CN114152817A - Space environment sensing method based on broadband antenna - Google Patents
Space environment sensing method based on broadband antenna Download PDFInfo
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- CN114152817A CN114152817A CN202111312944.9A CN202111312944A CN114152817A CN 114152817 A CN114152817 A CN 114152817A CN 202111312944 A CN202111312944 A CN 202111312944A CN 114152817 A CN114152817 A CN 114152817A
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- 238000012544 monitoring process Methods 0.000 claims abstract description 5
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- 238000005859 coupling reaction Methods 0.000 claims abstract description 4
- 238000005259 measurement Methods 0.000 claims description 11
- 238000004422 calculation algorithm Methods 0.000 claims description 7
- 230000008447 perception Effects 0.000 claims description 7
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 description 6
- 238000009825 accumulation Methods 0.000 description 4
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/08—Measuring electromagnetic field characteristics
- G01R29/10—Radiation diagrams of antennas
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Abstract
The invention discloses a space environment sensing method based on a broadband antenna, which comprises the following steps of S1: calculating the upper limit and the lower limit of the electronic density which can be sensed by the antenna according to the upper limit and the lower limit of the electronic cut-off frequency; s2: calculating an electron density-frequency-antenna working parameter data set A of the broadband antenna in the working bandwidth of the broadband antenna in the space environment of the electron density range in S1 under the theoretical environment by using an antenna and plasma coupling model, and solidifying the data set A into the spacecraft; s3: after the spacecraft normally operates in orbit, when electromagnetic waves with different frequencies in the antenna emission bandwidth are used, the input power and the reflected power of the antenna are measured by using the antenna system working state monitoring equipment, and a frequency-antenna working parameter data set B under the electron density of the antenna at the moment is calculated; s4: and comparing the data set B with the data set A to obtain the electron density value corresponding to the row, namely the real-time space environment electron density. The invention saves space resources and energy consumption resources of on-board equipment.
Description
Technical Field
The invention relates to the field of space environment sensing and spacecraft sensors, in particular to a space environment sensing method based on a broadband antenna.
Background
Spatial context awareness is an important part of spatial detection. Traditional space environment electron density perception needs the aircraft to carry a whole set of extra sensor equipment such as Langmuir probe, energy spectrometer, and these equipment only can carry on by the scientific research aircraft, and secondly these sensor equipment can occupy the valuable volume and the equipment resource of satellite, and in case launch rises to the air and can't upgrade and maintain, can appear because many factors such as radiation among the space environment and equipment ageing, the serious decline problem of perception accuracy.
Disclosure of Invention
The invention aims to overcome the technical defects and provides a space environment sensing method based on a broadband antenna, which is a method for sensing the electron density in a space environment, particularly a space by using a broadband transmitting antenna of spacecraft equipment, so that a whole set of additional equipment space resources and energy consumption resources can be saved, and the utilization rate of the equipment is improved; and the method can remotely maintain and adjust parameters at the later stage to improve the equipment sensing precision and improve the maintainability.
In order to achieve the purpose, the invention provides the following technical scheme: a space environment sensing method based on a broadband antenna comprises the following steps:
s1: the upper limit and the lower limit of the cut-off frequency of electrons in the space corresponding to the upper limit and the lower limit of the working frequency of the antenna are calculated according to the upper limit and the lower limit of the cut-off frequency of the electrons, and the upper limit and the lower limit of the electron density which can be sensed by the antenna are calculated according to the upper limit and the lower limit of the cut-off frequency of the electrons;
s2: calculating an electron density-frequency-antenna working parameter data set A, namely a reference data set, of the broadband antenna within the working bandwidth in the space environment of the electron density range in the step S1 under the theoretical environment by using an antenna and plasma coupling model; the higher the resolution of the data set is, the higher the spatial electron density precision obtained by inversion is; solidifying the data set result obtained by calculation into the spacecraft equipment;
s3: after the spacecraft normally operates in orbit, when electromagnetic waves with different frequencies in the antenna emission bandwidth are used, the input power and the reflected power of the antenna are measured by using the antenna system working state monitoring equipment, and a frequency-antenna working parameter data set B, namely a measurement data set, of the antenna under the electron density at the moment can be obtained by calculation according to the two data;
s4: and (4) comparing the frequency-antenna working parameter data set B obtained in the step (S3) with the rows in the data set A in the step (S2), wherein the electron density value corresponding to the rows obtained by comparison is the real-time space environment electron density. However, due to the existence of the measurement error, the input power and the reflected power of the data antenna measured in step S3 have errors, and eventually, the measurement data set B in step S3 and the reference data set a in step S2 may not be completely matched, and the optimal matching is performed using the algorithm. In this step, an algorithm is used to perform optimal matching between the measured data set B in S3 and the reference data set a in S2, and the matched data is the optimal data.
Further, the data set a is an electron density-frequency-return loss data set, and the data set B is a frequency-return loss data set.
The invention has the beneficial effects that:
(1) according to the invention, the aerial carried by the spacecraft can be used as the sensor to detect the space environment, the space environment can be sensed by monitoring the work data of the aerial while the aerial works, the traditional space environment detection sensor is replaced, and space resources and energy consumption resources of on-board equipment are saved.
(2) In the implementation process of the invention, the space environment electronic density data can be quickly obtained in the data table which is calculated on the ground in advance only according to the monitored antenna working data, and the requirement on the computing resources of the satellite-borne equipment is extremely low.
(3) The invention considers the problem of large final perception precision error caused by the measurement error generated in the actual working process of the equipment, introduces a new algorithm and can greatly improve the perception precision.
(4) The invention can update the data table through remote maintenance, can ensure the detection precision in the equipment aging process through adjusting parameters, greatly improves the maintainability and prolongs the service life of the space vehicle.
Drawings
FIG. 1 is a flow chart of the present invention;
fig. 2 is a schematic diagram of the detection circuit in step S3;
FIG. 3 is a graph of mean error versus measurement error for a match;
FIG. 4 is a graph of standard deviation of error for a match versus measurement error.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings and embodiments. The embodiments described herein are only for explaining the technical solution of the present invention and are not limited to the present invention.
The satellite-borne antenna in the embodiment of the invention is a broadband antenna carried by a satellite, and can emit electromagnetic waves with the frequency of 30KHz-3 MHz.
In the embodiment of the invention, as shown in fig. 1, the upper and lower limits of the working frequency range of the satellite are firstly utilized for 30KHz and 3MHz, and according to the formula:
where N is electron density, f is antenna frequency, m is electron mass, ε0Is the dielectric constant in vacuum, and e is the electron charge. The electron density range that the antenna can sense is calculated to be 1.13x107m-3To 1.13x1011m-3。
Taking N points in the electron density range, and calculating N electron densities N by using an antenna and space environment coupling modeliAntenna operating frequency f at (i ═ 1, 2.. n)i(i ═ 1,2,. m) and return loss RijCorresponding data of (i ═ 1, 2.. times, m) (j ═ 1, 2.. times, n), the reference data set a finally obtained is as follows:
the above data is consolidated into the aircraft.
The aircraft operates in space plasma in orbit, when the antenna works, the broadband antenna emits m frequency points with frequency f at the frequency sweeping frequency of 30KHz-3MHz of the bandwidthiElectromagnetic waves of (i ═ 1, 2.. m), the surrounding space environment does not change during the process because the process time is extremely short. The antenna system monitors the input power and the reflected power of the antenna when the antenna works at each frequency point electromagnetic wave, and the monitoring function is carried by the aircraft antenna system and is generally realized by adopting a bridge method, as shown in figure 2. At frequency point fkInput power P of time antennainkAnd reflected power PrekThe return loss R of the antenna can be obtained by calculationkComprises the following steps:
and finally, obtaining a data set B of the whole frequency band as follows:
comparing the data set B with the data set A obtained in the first step to obtain the electron density NkAnd (k ═ 1, 2.., n) is the electron density of the space environment at this time. However, due to the error of the measured value, any line N may not be actually comparedk(k ═ 1, 2.. times, n) corresponding data. At this time, the following algorithm is adopted to match the data corresponding to the electron density of the closest line, namely the electron density of the space environment at this time.
The algorithm comprises the following specific steps:
1. the process of acquiring data set B is repeated y times for coherent accumulation and averaged
2. Starting from the first line of the reference data set A, the following operations are performed on the elements in A and B
3. The operation is carried out on each row of A to obtain the S value of each row
4. Find out the minimum S value in S value array and its index x
Sx＝min[S1,S2,...,Sn]
5.NxNamely the matched optimal space environment electron density.
According to the method, the electron density data of the space environment are matched, the influence of the measurement error on the final result is effectively filtered, and the accumulation times y can be selected according to the requirement.
Fig. 3 and 4 show simulations of the sensing method, where m is 298 and n is 40. As shown in simulation, the algorithm has high result precision, even if the measurement error is large, the error of the result can still be controlled within a certain level to a certain extent, the value of mn can be far larger than the value in the actual use process, and the corresponding result precision can also be improved in a multiplied way. And the more the accumulation times, the higher the accuracy of the finally obtained electron density, after the aircraft runs for a period of time, the equipment can inevitably age, so that the measurement error becomes large, and the accumulation times can be properly increased at the moment so as to ensure the accuracy of the final result.
The foregoing merely represents a preferred embodiment of the invention, which is described in some detail and detail, and is not to be construed as limiting the scope of the invention. It should be noted that, for those skilled in the art, various changes, modifications and substitutions can be made without departing from the spirit of the present invention, and these are all within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116106641A (en) * | 2022-12-08 | 2023-05-12 | 南昌大学 | A high-precision and fast space environment perception method based on spaceborne antenna |
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| US20030218575A1 (en) * | 2002-05-01 | 2003-11-27 | Walker Joel F. | Plasma phased array electronic scan antenna |
| US20080000585A1 (en) * | 2006-06-30 | 2008-01-03 | Korea Research Institute Of Standards And Science | Apparatus for monitoring electron density and electron temperature of plasma and method thereof |
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| US20030218575A1 (en) * | 2002-05-01 | 2003-11-27 | Walker Joel F. | Plasma phased array electronic scan antenna |
| US20080000585A1 (en) * | 2006-06-30 | 2008-01-03 | Korea Research Institute Of Standards And Science | Apparatus for monitoring electron density and electron temperature of plasma and method thereof |
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| CN102610922A (en) * | 2012-03-31 | 2012-07-25 | 北京邮电大学 | Dynamic tunable microstrip antenna used in complex radio-wave environment and tuning method thereof |
| CN106371084A (en) * | 2016-12-02 | 2017-02-01 | 中国电波传播研究所（中国电子科技集团公司第二十二研究所） | Detection method for electron density of ionization layer based on radar echoes |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116106641A (en) * | 2022-12-08 | 2023-05-12 | 南昌大学 | A high-precision and fast space environment perception method based on spaceborne antenna |
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