电磁波在空间等离子体中传输与散射若干问题研究
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摘要
近年来随着航天科技的飞速发展，人类已将活动领域延伸到了星际空间，空间中的等离子体环境是人类开展空间探索活动的基本环境条件。空间等离子体环境包括电离层等离子体环境、星际和外空间等离子体环境等，其对航天通信系统的影响不容忽视。在探索未知空间的活动中，人们对通信系统提出了更高的要求，而电波传播环境是通信系统中不可忽略的重要组成部分。因此空间等离子体中的电波传播问题也越来越受到学者的关注。本文以等离子体中的电波传播和散射理论为出发点，主要围绕尘埃等离子体、电离层空间碎片、电离层加热及等离子鞘套等四个方面的电波传播与散射问题开展相关研究。本文主要工作如下：
1.首先介绍有关电离层中等离子体环境的基本知识，分析空间等离子体对电磁波传输、散射特性产生影响的主要因素，最后根据空间等离子体中的电子密度、离子密度等经验模型，从等离子体中的电波传播理论出发，讨论了等离子体中电波传播的WKB、传输矩阵、FDTD、射线追踪等数值计算方法。
2.电磁波在尘埃等离子体中的传播问题是一个越来越受到广泛关注的研究课题。本文首先从空间尘埃等离子体中尘埃颗粒的充放电模型出发，将充电尘埃粒子的电磁散射考虑为中心尘埃的散射及粒子外围德拜云的散射，分析充电尘埃系统的Mie-Debye散射，研究充电平衡条件下尘埃等离子体中的带电尘埃系统电磁散射特性。最后，根据尘埃系统的充放电方程和静电平衡条件计算尘埃粒子吸附电荷数随尘埃半径的变化关系。通过相关电离层模型模拟空间环境，采用输运理论计算得到高层大气环境中尘埃等离子体层对电磁波的反射、衰减特性。计算结果表明，当电磁波波频率一定时，尘埃对电磁波衰减与电子密度、尘埃粒子密度以及尘埃粒子半径成正比。
3.空间碎片长期运行在空间轨道上，并随着人类航天活动的不断深入而日益增多，严重地威胁着航天器的安全。本文首先根据空间碎片增减的因素，研究空间碎片的分布模型。在电离层准抛物模型的基础上，计算扰动电离层的电子密度分布图，研究电离层不均匀体的散射特性。结合坐标的尺度变换理论分析了椭球碎片的电磁散射特性。最后，采用Born近似取不均匀体的内场为入射波，推导了扰动区域中不均匀体和空间危险碎片的双站雷达散射截面计算公式，计算结果表明，电离层不均匀体将雷达探测波的大部分能量散射到前向及其附近方向，对碎片的地基雷达探测造成极大的影响，且当电磁波频率增大时，不均匀体对碎片探测的影响将减小。
4.电离层是一个巨大的天然等离子体物理实验室，是无线电波传播的承载体和通道，本文分析大功率无线电波注入电离层引起电离层的局部改变。在给定的加热条件下，低电离层可以根据电子的有效复合系数研究电子密度扰动模型。而对于电离层高层区域，考虑到电子和离子漂移的影响，加热机制与低层区域有很大不同。因此，需要通过电子、离子的动力学方程、连续性方程，分别建立低电离层和高电离层的电子密度扰动模型。分析表明地面发射大功率的高频电磁波注入电离层可以引起电离层中电子密度发生明显变化，且电磁波对电离层的加热作用具有饱和效应。最后，采用射线追踪方法，仿真分析了电磁波在加热电离层中不同路径传输的衰减。并基于以上加热电离层传播模型，建立了加热电离层多径信道模型，对仿真的信道模型进行了分析，表明加热电离层信道是一种时变色散衰落信道。
5.飞行器在空间高速飞行时周围形成等离子体包覆流场，对无线通信系统造成不可忽视的影响。本文建立钝头锥体的飞行器模型，根据飞行器外围流场特性，采用轴对称热化学非平衡流动的无量纲化控制方程组模拟高速飞行器表面绕流流场。根据流场的旋转对称性质，求解飞行器外围流场的温度分布、各组分密度分布以及不同马赫数下的电子密度分布。
6.根据飞行器流场仿真得出的电子密度分布参数，采用WKB等方法计算了等离子体鞘套中电磁波的衰减，通过分析鞘套的等离子体特性，计算了鞘套中电磁波传播产生的相移。并将钝头锥体飞行器模型进行三角面元剖分，采用PO方法计算了不同飞行速度下钝头锥体飞行器的RCS。在分析飞行器表面等离子体性质及其对通信信号的衰减等因素的基础上，构建了空间通信“黑障”预报模型。根据飞行器再入轨迹，对发生的“黑障”进行了预测。并针对黑障问题，建立了一种磁窗模型，仿真结果表明，该磁窗可以有效降低等离子体鞘套中的电子密度，减低“黑障”风险。
With the rapid development of space science and technology in recent years, people hasextended their exploration area to the interstellar space. While the space plasma environmentis the basic condition for people’s space exploration activity. The environment of spaceplasma includes ionospheric plasma environment, the star and the outer space plasmaenvironment, etc. At the same time, for the exploration activity of the unknown space isconcerned, people put forward a higher requirement on radio communication system, whileradio wave propagation environment is the significant component in communication systemwhich can not be neglected. So radio wave propagation in space plasma has attracted moreand more attention of the scholars. Based on the fundamental theory of the radio wavepropagation and scattering in plasma, emphasis is put on investigating on the related problemof dust plasma, space debris in ionosphere, ionospheric heating and plasma sheath. The mainworks are as follows:
Firstly, the basic knowledge of plasma environment in ionosphere is introduced. Then themain factors of space plasma which have influence on the electromagnetic wave transmissionand scattering is analyzed. According to the empirical models of electron density and iondensity in plasma, the numerical methods of radio wave propagation in plasma which includeWKB of radio wave propagation, transmission matrix, FDTD and ray tracing is discussed.
Secondly, the transmission of electromagnetic wave in dust plasma becomes a researchsubject which draws more and more attentions. The charge and discharge model of the dustparticles in space dust plasma is discussed. The electromagnetic scattering of the chargingdust is taken as the scattering from the central dust particle and the scattering from debyecloud out of the particle, the Mie-Debye scattering of the dust plasma is analyzed, theelectromagnetic scattering characteristics of the charged dust in dust plasma with equilibriumstate is examined. Finally, according to the charging equation and electrostatic equilibriumequation of dust particle, the relationship between the charge number of dust particle and dustparticle radius is calculated. On the basis of the space environment simulation, thecharacteristics of electromagnetic wave reflection and attenuation of dust plasma layer in theupper atmospheric environment is obtained with transport theory. It is found that theattenuation of electromagnetic wave by the dust for a fixing frequency of EM wave isproportional to electron density, dust particle density and dust particle radius.
Thirdly, as we have already known, space debris keeps running in orbital space, and itwill increase with the development of human space activity, which is a heavy threaten to the safety of spacecraft operation. According to the increase and decrease factors of the spacedebris, the distribution model of space debris is studied. Then, on the basis of ionospherequasi parabolic model, the ionosphere electron density distribution is analyzed to get theelectron density distribution contour map of the interferential ionosphere, and scatteringcharacteristics of the ionospheric irregularity is investigated. The electromagnetic scatteringanalytic solution of ellipsoidal debris has been deduced by the scale transformation theory.Then, by using Born approximation and by taking the ionospheric irregular infield as theincident wave, the radar cross section of the irregularity and space debris is derived. Thenumerical results show that most of the energy of radar wave is scattered by the ionosphericirregularity to the forward direction and near around, which has a significant impact on theground based radar detection of the debris. When the frequency of electromagnetic waveincreases, the influence of irregularity on debris detection will reduce.
Fourthly, ionosphere is a huge natural plasma physics laboratory. It is the carrier andchannel of the radio wave propagation. Based on the interaction mechanism of high-powerradio wave with the ionospheric plasma, the local change of the ionosphere is analyzed whenthe high-power radio wave is injected into the ionosphere. Under the given heating condition,electron density perturbation model is analyzed by electron's effective recombinationcoefficients for the low ionosphere. However, for the high ionosphere, the heating mechanismis different from that in the low ionosphere with considering the drift of the electrons and ions.According to the electron and ion’s kinetic equation and continuity equation, the low and highionosphere electron density perturbation model are given, respectively. It is shown that theinjection of electromagnetic wave with high-power and high-frequency transmitting from theground base into ionosphere can cause a significant change on the electron density in theionosphere. The pump wave has a saturation effects on ionospheric heating. Finally, theattenuation of electromagnetic wave propagation in the heating ionosphere are calculated byray tracing method. Based on the above transmission model, the multi-path model ofionospheric heating is established, which indicates that ionospheric heating channel is atime-varying channel with disperse fading.
Fifthly, when the aircraft flying in the space with high speed, the plasma cladding flowfield will be formed, which will have affects on the radio communication system that can notbe neglected. The sphere cone aircraft model is built in this paper. According to thecharacteristics of aircraft peripheral flow field, high speed aircraft circumferential flow field issimulated by the dimensionless control equations of axisymmetric, thermal chemical andnon-equilibrium flow. Considering the rotational symmetry characteristics of flow field, the temperature distribution of the aircraft peripheral flow field, the density distribution of eachgroup and the electron density distribution in different mach number are calculated.
Finally, according to electron density distribution parameters simulated by the aircraftflow field, WKB and other methods are utilized to calculate the attenuation ofelectromagnetic wave in plasma sheath. By analyzing the plasma characteristics of the sheath,the phase shift of electromagnetic wave propagation in sheath is computed. Then, the triangleelement method is used to meshing sphere cone aircraft model. Based on the PO method, theRCS of sphere cone aircraft in different flight velocity is calculated. On the basis of plasmasheath characteristics and it’s attenuation of communication signal,“Blackout” forecastingmodel for the space communication is constructed. According to the reentry trajectory of theaircraft,“Blackout”is forecasted. Aiming at this issue, the electromagnetic window model isestablished. It is shown that the electron density in plasma sheath is considerably reduced bythis electromagnetic window and this method could reduce the risk of “Blackout”.
1.首先介绍有关电离层中等离子体环境的基本知识，分析空间等离子体对电磁波传输、散射特性产生影响的主要因素，最后根据空间等离子体中的电子密度、离子密度等经验模型，从等离子体中的电波传播理论出发，讨论了等离子体中电波传播的WKB、传输矩阵、FDTD、射线追踪等数值计算方法。
2.电磁波在尘埃等离子体中的传播问题是一个越来越受到广泛关注的研究课题。本文首先从空间尘埃等离子体中尘埃颗粒的充放电模型出发，将充电尘埃粒子的电磁散射考虑为中心尘埃的散射及粒子外围德拜云的散射，分析充电尘埃系统的Mie-Debye散射，研究充电平衡条件下尘埃等离子体中的带电尘埃系统电磁散射特性。最后，根据尘埃系统的充放电方程和静电平衡条件计算尘埃粒子吸附电荷数随尘埃半径的变化关系。通过相关电离层模型模拟空间环境，采用输运理论计算得到高层大气环境中尘埃等离子体层对电磁波的反射、衰减特性。计算结果表明，当电磁波波频率一定时，尘埃对电磁波衰减与电子密度、尘埃粒子密度以及尘埃粒子半径成正比。
3.空间碎片长期运行在空间轨道上，并随着人类航天活动的不断深入而日益增多，严重地威胁着航天器的安全。本文首先根据空间碎片增减的因素，研究空间碎片的分布模型。在电离层准抛物模型的基础上，计算扰动电离层的电子密度分布图，研究电离层不均匀体的散射特性。结合坐标的尺度变换理论分析了椭球碎片的电磁散射特性。最后，采用Born近似取不均匀体的内场为入射波，推导了扰动区域中不均匀体和空间危险碎片的双站雷达散射截面计算公式，计算结果表明，电离层不均匀体将雷达探测波的大部分能量散射到前向及其附近方向，对碎片的地基雷达探测造成极大的影响，且当电磁波频率增大时，不均匀体对碎片探测的影响将减小。
4.电离层是一个巨大的天然等离子体物理实验室，是无线电波传播的承载体和通道，本文分析大功率无线电波注入电离层引起电离层的局部改变。在给定的加热条件下，低电离层可以根据电子的有效复合系数研究电子密度扰动模型。而对于电离层高层区域，考虑到电子和离子漂移的影响，加热机制与低层区域有很大不同。因此，需要通过电子、离子的动力学方程、连续性方程，分别建立低电离层和高电离层的电子密度扰动模型。分析表明地面发射大功率的高频电磁波注入电离层可以引起电离层中电子密度发生明显变化，且电磁波对电离层的加热作用具有饱和效应。最后，采用射线追踪方法，仿真分析了电磁波在加热电离层中不同路径传输的衰减。并基于以上加热电离层传播模型，建立了加热电离层多径信道模型，对仿真的信道模型进行了分析，表明加热电离层信道是一种时变色散衰落信道。
5.飞行器在空间高速飞行时周围形成等离子体包覆流场，对无线通信系统造成不可忽视的影响。本文建立钝头锥体的飞行器模型，根据飞行器外围流场特性，采用轴对称热化学非平衡流动的无量纲化控制方程组模拟高速飞行器表面绕流流场。根据流场的旋转对称性质，求解飞行器外围流场的温度分布、各组分密度分布以及不同马赫数下的电子密度分布。
6.根据飞行器流场仿真得出的电子密度分布参数，采用WKB等方法计算了等离子体鞘套中电磁波的衰减，通过分析鞘套的等离子体特性，计算了鞘套中电磁波传播产生的相移。并将钝头锥体飞行器模型进行三角面元剖分，采用PO方法计算了不同飞行速度下钝头锥体飞行器的RCS。在分析飞行器表面等离子体性质及其对通信信号的衰减等因素的基础上，构建了空间通信“黑障”预报模型。根据飞行器再入轨迹，对发生的“黑障”进行了预测。并针对黑障问题，建立了一种磁窗模型，仿真结果表明，该磁窗可以有效降低等离子体鞘套中的电子密度，减低“黑障”风险。
With the rapid development of space science and technology in recent years, people hasextended their exploration area to the interstellar space. While the space plasma environmentis the basic condition for people’s space exploration activity. The environment of spaceplasma includes ionospheric plasma environment, the star and the outer space plasmaenvironment, etc. At the same time, for the exploration activity of the unknown space isconcerned, people put forward a higher requirement on radio communication system, whileradio wave propagation environment is the significant component in communication systemwhich can not be neglected. So radio wave propagation in space plasma has attracted moreand more attention of the scholars. Based on the fundamental theory of the radio wavepropagation and scattering in plasma, emphasis is put on investigating on the related problemof dust plasma, space debris in ionosphere, ionospheric heating and plasma sheath. The mainworks are as follows:
Firstly, the basic knowledge of plasma environment in ionosphere is introduced. Then themain factors of space plasma which have influence on the electromagnetic wave transmissionand scattering is analyzed. According to the empirical models of electron density and iondensity in plasma, the numerical methods of radio wave propagation in plasma which includeWKB of radio wave propagation, transmission matrix, FDTD and ray tracing is discussed.
Secondly, the transmission of electromagnetic wave in dust plasma becomes a researchsubject which draws more and more attentions. The charge and discharge model of the dustparticles in space dust plasma is discussed. The electromagnetic scattering of the chargingdust is taken as the scattering from the central dust particle and the scattering from debyecloud out of the particle, the Mie-Debye scattering of the dust plasma is analyzed, theelectromagnetic scattering characteristics of the charged dust in dust plasma with equilibriumstate is examined. Finally, according to the charging equation and electrostatic equilibriumequation of dust particle, the relationship between the charge number of dust particle and dustparticle radius is calculated. On the basis of the space environment simulation, thecharacteristics of electromagnetic wave reflection and attenuation of dust plasma layer in theupper atmospheric environment is obtained with transport theory. It is found that theattenuation of electromagnetic wave by the dust for a fixing frequency of EM wave isproportional to electron density, dust particle density and dust particle radius.
Thirdly, as we have already known, space debris keeps running in orbital space, and itwill increase with the development of human space activity, which is a heavy threaten to the safety of spacecraft operation. According to the increase and decrease factors of the spacedebris, the distribution model of space debris is studied. Then, on the basis of ionospherequasi parabolic model, the ionosphere electron density distribution is analyzed to get theelectron density distribution contour map of the interferential ionosphere, and scatteringcharacteristics of the ionospheric irregularity is investigated. The electromagnetic scatteringanalytic solution of ellipsoidal debris has been deduced by the scale transformation theory.Then, by using Born approximation and by taking the ionospheric irregular infield as theincident wave, the radar cross section of the irregularity and space debris is derived. Thenumerical results show that most of the energy of radar wave is scattered by the ionosphericirregularity to the forward direction and near around, which has a significant impact on theground based radar detection of the debris. When the frequency of electromagnetic waveincreases, the influence of irregularity on debris detection will reduce.
Fourthly, ionosphere is a huge natural plasma physics laboratory. It is the carrier andchannel of the radio wave propagation. Based on the interaction mechanism of high-powerradio wave with the ionospheric plasma, the local change of the ionosphere is analyzed whenthe high-power radio wave is injected into the ionosphere. Under the given heating condition,electron density perturbation model is analyzed by electron's effective recombinationcoefficients for the low ionosphere. However, for the high ionosphere, the heating mechanismis different from that in the low ionosphere with considering the drift of the electrons and ions.According to the electron and ion’s kinetic equation and continuity equation, the low and highionosphere electron density perturbation model are given, respectively. It is shown that theinjection of electromagnetic wave with high-power and high-frequency transmitting from theground base into ionosphere can cause a significant change on the electron density in theionosphere. The pump wave has a saturation effects on ionospheric heating. Finally, theattenuation of electromagnetic wave propagation in the heating ionosphere are calculated byray tracing method. Based on the above transmission model, the multi-path model ofionospheric heating is established, which indicates that ionospheric heating channel is atime-varying channel with disperse fading.
Fifthly, when the aircraft flying in the space with high speed, the plasma cladding flowfield will be formed, which will have affects on the radio communication system that can notbe neglected. The sphere cone aircraft model is built in this paper. According to thecharacteristics of aircraft peripheral flow field, high speed aircraft circumferential flow field issimulated by the dimensionless control equations of axisymmetric, thermal chemical andnon-equilibrium flow. Considering the rotational symmetry characteristics of flow field, the temperature distribution of the aircraft peripheral flow field, the density distribution of eachgroup and the electron density distribution in different mach number are calculated.
Finally, according to electron density distribution parameters simulated by the aircraftflow field, WKB and other methods are utilized to calculate the attenuation ofelectromagnetic wave in plasma sheath. By analyzing the plasma characteristics of the sheath,the phase shift of electromagnetic wave propagation in sheath is computed. Then, the triangleelement method is used to meshing sphere cone aircraft model. Based on the PO method, theRCS of sphere cone aircraft in different flight velocity is calculated. On the basis of plasmasheath characteristics and it’s attenuation of communication signal,“Blackout” forecastingmodel for the space communication is constructed. According to the reentry trajectory of theaircraft,“Blackout”is forecasted. Aiming at this issue, the electromagnetic window model isestablished. It is shown that the electron density in plasma sheath is considerably reduced bythis electromagnetic window and this method could reduce the risk of “Blackout”.
引文
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