飞行器再入段电磁波传播与天线特性研究
摘要
飞行器以极高速度再入大气层的过程中,会在一段时间内出现电波损耗急剧增大的现象。飞行器与大气层相互作用时产生的等离子体,是引起电波损耗剧增,甚至导致通信中断的主要原因。本文对飞行器再入段的电磁波传播与天线特性进行了系统的研究,通过理论分析、数值仿真和测量实验等方法分析了等离子体产生的电波损耗,并提出了降低电波损耗的方法。
飞行器再入时产生的等离子体是一种具有高电子密度与高碰撞频率的导电流体,具有色散介质的性质。等离子体导致的电波损耗主要包括:等离子体对电磁波的吸收与反射衰减,以及等离子体中天线阻抗失配造成的增益下降。在分析等离子体对电磁波与天线的作用时,为描述等离子体的宏观性质,采用Drude散射模型来模拟。为研究等离子体对电磁波的衰减作用,对电磁波垂直入射均匀等离子体、斜入射均匀等离子体以及垂直入射非均匀等离子体进行了理论分析,对电磁波的功率吸收系数与功率反射系数进行了数值模拟。再入等离子体覆盖在飞行器天线上,会改变原已调谐好的天线参数,为研究覆盖等离子体的天线性能,对等离子体中对称振子天线的辐射与阻抗特性进行了理论分析,对输入阻抗、反射损耗与方向图进行了仿真研究。为适应实际的飞行器情况,建立了覆盖等离子体的喇叭天线模型,分析了天线的反射损耗、电场分布与方向图。
为验证理论与仿真分析,本文提出了一种测量等离子体中电波损耗的地面实验方案,该方案采用多根低压气体放电等离子体管组成了等离子体平板,模拟了再入段等离子体分布特性,确定了平均等离子体密度,将等离子体平板覆盖在发射天线上,利用收发对置的喇叭天线测量了等离子体造成的电磁波衰减与天线特性参数的改变。
降低等离子体产生的电波损耗对保障高速飞行器的通信十分重要。基于等离子体的流体性质,本文提出了一种改进再入段等离子体分布特性的结构,建立了相应的等离子体分布模型。该模型保持总体电子数不变,在电磁波极化方向上呈高低电子密度周期排列。为应用微波网络理论对所提出的降低电波损耗方法进行验证,建立了收发对置喇叭天线仿真模型,其中发射天线覆盖有等离子体层。在对等离子体模型参数进行优化设计后,对各频段天线的阻抗特性与辐射特性进行了仿真分析。采用这种等离子体模型后,电磁波的吸收与反射衰减有明显减少,天线的反射损耗减小而增益增大。地面实验测量结果表明所提出的方法可显著降低等离子体产生的电波损耗,改善天线的阻抗匹配特性。
对于一些具有等离子体喷焰的高速飞行器,提出了一种利用高电子密度射流构成等离子体天线的方法。利用高电子密度等离子体的类似金属性质,基于金属天线理论,对等离子体单极天线的阻抗特性与辐射特性进行了理论分析,通过适当的馈电方式与结构设计,构成了飞行器上使用的等离子体天线。为分析等离子体天线的基本性能,对同轴线馈电的柱形与锥形等离子体天线进行了仿真研究。结合再入环境中的情况,研究了等离子体层覆盖地板的柱形等离子体天线。为适应飞行器上应用,建立了环耦合馈电的柱形等离子体天线模型,提出了在馈电环与等离子体之间加入介质环套的方法,以防止高温对馈电环金属的烧蚀,并对等离子体包围的环耦合馈电等离子体天线进行了研究。本文制作并测量了环耦合馈电的等离子天线,结果表明利用等离子体可实现天线的辐射性能。由于现阶段应用的等离子体天线带宽较窄,为适应宽带测控系统的需要,基于圆盘单极子理论,提出了圆盘与椭圆盘形等离子体单极天线。对其阻抗与辐射特性进行了仿真分析,结果表明新型的等离子体天线有效地拓展了带宽。
本文详细分析了飞行器在再入段中高速飞行时的电磁波传播与天线特性,提出了降低电波损耗的方法,进行了理论分析、仿真研究与地面测量,为飞行试验提供了理论参考与借鉴。
When a high speed spacecraft flies in reentry aerosphere stage, a phenomenon of electromagnetic attenuation increasement rapidly is able to occur. The reentry plasma is generated by the interaction between spacecraft and aerosphere. The plasma is a main cause of electromagnetic attenuation rapid augment so much as the communication blackout occurment. In this paper, the electromagnetic wave attenuation caused by plasma and the mitigation technique are studied through different method such as theoretical analysis, simulated calculation, and experimental measurement.
Plasma in reentry aerosphere stage is a kind of electric liquid with high electron density, collision frequency and dispersive characteristic. The electromagnetic attenuation caused by plasma is consisted with the electromagnetic wave absorption and reflection of plasma, and the gain reduced by mismatch of antenna impedance. To describe the macrography characteristic of plasma, the Druce dispersion model is able to employ to analyze the interaction of electromagnetic wave and plasma as much as antenna and plasma. To research the electromagnetic wave attenuation of plasma, the theory of vertical incidence and oblique incidence in homogeneous plasma, and vertical incidence in nonhomogeneous is analyzed, and power absorption coefficient and power return loss of electromagnetic wave is simulated. The reentry plasma can change the initial antenna characteristic. To research the characteristic of antenna covered with plasma, a dipole antenna in plasma is researched. The theory of impedance and radiation characteristic is analyzed, and the input impedance, return loss and radiation pattern of the antenna is simulated. A horn antennacovered with plasma is proposed to analyze the antenna on spacecraft, and the return loss, electric field intensity and radiation pattern of the antenna is simulated.
To verify the results of theory and simulation analysis, a experiment scheme is proposed to measure the electromagnetic wave attenuation of plasma. The experiment scheme includes a plasma flat slab consist of several plasma tubes by low voltage gas discharge. The plasma flat slab can simulate the reentry plasma characteristic of the spacecraft. After determine the average electron density of the plasma flat slab, the plasma flat slab is put on the transmitting antenna,and the attenuation and the antenna characteristic of electromagnetic wave in plasma are measured by transmitting and receiving horn antenna.
It is important for the communication protection of high speed spacecraft to mitigate the electromagnetic wave attenuation caused by the plasma. Based on the liquid property of plasma, a configurationis proposed to change the characteristic of the reentry plasma, and the realignment model of plasma electron density is analyzed. When the total number of electron is fixed, the electron density of plasma is arranged normal to the polarization. To analyze the mitigation of electromagnetic wave attenuation based on microwave network theory, ahe model consisted with transmitting antenna and receiving antenna is proposed. The impedance and radiation characteristic is researched. The measurement results show the electromagnetic wave attenuation is mitigated, and the gain is increased. In this model, the transmitting antenna is covered with plasma. The parameter of the plasma electron density model is optimized, and the impedance characteristic and radiation characteristic in every frequency band is simulated and analyzed. The results show the proposed plasma model can reduce the absorption and reflection of electromagnetic wave, reduce the return loss of antenna, and increase the gain of antenna. The results in experiment show the proposed method can mitigate the electromagnetic wave attenuation, and improve the antenna characteristic.
For some high speed spacecrafts with high electron density plasma jet, a method is proposed to form a plasma antenna by plasma jet with high electron density. Based on the similar metal characteristic of plasma and metal antenna theory, the impedance characteristic and radiation characteristic of plasma monopole antenna is analyzed. The plasma antenna used on the spacecraft can be formed with appropriate feeding and configuration design. To analyze the antenna characteristic, the columnar plasma antenna and conical plasma antenna fed by coaxial line are simulated and analyzed. To adapt the reentry environment, a columnar plasma antenna with ground covered by plasma is researched. To adapt the application of reentry spacecraft, a columnar plasma antenna model fed by metal ring is proposed, and a dielectric ring is used between the feeding metal ring and columnar plasma to avoid the high temperature ablation. The columnar plasma antenna fed by metal ring surround by plasma is researched. A columnar plasma antenna fed by metal ring is designed and measured. The experiment results show the plasma can radiate the electromagnetic wave.To adapt the ues of wideband communication system, some wideband plasma antennas are proposed, such as circular plasma monopole antenna and elliptic plasma monopole antenna based on circular monopole theory. The impedance characteristic and radiation characteristic of these antennae are simulated and analyzed. The results show that the band width of the novel plasma antenna is extended markedly.
The electromagnetic wave attenuation of high speed reentry in aerosphere stage is analyzed in detail. Based on the liquid property of plasma and the similar metal characteristic of plasma, two methods of electromagnetic wave attenuation mitigation are proposed. The model of electromagnetic wave attenuation mitigation is designed and analyzed by theory and simulation, and the experiment is proposed and researched. The simulation and experiment results are the consultation for flight experiments.
飞行器再入时产生的等离子体是一种具有高电子密度与高碰撞频率的导电流体,具有色散介质的性质。等离子体导致的电波损耗主要包括:等离子体对电磁波的吸收与反射衰减,以及等离子体中天线阻抗失配造成的增益下降。在分析等离子体对电磁波与天线的作用时,为描述等离子体的宏观性质,采用Drude散射模型来模拟。为研究等离子体对电磁波的衰减作用,对电磁波垂直入射均匀等离子体、斜入射均匀等离子体以及垂直入射非均匀等离子体进行了理论分析,对电磁波的功率吸收系数与功率反射系数进行了数值模拟。再入等离子体覆盖在飞行器天线上,会改变原已调谐好的天线参数,为研究覆盖等离子体的天线性能,对等离子体中对称振子天线的辐射与阻抗特性进行了理论分析,对输入阻抗、反射损耗与方向图进行了仿真研究。为适应实际的飞行器情况,建立了覆盖等离子体的喇叭天线模型,分析了天线的反射损耗、电场分布与方向图。
为验证理论与仿真分析,本文提出了一种测量等离子体中电波损耗的地面实验方案,该方案采用多根低压气体放电等离子体管组成了等离子体平板,模拟了再入段等离子体分布特性,确定了平均等离子体密度,将等离子体平板覆盖在发射天线上,利用收发对置的喇叭天线测量了等离子体造成的电磁波衰减与天线特性参数的改变。
降低等离子体产生的电波损耗对保障高速飞行器的通信十分重要。基于等离子体的流体性质,本文提出了一种改进再入段等离子体分布特性的结构,建立了相应的等离子体分布模型。该模型保持总体电子数不变,在电磁波极化方向上呈高低电子密度周期排列。为应用微波网络理论对所提出的降低电波损耗方法进行验证,建立了收发对置喇叭天线仿真模型,其中发射天线覆盖有等离子体层。在对等离子体模型参数进行优化设计后,对各频段天线的阻抗特性与辐射特性进行了仿真分析。采用这种等离子体模型后,电磁波的吸收与反射衰减有明显减少,天线的反射损耗减小而增益增大。地面实验测量结果表明所提出的方法可显著降低等离子体产生的电波损耗,改善天线的阻抗匹配特性。
对于一些具有等离子体喷焰的高速飞行器,提出了一种利用高电子密度射流构成等离子体天线的方法。利用高电子密度等离子体的类似金属性质,基于金属天线理论,对等离子体单极天线的阻抗特性与辐射特性进行了理论分析,通过适当的馈电方式与结构设计,构成了飞行器上使用的等离子体天线。为分析等离子体天线的基本性能,对同轴线馈电的柱形与锥形等离子体天线进行了仿真研究。结合再入环境中的情况,研究了等离子体层覆盖地板的柱形等离子体天线。为适应飞行器上应用,建立了环耦合馈电的柱形等离子体天线模型,提出了在馈电环与等离子体之间加入介质环套的方法,以防止高温对馈电环金属的烧蚀,并对等离子体包围的环耦合馈电等离子体天线进行了研究。本文制作并测量了环耦合馈电的等离子天线,结果表明利用等离子体可实现天线的辐射性能。由于现阶段应用的等离子体天线带宽较窄,为适应宽带测控系统的需要,基于圆盘单极子理论,提出了圆盘与椭圆盘形等离子体单极天线。对其阻抗与辐射特性进行了仿真分析,结果表明新型的等离子体天线有效地拓展了带宽。
本文详细分析了飞行器在再入段中高速飞行时的电磁波传播与天线特性,提出了降低电波损耗的方法,进行了理论分析、仿真研究与地面测量,为飞行试验提供了理论参考与借鉴。
When a high speed spacecraft flies in reentry aerosphere stage, a phenomenon of electromagnetic attenuation increasement rapidly is able to occur. The reentry plasma is generated by the interaction between spacecraft and aerosphere. The plasma is a main cause of electromagnetic attenuation rapid augment so much as the communication blackout occurment. In this paper, the electromagnetic wave attenuation caused by plasma and the mitigation technique are studied through different method such as theoretical analysis, simulated calculation, and experimental measurement.
Plasma in reentry aerosphere stage is a kind of electric liquid with high electron density, collision frequency and dispersive characteristic. The electromagnetic attenuation caused by plasma is consisted with the electromagnetic wave absorption and reflection of plasma, and the gain reduced by mismatch of antenna impedance. To describe the macrography characteristic of plasma, the Druce dispersion model is able to employ to analyze the interaction of electromagnetic wave and plasma as much as antenna and plasma. To research the electromagnetic wave attenuation of plasma, the theory of vertical incidence and oblique incidence in homogeneous plasma, and vertical incidence in nonhomogeneous is analyzed, and power absorption coefficient and power return loss of electromagnetic wave is simulated. The reentry plasma can change the initial antenna characteristic. To research the characteristic of antenna covered with plasma, a dipole antenna in plasma is researched. The theory of impedance and radiation characteristic is analyzed, and the input impedance, return loss and radiation pattern of the antenna is simulated. A horn antennacovered with plasma is proposed to analyze the antenna on spacecraft, and the return loss, electric field intensity and radiation pattern of the antenna is simulated.
To verify the results of theory and simulation analysis, a experiment scheme is proposed to measure the electromagnetic wave attenuation of plasma. The experiment scheme includes a plasma flat slab consist of several plasma tubes by low voltage gas discharge. The plasma flat slab can simulate the reentry plasma characteristic of the spacecraft. After determine the average electron density of the plasma flat slab, the plasma flat slab is put on the transmitting antenna,and the attenuation and the antenna characteristic of electromagnetic wave in plasma are measured by transmitting and receiving horn antenna.
It is important for the communication protection of high speed spacecraft to mitigate the electromagnetic wave attenuation caused by the plasma. Based on the liquid property of plasma, a configurationis proposed to change the characteristic of the reentry plasma, and the realignment model of plasma electron density is analyzed. When the total number of electron is fixed, the electron density of plasma is arranged normal to the polarization. To analyze the mitigation of electromagnetic wave attenuation based on microwave network theory, ahe model consisted with transmitting antenna and receiving antenna is proposed. The impedance and radiation characteristic is researched. The measurement results show the electromagnetic wave attenuation is mitigated, and the gain is increased. In this model, the transmitting antenna is covered with plasma. The parameter of the plasma electron density model is optimized, and the impedance characteristic and radiation characteristic in every frequency band is simulated and analyzed. The results show the proposed plasma model can reduce the absorption and reflection of electromagnetic wave, reduce the return loss of antenna, and increase the gain of antenna. The results in experiment show the proposed method can mitigate the electromagnetic wave attenuation, and improve the antenna characteristic.
For some high speed spacecrafts with high electron density plasma jet, a method is proposed to form a plasma antenna by plasma jet with high electron density. Based on the similar metal characteristic of plasma and metal antenna theory, the impedance characteristic and radiation characteristic of plasma monopole antenna is analyzed. The plasma antenna used on the spacecraft can be formed with appropriate feeding and configuration design. To analyze the antenna characteristic, the columnar plasma antenna and conical plasma antenna fed by coaxial line are simulated and analyzed. To adapt the reentry environment, a columnar plasma antenna with ground covered by plasma is researched. To adapt the application of reentry spacecraft, a columnar plasma antenna model fed by metal ring is proposed, and a dielectric ring is used between the feeding metal ring and columnar plasma to avoid the high temperature ablation. The columnar plasma antenna fed by metal ring surround by plasma is researched. A columnar plasma antenna fed by metal ring is designed and measured. The experiment results show the plasma can radiate the electromagnetic wave.To adapt the ues of wideband communication system, some wideband plasma antennas are proposed, such as circular plasma monopole antenna and elliptic plasma monopole antenna based on circular monopole theory. The impedance characteristic and radiation characteristic of these antennae are simulated and analyzed. The results show that the band width of the novel plasma antenna is extended markedly.
The electromagnetic wave attenuation of high speed reentry in aerosphere stage is analyzed in detail. Based on the liquid property of plasma and the similar metal characteristic of plasma, two methods of electromagnetic wave attenuation mitigation are proposed. The model of electromagnetic wave attenuation mitigation is designed and analyzed by theory and simulation, and the experiment is proposed and researched. The simulation and experiment results are the consultation for flight experiments.
引文
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