并進(jìn)行對(duì)比分析。通過現(xiàn)有文獻(xiàn)中提供的計(jì)算和實(shí)驗(yàn)結(jié)果,驗(yàn)證了程序進(jìn)行熱動(dòng)力學(xué)非平衡和化學(xué)非平衡流場計(jì)算的可行性和可靠性。進(jìn)行電磁波與等離子體層相互作用分析,通過電磁波在等離子體層中傳播的傳輸系數(shù)、反射系數(shù)和吸收系數(shù)對(duì)兩者之間的相互作用進(jìn)行描述。討論等離子體層所具有的非均勻特性對(duì)電磁波傳播的影響,以及存在外加磁場時(shí)電磁波在離子體層中的傳播。以解決通訊黑障問題的為應(yīng)用背景,將入射電磁波頻率提高到太赫茲波段,為解決通訊中斷問題提供理論參考。進(jìn)行不同飛行場景下圓球繞流流體的計(jì)算,場景變化包括飛行馬赫數(shù)以及飛行高度,分析比較等離子體鞘套隨飛行高度和飛行馬赫數(shù)的變化規(guī)律以及造成該變化的原因。得出不同飛行場景下的包覆球體等離子體氣體的電子密度分布,計(jì)算相應(yīng)的等離子體頻率和等離子體碰撞頻率。進(jìn)行不同飛行場景下典型鈍錐繞流流場的計(jì)算,飛行場景為RAM試驗(yàn)中飛行軌跡上的幾個(gè)典型高度,得出電子密度以及相應(yīng)的等離子體鞘套和碰撞頻率,提取駐點(diǎn)線上流場特性進(jìn)行介電系數(shù)轉(zhuǎn)化,并計(jì)算駐點(diǎn)線上垂直入射電磁波的單程和雙程傳輸。同時(shí)提取非駐點(diǎn)線上的流場特性參數(shù)進(jìn)行介電系數(shù)轉(zhuǎn)換,并計(jì)算電磁波再非駐點(diǎn)線上的傳輸。將通過不同傳輸路徑得到的結(jié)果進(jìn)行比較分析。
[Abstract]:Since the first time in the history of flight of hypersonic flight on hypersonic research, humans began to enter into the constant deepening and development. All kinds of aircraft in hypersonic reentry to the near space hypersonic aircraft aviation powers researched actively, bring in advanced at the same time, also brought the problem can not be ignored. The effect of high temperature generated in hypersonic flight, the aircraft flow around the gas flow field in the dissociation, a series of chemical reactions such as ionization, causes the flow to form a group of ionized gases, called plasma sheath. Detection and identification of interaction between electromagnetic wave and plasma sheath of aircraft with the ground communication and radar on the aircraft caused underestimated impact. The existence of the plasma sheath communication and even cause blackout phenomenon, the flight safety Full of success and risks. In view of this phenomenon, the researchers start from the plasma sheath flow distribution characteristics, the formation mechanism of plasma sheath, the composition structure and the method of numerical simulation for a lot of research work, and on the basis of a large number of electromagnetic wave and plasma sheath study on the interaction, to solve the problems of plasma sheath on the hypersonic flight brought. Based on the finite volume method, a multi block grid structure based on grid approximation, by solving the governing equation of fluid product form of the Navier Stokes equations for numerical simulation of flow around the aircraft, using the implicit LU-SGS time advance method for 3D viscous flow calculation, the formation of convective flux calculation program. Based on the upwind difference scheme contains a variety of procedures, based on AUS M format, and several flux splitting scheme were analyzed by Reminne. By numerical simulation of flow field of the aircraft coating through computer program, the flow field will flow calculated with thermochemical nonequilibrium obtained by the calorimetric gas model were compared, summed up two models influence flow field simulation results computational fluid dynamics method. Based on the above finite volume thermal perfect gas flow simulation program, the introduction of a thermal kinetic model and kinetic model, which can calculate the thermal non-equilibrium, numerical simulation of chemical non equilibrium flow. The two temperature model and seven different components of chemical reaction kinetics, thermodynamics of non balance and non balance of the chemical solution of flow flow, the formation of the calculation program of hypersonic thermochemical nonequilibrium flow, calculated by different The chemical reaction model of flow field distribution were analyzed. The calculated and experimental results provided by existing literature, to verify the procedures for thermal and chemical non-equilibrium dynamics of the feasibility and reliability of equilibrium flow calculation. The electromagnetic wave and plasma layer interaction analysis, the transmission coefficient of electromagnetic wave propagation in plasma layer., to describe the interaction between reflection coefficient and absorption coefficient of plasma layer is discussed. Effects of inhomogeneous characteristics of electromagnetic wave propagation, and the presence of an applied magnetic field of electromagnetic waves in the plasma layer in the transmission. In order to solve the communication blackout as the application background, will increase the frequency of the incident electromagnetic wave to terahertz in order to solve the problem of communication interrupt band, and provide a theoretical reference. To calculate the flow around the sphere of the different flight scenarios, including flying scene change For Maher number and flight height, cause analysis and comparison of plasma sheath with flight altitude and flight Maher numbers and the changes caused by the changes of the electron density distribution obtained. Different flight scenarios covering sphere plasma gas, calculate the plasma frequency and plasma collision frequency. The calculation flow around the blunt cone under typical different flight scene, flying scenes for several typical high flight trajectory in RAM test on the obtained electron density and the corresponding plasma sheath and collision frequency, extracting line upper field characteristics of dielectric coefficient transformation, and calculate the stagnation line perpendicular to the incident electromagnetic wave of a one-way and two-way transmission. At the same time, extraction of non flow characteristic parameters of stagnation the line of dielectric coefficient conversion, and the calculation of the electromagnetic wave and transmission line. The stagnation point through different transmission path to The results were compared and analyzed.

【學(xué)位授予單位】：西安電子科技大學(xué)
【學(xué)位級(jí)別】：博士
【學(xué)位授予年份】：2016
【分類號(hào)】：V219

【相似文獻(xiàn)】

相關(guān)期刊論文 前8條

1 呼和敖德,胡振華,沈大才,鄔惠欣;球錐細(xì)長體等離子體鞘套分析[J];空氣動(dòng)力學(xué)學(xué)報(bào);1983年01期

2 袁忠才;;等離子體鞘套對(duì)飛行器再入過程信號(hào)傳播特性的影響分析[J];航天器環(huán)境工程;2014年01期

3 于哲峰;劉佳琪;任愛民;張生俊;馬平;石安華;;磁窗天線增強(qiáng)等離子體鞘套透波特性研究[J];宇航學(xué)報(bào);2011年07期

4 董乃涵 ,趙漢章 ,吳是靜;非均勻等離子鞘套中電波傳輸?shù)慕朴?jì)算[J];宇航學(xué)報(bào);1984年01期

5 楊書林 ,肖明;加電場減少等離子鞘套電子密度方案探討[J];國防科技大學(xué)學(xué)報(bào);1983年03期

6 孫欣;劉亞南;劉毅敏;王先義;王健;;基于傳輸矩陣法的等離子體鞘套傳輸特性分析[J];空間科學(xué)學(xué)報(bào);2014年02期

7 曾學(xué)軍;于哲峰;部紹清;柳森;馬平;石安華;梁世昌;;超高速模型及其等離子體鞘套R(shí)CS特性研究(英文)[J];空氣動(dòng)力學(xué)學(xué)報(bào);2010年06期

8 ;[J];;年期

相關(guān)會(huì)議論文 前3條

1 劉江凡;席曉莉;柳楊;;等離子體鞘套中電磁波傳播特性的ADE-FDTD計(jì)算[A];2009年全國天線年會(huì)論文集（下）[C];2009年

2 柳楊;王麗黎;劉江凡;席曉莉;;WKB方法在等離子體鞘套中電波傳播的應(yīng)用研究[A];2009年全國天線年會(huì)論文集（下）[C];2009年

3 劉鐵軍;方振民;;再入通訊中斷與天線超導(dǎo)磁窗[A];1991年全國微波會(huì)議論文集（卷Ⅱ）[C];1991年

相關(guān)博士學(xué)位論文 前3條

1 田媛;等離子體鞘套數(shù)值仿真及其與電磁波相互作用[D];西安電子科技大學(xué);2016年

2 高平;高速飛行器等離子體鞘套下導(dǎo)航信號(hào)及系統(tǒng)特性研究[D];西安電子科技大學(xué);2016年

3 鄭靈;飛行器等離子體鞘套對(duì)電磁波傳輸特性的影響研究[D];電子科技大學(xué);2013年

相關(guān)碩士學(xué)位論文 前8條

1 武曉南;等離子體鞘套中三波相互作用下電磁傳播特性研究[D];哈爾濱工業(yè)大學(xué);2015年

2 陳敏琪;利用PIC模擬等離子體中電磁波傳輸[D];哈爾濱工業(yè)大學(xué);2015年

3 羅琦;等離子體鞘套隱身特性研究[D];南京航空航天大學(xué);2010年

4 朱方;返回艙再入段雷達(dá)散射特性研究[D];蘭州大學(xué);2007年

5 楊永常;ZT-FDTD法分析航天器再入等離子鞘套對(duì)通信信號(hào)的影響[D];南京航空航天大學(xué);2010年

6 張亮;航天器再入段電波特性及加磁場減輕黑障效應(yīng)研究[D];南京理工大學(xué);2013年

7 劉昌臻;“黑障”測控傳輸體制研究[D];南京理工大學(xué);2012年

8 李皎;等離子鞘套下GPS捕獲跟蹤技術(shù)的研究[D];西安電子科技大學(xué);2013年

，

本文編號(hào)：1615802