Satellite coverage and satellite disturbance early warning method, system, device and storage medium

Abstract

The present invention proposes a satellite coverage and satellite disturbance early warning method, system, equipment and storage medium. The method includes: classifying satellites according to Kepler's three laws, analyzing satellite logs to obtain satellite coverage, and sorting the coverage of various types of satellites; traversing various types of satellites in turn according to the sorting, measuring the probability that all satellite signal gains reach 3dB, adjusting the satellite orbital level with a probability not higher than the threshold, and keeping other satellite orbital levels unchanged, so that the probability that all satellite signal gains reach 3dB is higher than the threshold, and a new satellite coverage sorting is obtained. According to the sorting, the normal motion orbits of various types of satellites under ideal conditions are obtained, the aerial base station transmits a detection signal, and the pilot satellite receives the detection signal and calculates the difference between the received power and the transmitted power, and considers the attenuation caused by weather, and judges the probability of satellite disturbance according to the difference power. If the probability is higher than the threshold, an alarm is triggered. The present invention makes the alarm triggering after data analysis at the level of satellite disturbance causes more scientific and efficient.

Description

Technical Field

[0001] The present invention relates to the field of satellite mobile communications, and in particular to a satellite coverage and satellite disturbance early warning method, system, equipment and storage medium. Background Art

[0002] Satellites orbit the earth, and their trajectory is called a satellite orbit. Regardless of the purpose of satellites, they all have one thing in common, that is, their orbital positions are all in a plane passing through the center of gravity of the earth. The orbital plane where the satellite moves is called the orbital plane. If the orbital plane of the satellite is in the equatorial plane, this orbit is called an equatorial orbit; if there is a certain angle between the orbital plane and the equatorial plane, it is called an inclined orbit, and this angle is called the orbital inclination; the orbit in which the orbital plane passes through the two poles of the earth is called a polar orbit. The time required for a satellite to orbit the earth is the satellite operation cycle, and the operation cycle of a geostationary satellite is 23h56min4.09s. Which satellite orbit a satellite mobile communication system uses depends on factors such as the system's coverage area, service business, management method and investment intensity. It is a problem to be solved in the feasibility study and demonstration stage of the system.

[0003] The causes of disturbances of artificial satellites are as follows:

[0004] The influence of the gravity of the sun and the moon. For low-altitude satellites, the influence of the earth's gravity is absolutely dominant, and the influence of the sun and the moon's gravity can be ignored. For satellites at higher altitudes, although the earth's gravity is still the main influencing factor, the gravity of the sun and the moon also have a certain influence. Taking geostationary satellites as an example, the gravitational forces of the sun and the moon on satellites are 137 and 1 / 6800 of the earth's gravity respectively. These gravitational forces cause the satellite's orbital position vector to swing slightly every day, and also cause cumulative changes in the orbital inclination, with an average deviation rate of about 0.55 years. If no correction is made, then within 26.6 years, the orbital inclination deviation angle will change from 0° to 14.63°, and then decrease to 0° after the same period of time. From the perspective of the earth, this disturbance will cause the geostationary satellite to slowly "drift" in the north-south direction.

[0005] Since the earth is not an ideal standard sphere, but slightly ellipsoidal (with a little bulge at the equator), and the surface of the earth is uneven, the gravity at the same height around the earth is not constant. Even in the geostationary orbit, the gravity still has slight fluctuations. Obviously, the unevenness of the gravity will cause the instantaneous velocity of the satellite to deviate from the theoretical value, thus generating disturbances in the orbital plane. For a geostationary satellite, the fluctuation of the instantaneous velocity will cause it to slowly "drift" in the east-west direction.

[0006] The influence of the uneven earth's gravitational field. Ultra-high-altitude satellites are in a highly vacuum environment, so the influence of atmospheric drag on them can be ignored. However, atmospheric drag may have a certain impact on low-altitude satellites, which will cause the mechanical properties of the satellite to be damaged, thereby gradually reducing the orbit. For example, the elliptical orbit satellite is affected by atmospheric drag, and its perigee and apogee altitudes will gradually decrease.

[0007] The influence of the drag of the earth's atmosphere. For general satellites, the influence of solar radiation pressure is not considered, but for geostationary satellites with large surface areas (such as those with large solar panels) and high positioning accuracy requirements, the position drift of the geostationary satellite in the east-west direction caused by solar radiation pressure must be considered.

[0008] The influence of solar radiation pressure. Disturbance is very unfavorable to the maintenance of the fixed position of the geostationary satellite. Therefore, in the geostationary satellite communication system, position keeping technology must be adopted to overcome the influence of disturbance and keep the satellite position error within the allowable range. Summary of the invention

[0009] In view of the deficiencies in the prior art, the present invention provides a satellite coverage and satellite disturbance early warning method, system, device and storage medium.

[0010] To achieve the above object, the present invention adopts the following technical solutions:

[0011] An aerial base station satellite coverage and satellite disturbance early warning method comprises the following steps:

[0012] Satellites are classified according to Kepler's three laws, log data of each type of satellite is collected and analyzed to obtain satellite coverage, and the coverage of each type of satellite is ranked;

[0013] According to the coverage range of satellites, each type of satellite is traversed in turn, the probability of signal gain of all types of satellites reaching 3dB is measured, and the orbital level of satellites with probability not higher than the threshold is adjusted, and the orbital level of satellites with probability higher than the threshold remains unchanged, so that the probability of signal gain of all satellites reaching 3dB is higher than the threshold or the number of moving levels has reached the limit value, and a new coverage range ranking of each type of satellite is obtained. The coverage range ranking of satellites is consistent with the satellite orbit height ranking;

[0014] The normal motion orbits of various types of satellites under ideal conditions are obtained by sorting the satellite orbit heights. The terahertz detection signal is transmitted through the aerial base station. After the pilot satellite receives the terahertz detection signal, the difference power between the received power and the transmitted power is calculated. The attenuation caused by weather conditions is taken into account when calculating the difference power between the received power and the transmitted power. The probability of the actual motion orbit of each type of satellite deviating from the normal motion orbit is judged based on the difference power. If the probability of the actual motion orbit deviating from the normal motion orbit is higher than the threshold, an alarm is triggered.

[0015] To optimize the above technical solutions, the specific measures taken also include:

[0016] Furthermore, the specific process of obtaining the new coverage range ranking of each type of satellite is as follows:

[0017] Sort the satellites by their coverage, starting with the satellite with the farthest coverage, and traverse each type of satellite in turn, performing the following processing on each type of satellite in turn:

[0018] For the satellite ranked at the nth position, 1≤n≤N, N represents the total number of types, firstly, signal enhancement is performed, and the probability that the signal gain of the satellite of this type reaches 3dB is predicted by using the wireless signal enhancement prediction model; if the probability that the signal gain reaches 3dB is higher than the threshold, the coverage range of the satellite of this type is correct and the orbital position remains unchanged, otherwise, the satellite of this type is moved down one orbit layer, and the above process is repeated in the new orbital layer until the probability that the signal gain of the satellite of this type reaches 3dB is higher than the threshold or the number of layers moved has reached the limit value;

[0019] Complete the processing of all types of satellites from 1 to N and obtain the correct coverage range ranking of each type of satellite.

[0020] Furthermore, the wireless signal enhancement prediction model is established based on the Markov chain, and the formula for predicting the signal gain of the satellite is:

[0021] X(k+1)=X(k)×P

[0022] Where X(k) represents the state vector of the predicted object at time k, P represents the one-step transition probability matrix, and X(k+1) represents the state vector of the predicted object at time k+1.

[0023] Furthermore, the weather condition is a rainy climate, and the attenuation rate of the terahertz detection signal is calculated using the following formula:

[0024] YR=KR A

[0025] In the formula, γ Ris the attenuation rate of the terahertz detection signal caused by rainfall, K is the parameter of horizontal polarization, A is the parameter of vertical polarization, and R is the precipitation.

[0026] Furthermore, the weather condition is a foggy climate, and the attenuation rate of the terahertz detection signal is calculated using the following formula:

[0027]

[0028] In the formula, γ c&f It represents the attenuation rate of the terahertz detection signal caused by the cloud climate, in dB / km, f is the operating frequency, V m For visibility.

[0029] Furthermore, the weather condition is snowy, and the attenuation rate of the terahertz detection signal is calculated using the following formula:

[0030] γ s =7.47×10 -5 f×I(1+5.77×10 -5 f 3 I0.6)

[0031] In the formula, γ s It represents the attenuation rate of the terahertz detection signal caused by snowfall climate, f is the operating frequency, and I is the snowfall intensity.

[0032] Furthermore, the weather condition is a dusty climate, and the attenuation rate of the terahertz detection signal is calculated based on the change in frequency.

[0033] The present invention also proposes an aerial base station satellite coverage and satellite disturbance early warning system, comprising:

[0034] The classification and sorting module is used to classify satellites according to Kepler's three laws, collect log data of various types of satellites and analyze them to obtain satellite coverage, and sort the coverage of various types of satellites;

[0035] The iterative calculation module is used to sort the satellites according to their coverage range, traverse each type of satellites in turn, measure the probability that the signal gain of all types of satellites reaches 3dB, adjust the orbital level of the satellites whose probability is not higher than the threshold, and keep the orbital level of the satellites whose probability is higher than the threshold unchanged, so that the probability that the signal gain of all satellites reaches 3dB is higher than the threshold or the number of moving levels has reached the limit value, and obtain the new coverage range sorting of each type of satellites. The satellite coverage range sorting is consistent with the satellite orbit height sorting; specifically:

[0036] Sort the satellites by their coverage, starting with the satellite with the farthest coverage, and traverse each type of satellite in turn, performing the following processing on each type of satellite in turn:

[0037] For the satellite ranked at the nth position, 1≤n≤N, N represents the total number of types, firstly, signal enhancement is performed, and the probability that the signal gain of the satellite of this type reaches 3dB is predicted by using the wireless signal enhancement prediction model; if the probability that the signal gain reaches 3dB is higher than the threshold, the coverage range of the satellite of this type is correct and the orbital position remains unchanged, otherwise, the satellite of this type is moved down one orbit layer, and the above process is repeated in the new orbital layer until the probability that the signal gain of the satellite of this type reaches 3dB is higher than the threshold or the number of layers moved has reached the limit value;

[0038] Complete the processing of all types of satellites from 1 to N and obtain the correct coverage range ranking of each type of satellite;

[0039] The alarm trigger module is used to obtain the normal motion orbits of various types of satellites under ideal conditions according to the satellite orbit height sorting, and transmit the terahertz detection signal through the aerial base station. After the pilot satellite receives the terahertz detection signal, it calculates the difference power between the received power and the transmitted power. When calculating the difference power between the received power and the transmitted power, the attenuation caused by weather conditions is considered. The probability of the actual motion orbit of each type of satellite deviating from the normal motion orbit is judged according to the difference power. If the probability of the actual motion orbit deviating from the normal motion orbit is higher than the threshold, an alarm is triggered.

[0040] The present invention also proposes an electronic device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the above-mentioned aerial base station satellite coverage and satellite disturbance warning method is implemented.

[0041] The present invention also proposes a computer-readable storage medium storing a computer program, wherein the computer program enables a computer to execute the above-mentioned aerial base station satellite coverage and satellite disturbance early warning method.

[0042] The beneficial effects of the present invention are:

[0043] The present invention refines and optimizes the classification of satellite orbits based on Kepler's three laws. The terahertz detection signal is transmitted through the aerial base station, and the pilot satellite calculates the difference power after receiving it. Thus, the probability of satellite disturbance is predicted. Innovatively, corresponding thresholds are set for different natural scenes where terahertz and other radio waves are absorbed by the natural environment, so that the interference triggering is more accurate. And with the widespread application of terahertz in 6G, the triggering of this threshold makes the existing alarm triggering after data analysis at the cause level of satellite disturbance more scientific and efficient. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 This is a schematic diagram of the satellite orbit altitude division;

[0045] Figure 2Flowchart for calculating correct satellite coverage;

[0046] Figure 3 This is a flow chart of the satellite disturbance prediction method. DETAILED DESCRIPTION

[0047] The present invention will now be described in further detail with reference to the accompanying drawings.

[0048] In one embodiment, the present invention proposes a method for predicting satellite coverage and satellite disturbance of an aerial base station.

[0049] According to the different heights of satellite orbits from the ground, satellite orbits can be divided into geostationary orbits (GEO), medium orbits (MEO), low orbits (LEO) and digh elliptical orbits (H). The division method is based on the high-energy radiation belt extending from the equator of the earth to the 40-50 degrees north and south latitude. Figure 1 As shown. Figure 1 The two radiation belts in the belt are the Van Allen Belt. In January 1958, the particle counter of Explorer 1 found incredible radiation intensity in the high altitude area above 1000km. After the exploration of Explorer 3 and 4, the existence of this radiation belt was finally confirmed and named after its discoverer. The Van Allen Belt is the earth's magnetic field from the solar wind. These high-energy particles will hit the satellite and produce X-rays and additional high-energy particles. High-energy particles have the ability to penetrate electrons. It is unrealistic to protect the radiation belt. Satellites can only exist in this area for a few years. Therefore, it is generally believed that the height H of the inner Van Allen belt is 1500km~5000km. When it is 3700km, the concentration of high-energy particles is the largest; the height H of the outer Van Allen belt is 12000km~19000km, and when H is 18500km, the concentration of high-energy particles is the largest. In other words, the areas below 1500km, 5000km~12000km and above 19000km are safe, which divides the corresponding low, medium and high orbits. Medium Earth Orbit (MEO) satellites operate in orbits between the inner and outer Van Allen belts. Although MEO satellites are exposed to radiation intensity about twice that of GEO satellites, they can be protected by electrical shielding measures and can use radiation-proof electronic components.

[0050] In addition, in areas near the Earth's South and North Poles, it is difficult to use geostationary satellite communications due to the high latitudes, so a long elliptical orbit (HEO) satellite with a certain inclination can be used. For example, Russia's "Lightning" satellite uses a long elliptical orbit with an apogee over the northern hemisphere, a period of 12 hours, and an inclination of 65°. Its apogee is about 40,000 km from the Earth's surface, and its perigee is about 500 km from the Earth's surface.

[0051] The method proposed by the present invention comprises:

[0052] According to Kepler's three laws, satellites are classified, log data of each type of satellite is collected and analyzed to obtain satellite coverage, and the coverage of each type of satellite is sorted. The contents of Kepler's three laws are as follows:

[0053] First law: The orbit of a satellite is an ellipse with one focus at the Earth's center of mass.

[0054] This law shows that in the gravitational field centered on the Earth's center of mass, the orbital plane of a satellite orbiting the Earth is an elliptical plane passing through the Earth's center of mass. This elliptical plane is called a Kepler ellipse, and its shape and size remain unchanged. In the elliptical plane orbit, the point farthest from the Earth's center is called the apogee, and the point closest to the Earth's center is called the perigee. Their positions in inertial space are also fixed. The orbital equation of a satellite orbiting the Earth's center is as follows.

[0055]

[0056] In (1), r is the distance between the satellite and the center of the Earth; a is the semi-major axis of the orbital ellipse; e is the eccentricity of the orbital ellipse; and V is the anomaly angle, which describes the position of the satellite in the orbit relative to the perigee at any time.

[0057] Second law: The geocentric radius of a satellite, that is, the distance vector between the Earth's center of mass and the satellite's center of mass, covers the same area in the same amount of time.

[0058] The third law: The ratio of the square of the satellite's period to the cube of the semi-major axis of the orbital ellipse is a constant.

[0059] The mathematical expression of this law is as follows.

[0060]

[0061] In (Equation 2), T is the period of satellite motion, that is, the time required for the satellite to orbit the earth; G is the gravitational constant; and M is the mass of the central celestial body (the earth).

[0062] Assume that the average angular velocity of the satellite is Then from (2) we can get the following equation.

[0063]

[0064] From this we can see that once the semi-major axis a of the satellite's elliptical orbit is determined, the average angular velocity n of the satellite's motion can be determined.

[0065] Newton's law of universal gravitation and Kepler's three laws are the theoretical basis for calculating satellite orbits, from which the orbital parameters of satellite motion can be derived.

[0066] The classification table of satellites according to coverage range is shown in Table 1. The higher the altitude, the wider the signal coverage range, but the degree of signal interference is also higher.

[0067] Table 1 Classification of satellite orbits

[0068]

[0069]

[0070] UAV: Unmanned Aerial Vehicle.

[0071] HAPS: High Altitude Platform Station (HAPS) communication system provides telecommunication services by placing wireless base stations on aircraft that stay at high altitudes for a long time. It is considered to be a broadband wireless access method with good potential application value after 2010. If the altitude is 20km, the ground coverage radius of the communication area can be about 500km.

[0072] VLEO: Constellation.

[0073] The approximate coverage range of an artificial satellite is determined by Table 1. Secondly, the gain value of the farthest range covered by the artificial satellite at the current altitude in the historical data is analyzed by taking the interference gain industry standard 3dB as the threshold, and the signal exceeding 3db is judged as high quality (3db and above is good signal, 1-3db is average signal, and below 1db is poor signal).

[0074] Then, the constructed wireless signal enhancement prediction model is used to predict and analyze whether the current real-time data reaches the probability value of 3dB. If the probability value exceeds 50%, the prediction authenticity is high.

[0075] According to the coverage range of satellites, each type of satellite is traversed in turn, the probability of signal gain reaching 3dB for all types of satellites is measured, and the orbital level of satellites with probability not higher than the threshold is adjusted, and the orbital level of satellites with probability higher than the threshold remains unchanged, so that the probability of signal gain reaching 3dB for all satellites is higher than the threshold or the number of moving levels has reached the limit value, and a new coverage range ranking of each type of satellite is obtained. The satellite coverage range ranking is consistent with the satellite orbit height ranking.

[0076] The specific process of obtaining the new coverage range ranking of each type of satellite is as follows:

[0077] Sort the satellites by their coverage, starting with the satellite with the farthest coverage, and traverse each type of satellite in turn, performing the following processing on each type of satellite in turn:

[0078] For the satellite ranked at the nth position, 1≤n≤N, N represents the total number of types, firstly, signal enhancement is performed, and the probability that the signal gain of the satellite of this type reaches 3dB is predicted by using the wireless signal enhancement prediction model; if the probability that the signal gain reaches 3dB is higher than the threshold, the coverage range of the satellite of this type is correct and the orbital position remains unchanged, otherwise, the satellite of this type is moved down one orbit layer, and the above process is repeated in the new orbital layer until the probability that the signal gain of the satellite of this type reaches 3dB is higher than the threshold or the number of layers moved has reached the limit value;

[0079] Complete the processing of all types of satellites from 1 to N and obtain the correct coverage range ranking of each type of satellite.

[0080] An example of using the wireless signal enhancement prediction model to predict the probability of the signal gain of this type of satellite reaching 3dB is given as follows: the current signal strength is 3db, and the predicted probability of the next weakening is 60%. The short-term prediction probability values ​​are obtained by using the signal intervals of the most recent 10 trends in the history of satellites of the same altitude (3db and above means good signal, 1-3db means average signal, and below 1db means poor signal). Good signal accounts for 4 out of 10 times, with a probability of 40%, average signal is 2 times, with a probability of 20%, and poor signal is 4 times, with a probability of 40%.

[0081] Finally, the short-term prediction probability value and the prediction probability of the wireless signal enhancement prediction model have an error within 10%, for example: 45% and 48%. The satellite signal coverage accuracy in the table that is close to reality is real and valid. Otherwise, it is inaccurate and the artificial satellite needs to be operated to re-measure the coverage and update the table.

[0082] The wireless signal enhancement prediction model is established based on the Markov chain, and the formula for predicting the signal gain of the satellite is:

[0083] X(k+1)=X(k)×P

[0084] Wherein, X(k) represents the state vector of the predicted object at time t=k, P represents the one-step transition probability matrix, and X(k+1) represents the state vector of the predicted object at time t=k+1.

[0085] A rectangular set is generated by accessing the wireless data stored in the empty constellation. The rectangular set includes: user terminal UE, satellite node name, and signal gain value. The signal gain value can be used to compare the previous gain level. This gain db-last gain db = this signal gain, and the signal strength of this signal can be indirectly obtained by combining the propagation delay.

[0086] For example, the probability of wireless signal gain (db) in the previous period is [0.3, 0.7], the probability of gain transfer (db) when the wireless signal becomes stronger in the previous period is [0.6, 0.4], and the probability of gain transfer (db) when the wireless signal becomes weaker in the current period is [0.3, 0.7].

[0087] Through the model calculation, we can get: X(k+1)=X(k)×P

[0088] The probability of gain transfer when the wireless signal becomes stronger in the next period is:

[0089] 0.3×0.6+0.3×0.7=0.39

[0090] The probability of gain transfer when the wireless signal becomes weak in the next period:

[0091] 0.3×0.4+0.7×0.7=0.61

[0092] Finally, the signal gain transfer probability in the next time period [0.39 0.61] is calculated by combining the predicted calculation results of the wireless signal enhancement prediction model with the current gain (db), according to the industry's common 3dB rule: every increase or decrease of 3dB means doubling or halving the power.

[0093]

[0094]

[0095] +3dB = 2*power;

[0096] +6dB = 4*power.

[0097] According to the satellite orbit height sorting, the normal orbit of each type of satellite under ideal conditions is obtained. At the same time, the orbit satisfies Kepler's three laws. However, due to the influence of some minor factors, the actual orbit of the satellite often deviates from the ideal orbit determined by Kepler's three laws. This phenomenon is called perturbation.

[0098] A terahertz detection signal is transmitted through an aerial base station. After receiving the detection signal, the pilot satellite calculates the difference power between the received power and the transmitted power. The attenuation caused by weather conditions is taken into account when calculating the difference power between the received power and the transmitted power. The probability of the actual motion orbit of each type of satellite deviating from the normal motion orbit is judged based on the difference power. If the probability of the actual motion orbit deviating from the normal motion orbit is higher than a threshold, an alarm is triggered.

[0099] The corresponding thresholds are set for different natural scenes where terahertz and other radio waves are absorbed by the natural environment, making the interference trigger more accurate. With the widespread application of terahertz in 6G, the triggering of this threshold will be more scientific and efficient for the alarm triggering after the data analysis of the existing satellite disturbance causes. The initial coverage value of artificial satellites combined with the probability of satellite disturbances provides an artificial intelligence-based analysis basis for the possible hidden causes of satellite disturbances.

[0100] First, in order to reduce the impact of satellite disturbances on the normal operation of satellite orbits, terahertz detection signal technology is used to deploy terahertz receivers and Beidou receivers on each satellite in the satellite constellation at each altitude of the aerial base station, so that it can continuously navigate 100-500 kilometers ahead of the aerial base station, referred to as: navigation satellite.

[0101] Secondly, terahertz receivers and Beidou receivers are deployed on the pilot satellite. The Beidou receiver receives RDSS short messages to obtain real-time information on whether the pilot satellite is deviating and adjust its course at any time.

[0102] Then, any satellite in the air base station transmits a terahertz signal to the pilot satellite. If the difference between the terahertz signal power received by the pilot satellite and the transmission power is 30%, the current natural environment is not ideal, and the probability of satellite disturbance is 70%. At the same time, if the Beidou navigation satellite indicates a yaw, the satellite disturbance is judged as an alarm. Otherwise, the pilot satellite notifies the artificial earth satellite to correct the yaw.

[0103] The natural environment mainly includes four typical weather conditions (rainwater communication, cloud and fog communication, snowfall communication, and sandstorm climate). (Different natural weather has different calculation formulas).

[0104] 1. The threshold of the attenuation rate of radio waves for rain communication. The setting unit is dB / km. The heavier the rain, the greater the interference. You can customize the weather forecast to be light rain, moderate rain, or heavy rain.

[0105] When radio waves are transmitted in line of sight, in addition to being attenuated in the air, they will also be attenuated by rain. If the radio waves are transmitted in rain, the attenuation rate of the terahertz detection signal is calculated using the following formula:

[0106] YKR A

[0107] In the formula, γ Ris the attenuation rate of the terahertz detection signal caused by rainfall, K is the parameter of horizontal polarization, A is the parameter of vertical polarization, and R is the precipitation.

[0108] 2. Cloud and fog communication radio wave attenuation rate threshold, setting unit: dB / km and GHz 20~500m (visibility)

[0109] The attenuation rate of the terahertz detection signal is calculated using the following formula:

[0110]

[0111] In the formula, γ c&f represents the attenuation rate of the terahertz detection signal caused by the foggy climate, f is the operating frequency, V m For visibility.

[0112] In fact, the visibility regulations are: dense fog, V m <50m; dense fog, 50m <V m <200m; light fog, 200m <V m <500m. The visibility range for the relationship between attenuation rate, frequency and visibility is 20 to 500m.

[0113] The analysis frequency of the atmospheric attenuation rate of the present invention has a value range of 0 to 350 GHz.

[0114] Threshold setting units: dB / km and GHz20~500m (visibility).

[0115] 3. Snowfall communication radio wave attenuation rate threshold, setting unit: Frequencies above 150GHz are greatly affected by the intensity of snowfall, and it is recommended to issue an alarm.

[0116] The attenuation rate of the terahertz detection signal is calculated using the following formula:

[0117] γ s =7.47×10 -5 f×I(1+5.77×10 -5 f 3 I 0.6 )

[0118] In the formula, γ s It represents the attenuation rate of the terahertz detection signal caused by snowfall climate, f is the operating frequency, and I is the snowfall intensity.

[0119] The relationship between attenuation and frequency and snowfall intensity. Among them, frequencies above 150 GHz are greatly affected by snowfall intensity, while frequencies below 150 GHz are relatively less affected by snowfall intensity.

[0120] Threshold setting unit: Frequencies above 150GHz are greatly affected by the intensity of snowfall, and an alarm is recommended.

[0121] 4. The characteristic attenuation rate and attenuation threshold setting of sand and dust climate, the characteristic attenuation rate corresponding to the frequency from 0 to 350GHz and the temperature from 0℃ to 60℃. The characteristic attenuation rate only increases with the increase of frequency and basically does not change with temperature.

[0122] Threshold setting unit: Below 20 GHz, the characteristic attenuation rate increases significantly with increasing frequency. Above 20 GHz, the characteristic attenuation rate increases relatively slowly with increasing frequency.

[0123] In another embodiment, the present invention proposes an aerial base station satellite coverage and satellite disturbance warning system based on the aerial base station satellite coverage and satellite disturbance warning method described in Embodiment 1, comprising:

[0124] The classification and sorting module is used to classify satellites according to Kepler's three laws, collect log data of various types of satellites and analyze them to obtain satellite coverage, and sort the coverage of various types of satellites;

[0125] The iterative calculation module is used to sort the satellites according to their coverage range, traverse each type of satellites in turn, measure the probability that the signal gain of all types of satellites reaches 3dB, adjust the orbital level of the satellites whose probability is not higher than the threshold, and keep the orbital level of the satellites whose probability is higher than the threshold unchanged, so that the probability that the signal gain of all satellites reaches 3dB is higher than the threshold or the number of moving levels has reached the limit value, and obtain the new coverage range sorting of each type of satellites. The satellite coverage range sorting is consistent with the satellite orbit height sorting; specifically:

[0126] Sort the satellites by their coverage, starting with the satellite with the farthest coverage, and traverse each type of satellite in turn, performing the following processing on each type of satellite in turn:

[0127] For the satellite ranked at the nth position, 1≤n≤N, N represents the total number of types, firstly, signal enhancement is performed, and the probability that the signal gain of the satellite of this type reaches 3dB is predicted by using the wireless signal enhancement prediction model; if the probability that the signal gain reaches 3dB is higher than the threshold, the coverage range of the satellite of this type is correct and the orbital position remains unchanged, otherwise, the satellite of this type is moved down one orbit layer, and the above process is repeated in the new orbital layer until the probability that the signal gain of the satellite of this type reaches 3dB is higher than the threshold or the number of layers moved has reached the limit value;

[0128] Complete the processing of all types of satellites from 1 to N and obtain the correct coverage range ranking of each type of satellite;

[0129] The alarm trigger module is used to obtain the normal motion orbits of various types of satellites under ideal conditions according to the satellite orbit height sorting, and transmit the terahertz detection signal through the aerial base station. After the pilot satellite receives the terahertz detection signal, it calculates the difference power between the received power and the transmitted power. When calculating the difference power between the received power and the transmitted power, the attenuation caused by weather conditions is considered. The probability of the actual motion orbit of each type of satellite deviating from the normal motion orbit is judged according to the difference power. If the probability of the actual motion orbit deviating from the normal motion orbit is higher than the threshold, an alarm is triggered.

[0130] In another embodiment, the present invention proposes an electronic device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the aerial base station satellite coverage and satellite disturbance warning method as described in Example 1 is implemented.

[0131] In another embodiment, the present invention proposes a computer-readable storage medium storing a computer program, wherein the computer program enables a computer to execute the aerial base station satellite coverage and satellite disturbance early warning method as described in the first embodiment.

[0132] In the embodiments disclosed in the present application, the computer storage medium can be a tangible medium that can contain or store a program for use by or in conjunction with an instruction execution system, device or equipment. The computer storage medium can include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices or equipment, or any suitable combination of the above. More specific examples of computer storage media can include electrical connections based on one or more lines, portable computer disks, hard disks, random access memories (RAM), read-only memories (ROM), erasable programmable read-only memories (EPROM or flash memory), optical fibers, portable compact disk read-only memories (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination of the above.

[0133] Those of ordinary skill in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed in this application can be implemented in electronic hardware or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.

[0134] The above are only preferred embodiments of the present invention, and the protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention. It should be pointed out that for ordinary technicians in this technical field, some improvements and modifications without departing from the principle of the present invention should be regarded as the protection scope of the present invention.

Claims

1. A method for satellite coverage of aerial base stations and early warning of satellite disturbances, characterized in that: The following steps are involved: Satellites are classified according to Kepler's three laws, log data of each type of satellite is collected and analyzed to obtain satellite coverage, and the coverage of each type of satellite is ranked; According to the coverage range of satellites, each type of satellite is traversed in turn, the probability of signal gain of all types of satellites reaching 3dB is measured, the orbital level of satellites with probability not higher than the threshold is adjusted, and the orbital level of satellites with probability higher than the threshold remains unchanged, so that the probability of signal gain of all satellites reaching 3dB is higher than the threshold or the number of moving levels has reached the limit value, and a new coverage range ranking of each type of satellite is obtained, and the coverage range ranking of satellites is consistent with the satellite orbit height ranking; the specific process of obtaining the new coverage range ranking of each type of satellite is as follows: Sort the satellites by their coverage, starting with the satellite with the farthest coverage, and traverse each type of satellite in turn, performing the following processing on each type of satellite in turn: For the satellite ranked at the nth position, 1≤n≤N, N represents the total number of types, firstly, signal enhancement is performed, and the probability that the signal gain of the satellite of this type reaches 3dB is predicted by using the wireless signal enhancement prediction model; if the probability that the signal gain reaches 3dB is higher than the threshold, the coverage range of the satellite of this type is correct and the orbital position remains unchanged, otherwise, the satellite of this type is moved down one orbit layer, and the above process is repeated in the new orbital layer until the probability that the signal gain of the satellite of this type reaches 3dB is higher than the threshold or the number of layers moved has reached the limit value; Complete the processing of all types of satellites from 1 to N and obtain the correct coverage ranking of each type of satellite; The normal motion orbits of various types of satellites under ideal conditions are obtained according to the satellite orbit altitude sorting, and a terahertz detection signal is transmitted through the aerial base station. After receiving the terahertz detection signal, the pilot satellite calculates the difference power between the received power and the transmitted power. When calculating the difference power between the received power and the transmitted power, the attenuation caused by weather conditions is considered, and the probability of the actual motion orbit of each type of satellite deviating from the normal motion orbit is judged according to the difference power. If the probability of the actual motion orbit deviating from the normal motion orbit is higher than a threshold, an alarm is triggered; the pilot satellite specifically refers to a satellite that guides the heading of the aerial base station, which is used to reduce the impact of satellite disturbances on the operation of the satellite orbit; the terahertz detection signal technology is used to deploy terahertz receivers and Beidou receivers on each satellite in the satellite group at each altitude of the aerial base station, so that the pilot satellite continues to navigate 100-500 kilometers ahead of the aerial base station.

2. The method for satellite coverage and satellite disturbance early warning of an aerial base station according to claim 1, characterized in that: The wireless signal enhancement prediction model is established based on the Markov chain, and the formula for predicting the signal gain of the satellite is: X(k+1)=X(k)×P Where X(k) represents the state vector of the predicted object at time k, P represents the one-step transition probability matrix, and X(k+1) represents the state vector of the predicted object at time k+1.

3. The method for satellite coverage and satellite disturbance early warning of an aerial base station according to claim 1, characterized in that: The weather condition is a rainy climate, and the attenuation rate of the terahertz detection signal is calculated using the following formula: γ R =KR A In the formula, γ R is the attenuation rate of the terahertz detection signal caused by rainfall, K is the parameter of horizontal polarization, A is the parameter of vertical polarization, and R is the precipitation.

4. The method for satellite coverage and satellite disturbance early warning of an aerial base station according to claim 1, characterized in that: The weather condition is a foggy climate, and the attenuation rate of the terahertz detection signal is calculated using the following formula: In the formula, γ c&f It represents the attenuation rate of the terahertz detection signal caused by the cloud climate, in dB / km, f is the operating frequency, V m For visibility.

5. The method for satellite coverage and satellite disturbance early warning of an aerial base station according to claim 1, characterized in that: The weather condition is snowy, and the attenuation rate of the terahertz detection signal is calculated using the following formula: c s =7.47×10 -5 f×I(1+5.77×10 -5 f 3 I 0.6 ) In the formula, γ s It represents the attenuation rate of the terahertz detection signal caused by snowfall climate, f is the operating frequency, and I is the snowfall intensity.

6. The method for satellite coverage and satellite disturbance early warning of an aerial base station according to claim 1, characterized in that: The weather condition is a dusty climate, and the attenuation rate of the terahertz detection signal is calculated based on the change in frequency.

7. An aerial base station satellite coverage and satellite disturbance early warning system, characterized in that: include: The classification and sorting module is used to classify satellites according to Kepler's three laws, collect log data of various types of satellites and analyze them to obtain satellite coverage, and sort the coverage of various types of satellites; The iterative calculation module is used to sort the satellites according to their coverage range, traverse each type of satellites in turn, measure the probability that the signal gain of all types of satellites reaches 3dB, adjust the orbital level of the satellites whose probability is not higher than the threshold, and keep the orbital level of the satellites whose probability is higher than the threshold unchanged, so that the probability that the signal gain of all satellites reaches 3dB is higher than the threshold or the number of moving levels has reached the limit value, and obtain the new coverage range sorting of each type of satellites. The satellite coverage range sorting is consistent with the satellite orbit height sorting; specifically: Sort the satellites by their coverage, starting with the satellite with the farthest coverage, and traverse each type of satellite in turn, performing the following processing on each type of satellite in turn: For the satellite ranked at the nth position, 1≤n≤N, N represents the total number of types, firstly, signal enhancement is performed, and the probability that the signal gain of the satellite of this type reaches 3dB is predicted by using the wireless signal enhancement prediction model; if the probability that the signal gain reaches 3dB is higher than the threshold, the coverage range of the satellite of this type is correct and the orbital position remains unchanged, otherwise, the satellite of this type is moved down one orbit layer, and the above process is repeated in the new orbital layer until the probability that the signal gain of the satellite of this type reaches 3dB is higher than the threshold or the number of layers moved has reached the limit value; Complete the processing of all types of satellites from 1 to N and obtain the correct coverage ranking of each type of satellite; The alarm trigger module is used to obtain the normal motion orbits of various types of satellites under ideal conditions according to the satellite orbit altitude sorting, and transmit terahertz detection signals through the aerial base station. After the pilot satellite receives the terahertz detection signal, it calculates the difference power between the received power and the transmitted power. When calculating the difference power between the received power and the transmitted power, the attenuation caused by weather conditions is considered, and the probability of the actual motion orbit of each type of satellite deviating from the normal motion orbit is judged according to the difference power. If the probability of the actual motion orbit deviating from the normal motion orbit is higher than a threshold, an alarm is triggered; the pilot satellite specifically refers to a satellite that guides the heading of the aerial base station, which is used to reduce the impact of satellite disturbances on the operation of the satellite orbit; the terahertz detection signal technology is used to deploy terahertz receivers and Beidou receivers on each satellite in the satellite group at each altitude of the aerial base station, so that the pilot satellite continues to navigate 100-500 kilometers ahead of the aerial base station.

8. An electronic device, characterized in that: include: A memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the method for satellite coverage and satellite disturbance early warning of an aerial base station as described in any one of claims 1 to 6 is implemented.

9. A computer-readable storage medium, characterized in that: A computer program is stored, and the computer program enables the computer to execute the aerial base station satellite coverage and satellite disturbance early warning method as described in any one of claims 1-6.

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