A high-precision and fast space environment perception method based on satellite-borne antenna

Abstract

The present invention discloses a high-precision and rapid space environment perception method based on a spaceborne antenna. The method comprises the following steps: S1: a circularly polarized antenna performs left-hand circularly polarized transmission to obtain a frequency-standing wave ratio data set A of the antenna; S2: a circularly polarized antenna performs right-hand circularly polarized transmission to obtain a frequency-standing wave ratio data set B of the antenna; S3: an electron density-frequency-standing wave ratio parameter data set C of the circularly polarized antenna in a left-hand circularly polarized transmission mode and an electron density-frequency-standing wave ratio parameter data set D of the circularly polarized antenna in a space environment under a theoretical environment are calculated; and S4: data set A is matched with data set C to obtain an electron density value N corresponding to the most matched row. l , match dataset B with dataset D and get the electron density value N corresponding to the best matching row r ; S5: for N l and N r The weighted average is taken to obtain the electron density N. The present invention can quickly and accurately perceive the electron density in a space environment without accumulation.

Description

Technical Field

[0001] The present invention relates to the fields of space environment perception and spacecraft sensors, and in particular to a high-precision and rapid space environment perception method based on a satellite-borne antenna. Background Art

[0002] There are two main types of existing space-borne space environment perception equipment and methods: active sensing methods that rely on space-borne radar, and passive sensing methods that rely on space-borne sensors such as Langmuir probes and spectrometers. Active sensing methods cannot perceive the satellite's in-situ space environment due to the radar's close-range blind spot. Passive sensing methods, on the other hand, lack precision, are highly volatile due to the influence of the space environment, require data accumulation, and have low sensing speeds and high latency in obtaining results. Summary of the Invention

[0003] The purpose of the present invention is to overcome the above-mentioned technical deficiencies and propose a high-precision and rapid space environment perception method based on satellite-borne antennas, which uses the satellite's own onboard transmitting antenna to perform high-precision and high-speed perception of the space environment, especially the electron density in space. This method only requires the use of the satellite's existing antenna for circularly polarized transmission to achieve high-precision space environment perception without the need for additional equipment or accumulation, and the perception speed is extremely fast.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a high-precision and rapid space environment perception method based on a satellite-borne antenna, comprising the following steps:

[0005] S1, when the satellite is in a space environment, feed its n (n ≥ 1) circularly polarized antennas to emit left-hand circularly polarized electromagnetic waves and step-change their transmission frequency; at this time, record the antenna standing wave ratio parameters monitored by the antenna circuit to obtain the frequency-standing wave ratio dataset A of the n circularly polarized antennas in the left-hand circularly polarized transmission mode; among them, the frequency-standing wave ratio dataset of the i-th (i = 1, 2, ..., n) circularly polarized antenna in the left-hand circularly polarized transmission mode is A i ;

[0006] In S2, when the satellite is in a space environment, its n circularly polarized antennas are fed with power. The feeding phase is opposite to that in S1, causing them to emit right-hand circularly polarized electromagnetic waves and step-change their transmission frequency. At this time, the standing wave ratio parameters of the antenna monitored by the antenna circuit are recorded to obtain a frequency-standing wave ratio dataset B of n (n ≥ 1) circularly polarized antennas in the right-hand circularly polarized transmission mode. Among them, the frequency-standing wave ratio dataset of the i-th circularly polarized antenna in the right-hand circularly polarized transmission mode is B i ;

[0007] S3, using the antenna-plasma coupling model, calculate the electron density-frequency-standing wave ratio parameter dataset C of the i-th circularly polarized antenna in the left-hand circularly polarized mode in a space environment under theoretical conditions. i The electron density-frequency-standing wave ratio parameter dataset D of the antenna in right-hand circular polarization mode i , obtain the electron density-frequency-standing wave ratio parameter dataset C of n circularly polarized antennas in left-hand circular polarization mode and the electron density-frequency-standing wave ratio parameter dataset D of the antennas in right-hand circular polarization mode in a space environment under a theoretical environment; solidify the calculated dataset results into the spacecraft equipment;

[0008] S4, matching the frequency-standing wave ratio dataset A of the n circularly polarized antennas in the left-hand circularly polarized transmission mode obtained in step S1 with the dataset C in step S3, and obtaining the electron density value corresponding to the best matching row is the real-time space environment electron density N l,1 -N l,n The frequency-standing wave ratio data set B in the right-hand circular polarization transmission mode obtained in step S2 is matched with the data set D in step S3, and the electron density value corresponding to the row that best matches is the real-time space environment electron density N r,1 -N r,n ;

[0009] S5, due to the existence of measurement errors and other factors, there is a certain error between the perceived electron density and the actual electron density. l,1 -N l,n and N r,1 -N r,n Take the weighted average to get the electron density N, which is the high-precision inversion result closest to the real electron density. N can be adjusted according to the working condition of the antenna. l,1 -N l,n and N r,1 -N r,n The weights are adjusted in real time to achieve more accurate inversion results.

[0010] The beneficial effects of the present invention are:

[0011] (1) The present invention can achieve high-precision perception without the need for accumulation, with a fast perception speed and is basically unaffected by changes in the spatial environment.

[0012] (2) The accuracy of the present invention is superior to that of existing passive sensing methods, and its in-situ sensing function can also complement the sensing range of existing active sensing methods.

[0013] (3) The present invention utilizes the antenna and monitoring circuit of the spacecraft to perform high-precision perception of the space environment, with low power consumption and high precision, which can save space resources and power consumption resources of on-board equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic diagram of high-precision in-situ space environment perception based on spaceborne circularly polarized antennas;

[0015] Figure 2 It is a flow chart of the present invention. DETAILED DESCRIPTION

[0016] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. The specific embodiments described herein are only used to explain the technical solution of the present invention and are not intended to limit the present invention.

[0017] The satellite-borne antenna in the embodiment of the present invention refers to the circularly polarized antenna carried by the satellite, which can transmit left-hand circularly polarized electromagnetic waves and right-hand circularly polarized electromagnetic waves. Figure 1 shown.

[0018] In the embodiment of the present invention, when the satellite antenna operates in the left-hand circular polarization mode, the relative dielectric constant ε of the space plasma is l for:

[0019]

[0020] When the satellite antenna operates in right-hand circular polarization mode, the relative dielectric constant ε of the space plasma is r for:

[0021]

[0022] Where ω is the angular frequency of the emitted electromagnetic wave; ω ce is the angular frequency of the electron spin; ω p is the plasma angular frequency; ν is the electron collision frequency. Among them:

[0023] ω=2πf (3)

[0024]

[0025] Where N is the electron density of the space environment, f is the antenna transmission frequency, m is the electron mass, ε0 is the dielectric constant in a vacuum, and e is the electron charge. The above formula (1-4) can be used to calculate the corresponding relationship between the space environment electron density N, the antenna transmission frequency f, and the space environment dielectric constant. It is obvious that under the same space environment electron density, the space environment dielectric constant is different when the antenna operates in left-hand circular polarization mode and when it operates in right-hand circular polarization mode. Therefore, the antenna's standing wave ratio in these two conditions will also be different.

[0026] The satellite is equipped with n (n≥1) antennas, with m electron densities preset. The antenna and space environment coupling model is used to calculate the electron density N i Antenna operating frequency f under (i=1,2,...m) i (i=1,2,...k) and return loss V ij The corresponding data of (i=1,2,...,k)(j=1,2,...,k). The final obtained benchmark data set C in the left-hand circular polarization mode of the i-th (i=1,2,...,n) satellite antenna i as follows:

[0027]

[0028] The final benchmark dataset D in right-hand circular polarization mode i as follows:

[0029]

[0030] The spacecraft is in orbit and operates in space plasma. When the antenna is working, it sweeps and transmits k frequency points with a frequency of f in the working bandwidth in a left-hand circular polarization mode. i (i=1,2,...k) electromagnetic waves, and then, the same frequency electromagnetic waves are swept in right-hand circular polarization mode. Because this process is extremely short, the surrounding space environment does not change during the process. The antenna system monitors the antenna's standing wave ratio when the antenna operates at each frequency point of electromagnetic waves. This monitoring function is built into the aircraft antenna system. The corresponding data set A is finally monitored in left-hand circular polarization mode. i for:

[0031]

[0032] Corresponding data set B monitored in right-hand circular polarization mode i for:

[0033]

[0034] Dataset A i With dataset C i Compare with dataset B i With dataset D i Compare and find the electron density N that best matches the two modes of the i-th (i=1,2,...,n) satellite antenna i,l and N i,r That is the electron density of the perceived space environment.

[0035] Due to various factors such as measurement errors, the electron density N perceived in the two modes may actually be i,l and N i,rThere are errors between the two inverted electron density values and the true value.

[0036]

[0037] The final electron density N is the space environment electron density closest to the true value inverted by the nth satellite antenna, where w i,l and w i,r is the weight of the left-hand circular polarization sensing result and the right-hand circular polarization sensing result of the i-th antenna.

[0038] The electron density data of the space environment inverted using the above method uses n antennas, each using both left-hand and right-hand circular polarization modes, to simultaneously sense the electron density of the same space environment 2n times. Finally, a weighted average is taken, resulting in extremely high sensing accuracy. Because it does not require multiple accumulations, it also has extremely fast sensing speed.

[0039] The present invention provides a high-precision and rapid space environment perception method based on satellite-borne antennas, such as Figure 2 Shown, including:

[0040] S1, when the satellite is in a space environment, feed its n (n ≥ 1) circularly polarized antennas to emit left-hand circularly polarized electromagnetic waves and step-change their transmission frequency; at this time, record the antenna standing wave ratio parameters monitored by the antenna circuit to obtain the frequency-standing wave ratio dataset A of the n circularly polarized antennas in the left-hand circularly polarized transmission mode; among them, the frequency-standing wave ratio dataset of the i-th (i = 1, 2, ..., n) circularly polarized antenna in the left-hand circularly polarized transmission mode is A i ;

[0041] In S2, when the satellite is in a space environment, its n circularly polarized antennas are fed with power. The feeding phase is opposite to that in S1, causing them to emit right-hand circularly polarized electromagnetic waves and step-change their transmission frequency. At this time, the standing wave ratio parameters of the antenna monitored by the antenna circuit are recorded to obtain a frequency-standing wave ratio dataset B of n (n ≥ 1) circularly polarized antennas in the right-hand circularly polarized transmission mode. Among them, the frequency-standing wave ratio dataset of the i-th circularly polarized antenna in the right-hand circularly polarized transmission mode is B i ;

[0042] S3, using the antenna-plasma coupling model, calculate the electron density-frequency-standing wave ratio parameter dataset C of the i-th circularly polarized antenna in the left-hand circularly polarized mode in a space environment under theoretical conditions. i The electron density-frequency-standing wave ratio parameter dataset D of the antenna in right-hand circular polarization mode i, obtain the electron density-frequency-standing wave ratio parameter dataset C of n circularly polarized antennas in left-hand circular polarization mode and the electron density-frequency-standing wave ratio parameter dataset D of the antennas in right-hand circular polarization mode in a space environment under a theoretical environment; solidify the calculated dataset results into the spacecraft equipment;

[0043] S4, matching the frequency-standing wave ratio dataset A of the n circularly polarized antennas in the left-hand circularly polarized transmission mode obtained in step S1 with the dataset C in step S3, and obtaining the electron density value corresponding to the best matching row is the real-time space environment electron density N l,1 -N l,n The frequency-standing wave ratio data set B in the right-hand circular polarization transmission mode obtained in step S2 is matched with the data set D in step S3, and the electron density value corresponding to the row that best matches is the real-time space environment electron density N r,1 -N r,n ;

[0044] S5, due to the existence of measurement errors and other factors, there is a certain error between the perceived electron density and the actual electron density. l,1 -N l,n and N r,1 -N r,n Take the weighted average to get the electron density N, which is the high-precision inversion result closest to the real electron density. N can be adjusted according to the working conditions of each antenna. l,1 -N l,n and N r,1 -N r,n The weights are adjusted in real time to achieve more accurate inversion results.

[0045] The above description merely represents the preferred embodiments of the present invention, and while the description is relatively detailed and specific, it should not be construed as limiting the scope of the present invention. It should be noted that a person skilled in the art would be able to make various modifications, improvements, and substitutions without departing from the spirit of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be determined by the appended claims.

Claims

1. A high-precision and rapid space environment perception method based on a spaceborne antenna, characterized by: The steps include: S1, when the satellite is in the space environment, The circularly polarized antenna is fed to emit left-hand circularly polarized electromagnetic waves and its emission frequency is changed step by step; Record the standing wave ratio parameters of the antenna monitored by the antenna circuit and obtain Frequency-standing wave ratio dataset of a circularly polarized antenna in left-hand circularly polarized transmission mode A , among which, The frequency-standing wave ratio dataset of the root circularly polarized antenna in the left-hand circularly polarized transmission mode is , ; S2, when the satellite is in the space environment, The circularly polarized antenna is fed with power, and the feeding phase is opposite to that in S1, so that it emits right-hand circularly polarized electromagnetic waves and changes its transmission frequency in steps; the standing wave ratio parameters of the antenna monitored by the antenna circuit are recorded to obtain Frequency-standing wave ratio dataset of the root circularly polarized antenna in right-hand circularly polarized transmission mode B Among them, The frequency-standing wave ratio dataset of the root circularly polarized antenna in the right-hand circularly polarized transmission mode is ; S3, using the antenna and plasma coupling model, calculates the first Electron density-frequency-standing wave ratio parameter dataset of the root circularly polarized antenna in left-hand circularly polarized mode The electron density-frequency-standing wave ratio parameter dataset of the antenna in right-hand circular polarization mode , we get the spatial environment in the theoretical environment Electron density-frequency-standing wave ratio parameter dataset of the root circularly polarized antenna in left-hand circularly polarized mode C The electron density-frequency-standing wave ratio parameter dataset of the antenna in right-hand circular polarization mode D ; Solidify the calculated data set results into the spacecraft equipment; S4, the result obtained in step S1 Frequency-standing wave ratio dataset of a circularly polarized antenna in left-hand circularly polarized transmission mode A Match it with the data set C in step S3, and the electron density value corresponding to the best matching row is the real-time space environment electron density. ; The frequency-standing wave ratio data set under the right-hand circular polarization transmission mode obtained in step S2 B The dataset in step S3 D Matching is performed, and the electron density value corresponding to the most matching row is the real-time space environment electron density. ; S5, yes and Take the weighted average to get the electron density This is the high-precision inversion result that is closest to the actual electron density.

2. The high-precision and rapid space environment perception method based on a satellite-borne antenna according to claim 1, characterized in that: In the step S5, the antenna is and The weights are adjusted in real time.

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