CN105244636B - A kind of conversion coefficient computational methods of spacecraft module internal electric field measurement antenna - Google Patents
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Abstract
一种航天器舱内电场测量天线的转换系数计算方法，利用软件仿真的方法建立收发链路模型，并在测量天线包络上建立电场探针，模拟喇叭天线模型口面与测量天线模型口面之间不同距离条件下的收发链路模型，获取电场探针数值和测量天线端口电压数值，并对获取的数值进行拟合，获得电场探针数值和测量天线端口电压数值之间的关系曲线，最终获得测量天线的转换系数，该方法通过计算机模拟的方法实现了航天器舱内电场测量天线的转换系数的获取，与现有方法相比，大大简化了求解过程，缩短了求解时间，节约了求解成本，最大程度上满足了航天器舱内电场测量天线的转换系数计算的需求。
A method for calculating the conversion coefficient of the electric field measurement antenna in the spacecraft cabin, using software simulation to establish a transceiver link model, and establishing an electric field probe on the measurement antenna envelope, simulating the mouth surface of the horn antenna model and the measurement antenna model The transceiver link model under different distance conditions, obtain the electric field probe value and the measured antenna port voltage value, and fit the obtained value to obtain the relationship curve between the electric field probe value and the measured antenna port voltage value, Finally, the conversion coefficient of the measurement antenna is obtained. This method realizes the acquisition of the conversion coefficient of the electric field measurement antenna in the spacecraft cabin through computer simulation. Compared with the existing method, it greatly simplifies the solution process, shortens the solution time, and saves The solution cost meets the requirements of the calculation of the conversion coefficient of the electric field measurement antenna in the spacecraft cabin to the greatest extent.
Description
技术领域technical field
本发明涉及一种天线转换系数计算方法，特别是一种航天器舱内电场测量天线的转换系数计算方法，属于电磁场与微波技术领域。The invention relates to a method for calculating the conversion coefficient of an antenna, in particular to a method for calculating the conversion coefficient of an electric field measurement antenna in a spacecraft cabin, and belongs to the technical field of electromagnetic fields and microwaves.
背景技术Background technique
航天器的电磁环境适应性是其可靠性设计和电磁兼容性设计必须考虑的重要问题，随着航天器在功能和性能上的提高，产品集成度的增大，在有限的空间内收发天线密集，使航天器舱体内部的电磁环境日趋复杂。为了获取舱体内部的电场分布和量级情况，通常在舱体内部布置商用电场探头进行测量，然而现有的商用电场探头存在一定局限性，一是其灵敏度较低，最小响应幅度约为5V/m，无法测量更小的信号，二是其输出为一个所有测量频段的综合电场强度，无法获知其中任意频点处的电场分布和大小，因此需要利用小型测量天线来完成航天器舱内电场的测量，亟需一种快速、高效求解航天器舱内电场测量天线的转换系数的方法。The electromagnetic environment adaptability of the spacecraft is an important issue that must be considered in its reliability design and electromagnetic compatibility design. With the improvement of the function and performance of the spacecraft and the increase of product integration, the transceiver antennas are densely packed in a limited space. , making the electromagnetic environment inside the spacecraft cabin increasingly complex. In order to obtain the electric field distribution and magnitude inside the cabin, commercial electric field probes are usually arranged inside the cabin for measurement. However, the existing commercial electric field probes have certain limitations. First, their sensitivity is low, and the minimum response range is about 5V /m, smaller signals cannot be measured, and the second is that its output is a comprehensive electric field strength of all measurement frequency bands, and the distribution and magnitude of the electric field at any frequency point cannot be known, so it is necessary to use a small measurement antenna to complete the electric field in the spacecraft cabin There is an urgent need for a fast and efficient method to solve the conversion coefficient of the electric field measurement antenna in the spacecraft cabin.
现有主要通过实验的方法来求解航天器舱内电场测量天线的转换系数，利用该方法可以保证转换系数求解的精度，但该方法需要专业的场地和设备实现，实验一次需要耗时1～2天，且花费在几万元，无法满足快速、高效获取航天器舱内电场测量天线的转换系数的日常需求。At present, the conversion coefficient of the electric field measurement antenna in the spacecraft cabin is mainly solved by the experimental method. Using this method can ensure the accuracy of the conversion coefficient solution, but this method requires professional venues and equipment to implement, and it takes 1 to 2 hours for one experiment. days, and the cost is tens of thousands of yuan, which cannot meet the daily needs of quickly and efficiently obtaining the conversion coefficient of the electric field measurement antenna in the spacecraft cabin.
发明内容Contents of the invention
本发明的技术解决问题是：克服现有技术的不足，提供了一种航天器舱内电场测量天线的转换系数计算方法，利用软件仿真的方法建立收发链路模型，并在测量天线包络上建立电场探针，模拟喇叭天线模型口面与测量天线模型口面之间不同距离条件下的收发链路模型，获取电场探针数值和测量天线端口电压数值，并对获取的数值进行拟合，获得电场探针数值和测量天线端口电压数值之间的关系曲线，最终获得测量天线的转换系数，该方法通过计算机模拟的方法实现了航天器舱内电场测量天线的转换系数的获取，与现有方法相比，大大简化了求解过程，缩短了求解时间，节约了求解成本，最大程度上满足了航天器舱内电场测量天线的转换系数计算的需求。The technical solution problem of the present invention is: overcome the deficiencies in the prior art, provide a kind of conversion factor calculation method of the electric field measuring antenna in the spacecraft cabin, utilize the method for software simulation to establish the transceiving link model, and measure antenna envelope Establish an electric field probe to simulate the transceiver link model under different distances between the mouth surface of the horn antenna model and the measurement antenna model, obtain the value of the electric field probe and the voltage value of the measured antenna port, and fit the obtained values, Obtain the relationship curve between the value of the electric field probe and the voltage value of the measurement antenna port, and finally obtain the conversion coefficient of the measurement antenna. This method realizes the acquisition of the conversion coefficient of the electric field measurement antenna in the spacecraft cabin through computer simulation, which is different from the existing Compared with the method, the solution process is greatly simplified, the solution time is shortened, the solution cost is saved, and the requirements for the calculation of the conversion coefficient of the electric field measurement antenna in the spacecraft cabin are met to the greatest extent.
本发明的技术解决方案是：一种航天器舱内电场测量天线的转换系数计算方法，包括以下步骤：The technical solution of the present invention is: a kind of conversion factor calculation method of the electric field measuring antenna in the spacecraft cabin, comprises the following steps:
(1)根据待求转换系数的频率范围f，在电磁仿真软件中建立喇叭天线的模型，所述喇叭天线的工作频段覆盖待求转换系数的频率范围f；(1) according to the frequency range f of the conversion coefficient to be sought, the model of the horn antenna is set up in the electromagnetic simulation software, and the operating frequency band of the horn antenna covers the frequency range f of the conversion coefficient to be sought;
(2)根据预先给定的测量天线的结构尺寸参数和电气性能指标，在电磁仿真软件中建立测量天线的模型，所述电气性能指标包括天线的电压驻波比和增益，所述测量天线的结构尺寸参数包括介质基板尺寸、辐射贴片尺寸、馈电探针位置和材料特性；(2) According to the structural size parameters and electrical performance indicators of the predetermined measurement antenna, the model of the measurement antenna is established in the electromagnetic simulation software, the electrical performance indicators include the voltage standing wave ratio and the gain of the antenna, and the measurement antenna Structural size parameters include dielectric substrate size, radiation patch size, feeding probe position and material properties;
(3)在电磁仿真软件中，利用步骤(2)中建立的测量天线模型，仿真计算出测量天线的电压驻波比和增益，并与步骤(2)中预先给定的天线电压驻波比和增益比较，若达到指标要求，则进入步骤(4)；否则，对测量天线模型的结构尺寸参数进行调整后再进行仿真计算和比较，直到达到指标要求后进入步骤(4)；(3) In the electromagnetic simulation software, use the measurement antenna model established in step (2) to simulate and calculate the voltage standing wave ratio and gain of the measurement antenna, and compare it with the predetermined antenna voltage standing wave ratio in step (2). Compared with the gain, if the index requirements are met, then enter step (4); otherwise, adjust the structural size parameters of the measurement antenna model and then perform simulation calculation and comparison until the index requirements are met and enter step (4);
(4)以步骤(1)中的喇叭天线模型作为发射天线，步骤(3)中的测量天线模型作为接收天线，建立收发链路模型，所述喇叭天线模型口面与接收天线模型口面之间的距离为L；(4) with the horn antenna model in the step (1) as the transmitting antenna, the measurement antenna model in the step (3) as the receiving antenna, set up the transceiver link model, the mouth of the horn antenna model and the mouth of the receiving antenna model The distance between is L;
(5)在步骤(3)中建立的测量天线模型结构包络上建立N个电场探针；(5) set up N electric field probes on the measurement antenna model structural envelope set up in step (3);
(6)设置L＝L1；(6) Set L=L1;
(7)设置喇叭天线和测量天线的馈电端口为波导端口，喇叭天线端口馈电功率为Pin，求解频率为f，仿真计算收发链路模型；(7) The feeding port of the horn antenna and the measuring antenna is set as a waveguide port, the feed power of the horn antenna port is P in , the solution frequency is f, and the simulation calculation link model is calculated;
(8)在收发链路模型仿真计算完成后，从计算结果中获取喇叭天线到测量天线端口的传输系数，并进行Round数学求整，记为S21，则测量天线端口接收功率Pout由公式：(8) After the simulation calculation of the transceiver link model is completed, the transmission coefficient from the horn antenna to the measurement antenna port is obtained from the calculation result, and rounded mathematically, which is denoted as S 21 , then the received power P out of the measurement antenna port is given by the formula :
Pout＝Pin+S21 P out =P in +S 21
给出；give;
(9)从计算结果中获取测量天线结构包络的N个电场探针的数值，去除N个值中的最大值和最小值，将剩余N-2个电场值取平均数，并进行Round数学求整，记为Eav；(9) Obtain the values of the N electric field probes for measuring the envelope of the antenna structure from the calculation results, remove the maximum and minimum values of the N values, average the remaining N-2 electric field values, and perform Round mathematics Find the integer and record it as E av ;
(10)将步骤(8)中获得的Pout值设为X轴，步骤(9)中获得的电场平均值Eav设为Y轴，在直角坐标系中描出此点；(10) set the P out value obtained in step (8) as the X axis, and set the electric field average E av obtained in the step (9) as the Y axis, and trace this point in the Cartesian coordinate system;
(11)设置L＝L2，重复(7)～(10)步；(11) set L=L2, repeat (7)～(10) steps;
(12)设置L＝L3，重复(7)～(10)步；(12) set L=L3, repeat (7)～(10) steps;
(13)将(10)～(12)步在直角坐标系中描出的3点按照最小二乘法进行曲线拟合，所得直线为所求频点f处测量天线测量电场强度与端口接收功率之间关系曲线；(13) Carry out curve fitting on the three points drawn in steps (10)~(12) in the Cartesian coordinate system according to the least square method, and the obtained straight line is the distance between the measured electric field strength of the measuring antenna at the frequency point f and the received power of the port Relationship lines;
(14)在步骤(13)获取的关系曲线上任意取一点(x，y)，频点f处测量天线的转换系数TF通过公式：(14) arbitrarily get a point (x, y) on the relational curve that step (13) obtains, the conversion coefficient TF of measuring antenna at frequency point f is by formula:
TF(dB/m)＝y(dBuV/m)-107(dB)-x(dBm)TF(dB/m)=y(dBuV/m)-107(dB)-x(dBm)
给出。give.
所述步骤(3)中达到指标要求具体为：仿真计算出的测量天线的电压驻波比与预先给定的天线电压驻波比之间差值的绝对值与预先给定的天线电压驻波比之比小于预设的电压驻波比阈值；且仿真计算出的测量天线的增益与预先给定的天线增益之间差值的绝对值与预先给定的天线增益的绝对值之比小于预设的增益阈值；所述电压驻波比阈值和增益阈值的取值范围均为：1％～5％。Reaching the index requirement in the described step (3) is specifically: the absolute value of the difference between the voltage standing wave ratio of the measurement antenna calculated by simulation and the predetermined antenna voltage standing wave ratio and the predetermined antenna voltage standing wave ratio The ratio ratio is less than the preset voltage standing wave ratio threshold; and the ratio of the absolute value of the difference between the gain of the measured antenna calculated by simulation and the predetermined antenna gain to the absolute value of the predetermined antenna gain is less than the preset The gain threshold is set; the value ranges of the voltage standing wave ratio threshold and the gain threshold are both: 1% to 5%.
所述喇叭天线模型的口面正对测量天线模型的口面，且两天线模型的极化方式相同。The mouth surface of the horn antenna model faces the mouth surface of the measurement antenna model, and the polarization modes of the two antenna models are the same.
所述在步骤(3)中建立的测量天线模型结构包络上建立N个电场探针，具体为：Set up N electric field probes on the measurement antenna model structure envelope set up in step (3), specifically:
若测量天线为全向天线，则正辐射方向对应的结构包络与反辐射方向对应的结构包络对称，正辐射方向对应的结构包络与反辐射方向对应的结构包络上的电场探针数量相同，且位置一一对应；If the measuring antenna is an omnidirectional antenna, the structural envelope corresponding to the forward radiation direction is symmetrical to the structural envelope corresponding to the reverse radiation direction, and the electric field probe on the structural envelope corresponding to the forward radiation direction and the structural envelope corresponding to the reverse radiation direction The number is the same, and the positions correspond to each other;
若测量天线为定向天线，则在测量天线辐射方向正对的结构包络上建立电场探测。If the measuring antenna is a directional antenna, the electric field detection is established on the structure envelope facing the radiation direction of the measuring antenna.
所述N大于等于10。The N is greater than or equal to 10.
所述测量天线模型结构包络与测量天线表面的距离为h，具体由公式：The distance between the structural envelope of the measuring antenna model and the surface of the measuring antenna is h, specifically by the formula:
给出，其中c为真空中光速，f为待求转换系数的频点。Given, where c is the speed of light in vacuum, and f is the frequency point of the conversion coefficient to be obtained.
所述电场探针在测量天线模型结构包络上均匀分布。The electric field probes are uniformly distributed on the structural envelope of the measuring antenna model.
所述L1>L2>L3>0。The L1>L2>L3>0.
本发明与现有技术相比的有益效果是：The beneficial effect of the present invention compared with prior art is:
本发明基于单台计算机对收发链路进行模拟，实现了航天器舱内电场测量天线转换系数的计算，与现有的实验方法相比，大大简化了求解过程，缩短了求解时间，节约了求解成本。The invention simulates the transceiver link based on a single computer, and realizes the calculation of the conversion coefficient of the electric field measurement antenna in the spacecraft cabin. Compared with the existing experimental method, the solution process is greatly simplified, the solution time is shortened, and the solution cost is saved. cost.
附图说明Description of drawings
图1为本发明流程图；Fig. 1 is a flowchart of the present invention;
图2为测量天线结构示意图；Figure 2 is a schematic diagram of the measurement antenna structure;
图3为收发链路模型示意图；Figure 3 is a schematic diagram of a transceiver link model;
图4为本发明中实施例电场探针设置示意图；Fig. 4 is the schematic diagram of the setting of the electric field probe in the embodiment of the present invention;
图5为本发明仿真结果示意图。Fig. 5 is a schematic diagram of the simulation results of the present invention.
具体实施方式detailed description
下面结合附图对本发明的具体实施方式进行进一步的详细描述。Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.
基于现有商用探头的弊端，采用了一套小型化的舱内电场测量系统，系统前端为一矩形印刷贴片天线，通过连接后端的频谱仪等设备可以直观的测到舱内任意频点处的电场分布和相对量级情况。此系统的输出为电场经测量天线在天线端口处的接收功率值P，只能测量不同位置处功率的相对变化情况，由于电场E需要通过式E＝TF+P计算，没有测量天线的转换系数TF，测量天线所处位置的具体电场强度大小仍未知。为了进一步获取具体频点、具体位置处的具体电场强度大小，需要获取测量天线的转换系数，其描述的是将所处空间电场转换为天线端口功率的能力，然而由于研制的测量天线尺寸过小且只有一套，传统的基于试验的天线转换系数计算方法，如两天线法和三天线法无法适用，因此结合舱内电场分布特点以及数字化仿真设计技术，提出一种计算舱内电场测量天线的转换系数的方法。Based on the shortcomings of existing commercial probes, a set of miniaturized in-cabin electric field measurement system is adopted. The front end of the system is a rectangular printed patch antenna, which can be intuitively measured at any frequency point in the cabin by connecting the spectrum analyzer and other equipment at the back end. The electric field distribution and relative magnitude of the situation. The output of this system is the received power value P of the electric field at the antenna port by measuring the antenna. It can only measure the relative change of power at different positions. Since the electric field E needs to be calculated by the formula E=TF+P, there is no conversion coefficient for the measured antenna. TF, the specific electric field strength at the location of the measuring antenna is still unknown. In order to further obtain the specific electric field intensity at specific frequency points and specific locations, it is necessary to obtain the conversion coefficient of the measurement antenna, which describes the ability to convert the electric field in the space into the power of the antenna port. However, the size of the developed measurement antenna is too small And there is only one set, the traditional test-based antenna conversion coefficient calculation method, such as the two-antenna method and the three-antenna method, cannot be applied. Therefore, combining the characteristics of the electric field distribution in the cabin and digital simulation design technology, a method for calculating the electric field measurement antenna in the cabin is proposed. Method for converting coefficients.
本方法通过构建以喇叭天线和测量天线为单元的收发链路模型，并在测量天线周围建立电场探针包络，计算获取收发链路间的隔离度信息反演出测量天线端口电压值，并结合包络电场的平均值，运用线性规划方法计算得到测量天线的转换系数值。This method builds a transceiver link model with the horn antenna and the measurement antenna as the unit, and establishes an electric field probe envelope around the measurement antenna, calculates and obtains the isolation information between the transceiver links to invert the measurement antenna port voltage value, and combines The average value of the envelope electric field is calculated by using the linear programming method to obtain the conversion coefficient value of the measuring antenna.
如图1所示为本发明的方法流程图，从图1可知，本发明中一种航天器舱内电场测量天线的转换系数计算方法，其特征在于包括以下步骤：As shown in Figure 1 is the method flow chart of the present invention, as can be seen from Figure 1, a kind of conversion factor calculation method of the electric field measuring antenna in the spacecraft cabin among the present invention, it is characterized in that comprising the following steps:
(1)根据待求转换系数的频率范围f，在电磁仿真软件中建立喇叭天线的模型，所述喇叭天线的工作频段覆盖待求转换系数的频率范围f；所述电磁仿真软件可以采用HFSS、CST或者FEKO。(1) according to the frequency range f of the conversion coefficient to be sought, the model of the horn antenna is set up in the electromagnetic simulation software, and the operating frequency band of the horn antenna covers the frequency range f of the conversion coefficient to be sought; the electromagnetic simulation software can adopt HFSS, CST or FEKO.
(2)根据预先给定的测量天线的结构尺寸参数和电气性能指标，在电磁仿真软件中建立测量天线的模型，所述电气性能指标包括天线的电压驻波比和增益，所述测量天线的结构尺寸参数包括、介质基板尺寸、辐射贴片尺寸、馈电探针位置和材料特性；测量天线示意图见图2；(2) According to the structural size parameters and electrical performance indicators of the predetermined measurement antenna, the model of the measurement antenna is established in the electromagnetic simulation software, the electrical performance indicators include the voltage standing wave ratio and the gain of the antenna, and the measurement antenna Structural size parameters include dielectric substrate size, radiation patch size, feeding probe position and material properties; the schematic diagram of the measurement antenna is shown in Figure 2;
(3)在电磁仿真软件中，利用步骤(2)中建立的测量天线模型，仿真计算出测量天线的电压驻波比和增益，并与步骤(2)中预先给定的天线电压驻波比和增益比较，若达到指标要求，则进入步骤(4)；否则，对测量天线模型的结构尺寸参数进行调整后再进行仿真计算和比较，直到达到指标要求后进入步骤(4)；所述达到指标要求具体为：仿真计算出的测量天线的电压驻波比与预先给定的天线电压驻波比之间差值的绝对值与预先给定的天线电压驻波比之比小于预设的电压驻波比阈值；且仿真计算出的测量天线的增益与预先给定的天线增益之间差值的绝对值与预先给定的天线增益的绝对值之比小于预设的增益阈值；所述电压驻波比阈值和增益阈值的取值范围均为：1％～5％。通过阈值的选取可以保证不同计算精度转换系数的获取。(3) In the electromagnetic simulation software, use the measurement antenna model established in step (2) to simulate and calculate the voltage standing wave ratio and gain of the measurement antenna, and compare it with the predetermined antenna voltage standing wave ratio in step (2). Compared with the gain, if the index requirement is reached, then enter step (4); otherwise, after adjusting the structural size parameters of the measurement antenna model, carry out simulation calculation and comparison until reaching the index requirement and then enter step (4); The index requirements are specifically: the ratio of the absolute value of the difference between the voltage standing wave ratio of the measured antenna calculated by simulation and the predetermined antenna voltage standing wave ratio to the predetermined antenna voltage standing wave ratio is less than the preset voltage The standing wave ratio threshold; and the ratio of the absolute value of the difference between the gain of the measured antenna calculated by simulation and the predetermined antenna gain to the absolute value of the predetermined antenna gain is less than the preset gain threshold; the voltage The value ranges of the standing wave ratio threshold and the gain threshold are both: 1% to 5%. The selection of the threshold can ensure the acquisition of conversion coefficients with different calculation precisions.
(4)以步骤(1)中的喇叭天线模型作为发射天线，步骤(3)中的测量天线模型作为接收天线，建立收发链路模型，具体如图3所示，所述喇叭天线模型口面与接收天线模型口面之间的距离为L；优选的收发链路模型为：喇叭天线模型的口面正对测量天线模型的口面，且两天线模型的极化方式相同。当采用这样的模型时，转换系数的计算精度最高。(4) With the horn antenna model in the step (1) as the transmitting antenna, the measurement antenna model in the step (3) as the receiving antenna, set up the transceiver link model, specifically as shown in Figure 3, the mouth of the horn antenna model The distance from the face of the receiving antenna model is L; the optimal transceiver link model is: the face of the horn antenna model faces the face of the measuring antenna model, and the polarization of the two antenna models is the same. When such a model is used, the conversion factor is calculated with the highest accuracy.
(5)在步骤(3)中建立的测量天线模型结构包络上建立N个电场探针；具体为：(5) N electric field probes are set up on the measurement antenna model structural envelope set up in step (3); specifically:
所述电场探针在测量天线模型结构包络上均匀分布。若测量天线为全向天线，则正辐射方向对应的结构包络与反辐射方向对应的结构包络对称，正辐射方向对应的结构包络与反辐射方向对应的结构包络上的电场探针数量相同，且位置一一对应；The electric field probes are uniformly distributed on the structural envelope of the measuring antenna model. If the measuring antenna is an omnidirectional antenna, the structural envelope corresponding to the forward radiation direction is symmetrical to the structural envelope corresponding to the reverse radiation direction, and the electric field probe on the structural envelope corresponding to the forward radiation direction and the structural envelope corresponding to the reverse radiation direction The quantity is the same, and the positions correspond to each other;
若测量天线为定向天线，则在测量天线辐射方向正对的结构包络上建立电场探测。探针的选取需要兼顾全面性和有效性，因此需要在辐射方向上尽可能均匀分布。If the measuring antenna is a directional antenna, the electric field detection is established on the structure envelope facing the radiation direction of the measuring antenna. The selection of probes needs to take both comprehensiveness and effectiveness into account, so it needs to be distributed as evenly as possible in the radiation direction.
所述N大于等于10。The N is greater than or equal to 10.
所述测量天线模型结构包络与测量天线表面的距离为h，具体由公式：The distance between the structural envelope of the measuring antenna model and the surface of the measuring antenna is h, specifically by the formula:
给出，其中c为真空中光速，f为待求转换系数的频点。采用该距离，保证了测量天线测量的电场为包络电场。Given, where c is the speed of light in vacuum, and f is the frequency point of the conversion coefficient to be obtained. With this distance, it is guaranteed that the electric field measured by the measuring antenna is an envelope electric field.
(6)设置L＝L1；(6) Set L=L1;
(7)设置喇叭天线和测量天线的馈电端口为波导端口，喇叭天线端口馈电功率为Pin，求解频率为f，仿真计算收发链路模型；(7) The feeding port of the horn antenna and the measuring antenna is set as a waveguide port, the feed power of the horn antenna port is P in , the solution frequency is f, and the simulation calculation link model is calculated;
(8)在收发链路模型仿真计算完成后，从计算结果中获取喇叭天线到测量天线端口的传输系数，并进行Round数学求整，记为S21，则测量天线端口接收功率Pout由公式：(8) After the simulation calculation of the transceiver link model is completed, the transmission coefficient from the horn antenna to the measurement antenna port is obtained from the calculation result, and rounded mathematically, which is denoted as S 21 , then the received power P out of the measurement antenna port is given by the formula :
Pout＝Pin+S21 P out =P in +S 21
给出；give;
(9)从计算结果中获取测量天线结构包络的N个电场探针的数值，去除N个值中的最大值和最小值，将剩余N-2个电场值取平均数，并进行Round数学求整，记为Eav；(9) Obtain the values of the N electric field probes for measuring the envelope of the antenna structure from the calculation results, remove the maximum and minimum values of the N values, average the remaining N-2 electric field values, and perform Round mathematics Find the integer and record it as E av ;
(10)将步骤(8)中获得的Pout值设为X轴，步骤(9)中获得的电场平均值Eav设为Y轴，在直角坐标系中描出此点；(10) set the P out value obtained in step (8) as the X axis, and set the electric field average E av obtained in the step (9) as the Y axis, and trace this point in the Cartesian coordinate system;
(11)设置L＝L2，重复(7)～(10)步；(11) set L=L2, repeat (7)～(10) steps;
(12)设置L＝L3，重复(7)～(10)步；在实际求解过程中，一般有L1>L2>L3>0；(12) Set L=L3, repeat (7)～(10) steps; in the actual solution process, generally have L1>L2>L3>0;
(13)将(10)～(12)步在直角坐标系中描出的3点按照最小二乘法进行曲线拟合，所得直线为所求频点f处测量天线测量电场强度与端口接收功率之间关系曲线；(13) Carry out curve fitting on the three points drawn in steps (10)~(12) in the Cartesian coordinate system according to the least square method, and the obtained straight line is the distance between the measured electric field strength of the measuring antenna at the frequency point f and the received power of the port Relationship lines;
(14)在步骤(13)获取的关系曲线上任意取一点(x，y)，频点f处测量天线的转换系数TF通过公式：(14) arbitrarily get a point (x, y) on the relational curve that step (13) obtains, the conversion coefficient TF of measuring antenna at frequency point f is by formula:
TF(dB/m)＝y(dBuV/m)-107(dB)-x(dBm)TF(dB/m)=y(dBuV/m)-107(dB)-x(dBm)
给出。give.
具体实施例specific embodiment
本发明以一个全向天线为例对本发明中的方法进行验证，在测量天线模型结构包络正面设置9个电场探针，9个探针位于同一个捕获平面，9个探针在测量天线正面的投影分别位于测量天线正面的中心，4个顶角和4条边的中心；在测量天线模型结构包络的背面按同样方式设置9个电场探针，具体如图4所示。The present invention takes an omnidirectional antenna as an example to verify the method in the present invention. Nine electric field probes are set on the front of the envelope of the measuring antenna model structure. The nine probes are located on the same capture plane, and the nine probes are on the front of the measuring antenna. The projections of are respectively located at the center of the front of the measuring antenna, the center of the four corners and the center of the four sides; 9 electric field probes are set in the same way on the back of the measuring antenna model structure envelope, as shown in Figure 4.
设置L1＝1m，L2＝0.5m，L3＝0.25m，仿真结果如图5所示，从图5可知，利用本发明中的方法计算转换系数TF，进而计算得到的舱内电场与理论TF计算得到的电场很接近，与商用探头测得的电场值之间的误差小于6dB，满足航天器舱内电场环境测量需求。Set L1=1m, L2=0.5m, L3=0.25m, the simulation result is as shown in Figure 5, as can be seen from Figure 5, utilize the method in the present invention to calculate conversion factor TF, and then calculate the cabin electric field that obtains and theoretical TF calculation The obtained electric field is very close, and the error between it and the electric field value measured by the commercial probe is less than 6dB, which meets the measurement requirements of the electric field environment in the spacecraft cabin.
本发明中的实施例在计算机配置为8核2.5GHZ CPU，8GHz内存条件下，计算一次转换系数耗时2h，与实验方法相比，大大节省了计算时间。In the embodiment of the present invention, under the condition that the computer is configured with an 8-core 2.5GHZ CPU and 8GHz memory, it takes 2 hours to calculate the conversion coefficient once. Compared with the experimental method, the calculation time is greatly saved.
通过本发明方法的运用，在型号研制阶段，可以通过已有的舱内电场测量系统准确测量并计算舱内任意频点处电场的分布情况和量级大小，全面获取舱内电磁环境数据，为舱内设备设计和研制提供指标依据。Through the use of the method of the present invention, in the model development stage, the existing electric field measurement system in the cabin can accurately measure and calculate the distribution and magnitude of the electric field at any frequency point in the cabin, and obtain the electromagnetic environment data in the cabin comprehensively. In-cabin equipment design and development provide index basis.
本发明说明书中未作详细描述的内容属于本领域专业技术人员的公知技术。The content that is not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.
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