星载电场仪关键技术研究
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摘要
电场是研究空间天气学和空间环境一个很重要的参量,它的数值大小及其变化涉及到太阳活动、雷暴活动、地震活动及大气环境污染等。星载电场仪探测系统的建立将极大地完善我国气象、地震、空间天气监测以及对空间环境探测的能力,并为后续的空间探测技术的发展提供了坚实的理论基础和新的技术手段。
本文重点研究与星载双探针电场仪相关的关键技术。
由于星载电场仪在空间等离子体中进行电场探测的特殊性,很多外界因素都会影响到其探测的精度,为了避免这些因素的影响,本文详尽的分析了目前国内外所了解的可以对探测产生干扰的影响因素,重点介绍了:等离子体梯度、探针支持系统和卫星、尾流、等离子体噪声以及外界磁场和卫星姿态数据对测量造成的影响,提出了避免或减弱这些影响因素的方法。
设计了测量用的探针,介绍了其外形,材质以及外部涂层的考虑,最后给出了具体的外形参数。
设计了探针内部的恒流源电路,该恒流源输出电流最小为±10nA,最大为±1.28μA,步进为10nA,经过实验测量,对于正向恒流源电路,其相对误差最大为0.9%,对于负向恒流源电路,其最大相对误差约为1.9%。
由于探头电压未知,测量困难,如何能根据探头实际电势情况来确定偏置电流的大小,进而确定出探头的最佳工作点一直是空间电场探针中的一个难点。本文提出了一种最佳工作点确定算法,并通过同时模拟探针光电流变化和模拟探针在等离子体中的工作情况对该算法进行了验证,实验证明,采用该方法可以顺利的找到能使探头电位最接近周围的等离子体的电位,从而实现探头的自动化调整。
设计了电场仪中所用的低噪声、宽频带前置放大电路,并通过对前放电路的噪声分析,提出了进一步降低噪声的方法。所设计的前置放大电路带宽0～5MHz,需要重点关注的100Hz～30KHz频段的总输入噪声仅0.69μV。
最后,根据项目设计要求,给出了整个星载双探针电场仪的详细设计。
Space electric field is an important parameter to study space weather and space environment. The magnitude and change of its numerical value is related to solar activity, thunderstorm, earthquake, atmosphere environment pollution and so on. The foundation of the satellite-borne electric field instrument detecting system will remarkably improve the ability of the detection of weather, earthquake, space weather and space environment. It also provides new theory and technology for the development of space detection.
This paper mainly studies the key technology of satellite-borne double probe electric field instrument.
Because of the particularity of the electric field detection using the satellite-borne electric field instrument in space plasma, many outside factors will influence the detection precision. To avoid the influence of the outside factors, this paper analyses the influence factors at home and abroad which could disturb the detection in detail , emphatically introduces plasma gradient, satellite and probe support system, wake, plasma noise and the influence of outside magnetic field and satellite attitude on detection, and also present the method to avoid or weaken the influential factors.
The probe for detection is designed and the shape, material, external coating and the detailed configuration parameters of the probe is introduced.
The current source is introduced. The current source can provide aconstant current varying from -1. 28μA to 1. 28μA in 256 steps, which ischanged along with the input control voltage. Each step varied 10nA. The experimental measurement shows the max relative error of positive current source is 0. 9% and the max relative error of negative current source is 1.9%.
Because the probe potential is unknown and is difficult to measure, it is difficult to obtain the bias current through the actual probe potential and find the optimum operating point of the probe .This paper presents a method to find the optimum operating point and validates it through experiment of simulating the probe photocurrent changes and the work situations of the probe in the plasma. The experiment shows that this method can obtain the probe potential which is mostly close to the potential of the ambient plasma and achieves the probe automatic adjusting.
Based on the analysis of detection theory of satellite-borne electric field instrument, the design of a wide-band low noise preamplifier circuit used in the electric field instrument is introduced. Then the noise analysis of the preamplifier circuit and the method of reducing noise are presented. The bandwidth of this preamplifier circuit is 0～5MHz and theinput noise of the 100Hz~30KHz frequency range is only 0. 69μV.
Finally, according to the need of the project, the detailed design of the whole satellite-borne double probe electric field instrument is presented.
本文重点研究与星载双探针电场仪相关的关键技术。
由于星载电场仪在空间等离子体中进行电场探测的特殊性,很多外界因素都会影响到其探测的精度,为了避免这些因素的影响,本文详尽的分析了目前国内外所了解的可以对探测产生干扰的影响因素,重点介绍了:等离子体梯度、探针支持系统和卫星、尾流、等离子体噪声以及外界磁场和卫星姿态数据对测量造成的影响,提出了避免或减弱这些影响因素的方法。
设计了测量用的探针,介绍了其外形,材质以及外部涂层的考虑,最后给出了具体的外形参数。
设计了探针内部的恒流源电路,该恒流源输出电流最小为±10nA,最大为±1.28μA,步进为10nA,经过实验测量,对于正向恒流源电路,其相对误差最大为0.9%,对于负向恒流源电路,其最大相对误差约为1.9%。
由于探头电压未知,测量困难,如何能根据探头实际电势情况来确定偏置电流的大小,进而确定出探头的最佳工作点一直是空间电场探针中的一个难点。本文提出了一种最佳工作点确定算法,并通过同时模拟探针光电流变化和模拟探针在等离子体中的工作情况对该算法进行了验证,实验证明,采用该方法可以顺利的找到能使探头电位最接近周围的等离子体的电位,从而实现探头的自动化调整。
设计了电场仪中所用的低噪声、宽频带前置放大电路,并通过对前放电路的噪声分析,提出了进一步降低噪声的方法。所设计的前置放大电路带宽0～5MHz,需要重点关注的100Hz～30KHz频段的总输入噪声仅0.69μV。
最后,根据项目设计要求,给出了整个星载双探针电场仪的详细设计。
Space electric field is an important parameter to study space weather and space environment. The magnitude and change of its numerical value is related to solar activity, thunderstorm, earthquake, atmosphere environment pollution and so on. The foundation of the satellite-borne electric field instrument detecting system will remarkably improve the ability of the detection of weather, earthquake, space weather and space environment. It also provides new theory and technology for the development of space detection.
This paper mainly studies the key technology of satellite-borne double probe electric field instrument.
Because of the particularity of the electric field detection using the satellite-borne electric field instrument in space plasma, many outside factors will influence the detection precision. To avoid the influence of the outside factors, this paper analyses the influence factors at home and abroad which could disturb the detection in detail , emphatically introduces plasma gradient, satellite and probe support system, wake, plasma noise and the influence of outside magnetic field and satellite attitude on detection, and also present the method to avoid or weaken the influential factors.
The probe for detection is designed and the shape, material, external coating and the detailed configuration parameters of the probe is introduced.
The current source is introduced. The current source can provide aconstant current varying from -1. 28μA to 1. 28μA in 256 steps, which ischanged along with the input control voltage. Each step varied 10nA. The experimental measurement shows the max relative error of positive current source is 0. 9% and the max relative error of negative current source is 1.9%.
Because the probe potential is unknown and is difficult to measure, it is difficult to obtain the bias current through the actual probe potential and find the optimum operating point of the probe .This paper presents a method to find the optimum operating point and validates it through experiment of simulating the probe photocurrent changes and the work situations of the probe in the plasma. The experiment shows that this method can obtain the probe potential which is mostly close to the potential of the ambient plasma and achieves the probe automatic adjusting.
Based on the analysis of detection theory of satellite-borne electric field instrument, the design of a wide-band low noise preamplifier circuit used in the electric field instrument is introduced. Then the noise analysis of the preamplifier circuit and the method of reducing noise are presented. The bandwidth of this preamplifier circuit is 0～5MHz and theinput noise of the 100Hz~30KHz frequency range is only 0. 69μV.
Finally, according to the need of the project, the detailed design of the whole satellite-borne double probe electric field instrument is presented.
引文
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