Satellite link adjusting method in dynamic scene and electronic equipment

Abstract

The invention provides a method for adjusting a satellite link in a dynamic scene and electronic equipment. According to parameter data, monitored in real time in a dynamic scene, of a communication terminal and a satellite link, atmospheric environment data and position attitude information of a communication terminal carrier, various attenuation information of a space channel, an antenna-to-satellite scanning angle and an antenna gain value are determined, and various attenuation functions in a preset time period are further determined. And then a link quality change trend function is obtained after weighted summation according to the attenuation functions, so that a link quality change trend value, determined according to the link quality change trend function, at the current moment is compared with a first threshold value, and if the value is greater than the first threshold value, it is proved that the satellite link quality has the risk that communication cannot be carried out; the most appropriate target adjustment mode needs to be determined according to the condition of the current satellite link, and adjustment is performed according to the target adjustment mode before the quality of the satellite link is reduced, so that the continuous stability and reliability of the satellite link are ensured.

Description

Technical Field

[0001] The present application relates to the field of satellite communication technology, and in particular to a satellite link adjustment method and electronic equipment in a dynamic scenario. Background Art

[0002] With the rapid development of satellite communication technology, satellite Internet is gradually becoming an important part of future communication networks, especially in complex and dynamic scenarios such as remote areas, oceans, deserts, forests and in the air, satellite communication has shown its unique advantages. However, the communication environment in these scenarios is complex and changeable, such as the relative motion between satellites and ground terminals, the attitude changes of terminal carrier antennas, atmospheric interference, etc., all of which pose severe challenges to communication quality.

[0003] Existing satellite communication terminals often lack sufficient adaptive adjustment capabilities when faced with complex dynamic scenarios, resulting in reduced communication performance and affected stability and reliability. Summary of the invention

[0004] In view of this, the purpose of the present application is to propose a satellite link adjustment method and electronic device in a dynamic scenario to solve or partially solve the above technical problems.

[0005] Based on the above purpose, the present application provides a method for adjusting a satellite link in a dynamic scenario, including:

[0006] Real-time monitoring of communication terminal and satellite link parameter data, atmospheric environment data and position and attitude information of communication terminal carrier in dynamic scenes;

[0007] Determine, based on the parameter data of the communication terminal and the satellite link, the rainfall attenuation information, the gas loss information, the cloud attenuation information, the free space path loss information and the cross polarization loss information of the space channel under the atmospheric environment data;

[0008] According to the position and attitude information of the communication terminal carrier and the orbital position of the satellite, the antenna-to-star scanning angle of the line connecting the satellite and the antenna origin and the antenna normal is determined;

[0009] Determine the antenna-to-star scanning angle deviation based on the antenna-to-star scanning angle, and determine the antenna-to-star azimuth angle deviation, and then determine the antenna gain value of the antenna-to-star scanning angle deviation and the antenna-to-star azimuth angle deviation according to the antenna gain pattern;

[0010] Determine within a predetermined time period: a rainfall attenuation function formed by rainfall attenuation information, a satellite scanning angle function formed by an antenna satellite scanning angle, a carrier-to-noise ratio function formed by a carrier-to-noise ratio, and an antenna gain function formed by an antenna gain value;

[0011] Determine the rainfall attenuation variation trend function, the satellite scanning angle variation trend function, the carrier-to-noise ratio variation trend function and the antenna gain variation trend function and perform weighted summation to obtain the link quality variation trend function;

[0012] In response to determining that the link quality change trend value at the current moment determined according to the link quality change trend function is greater than a first threshold, a target adjustment method corresponding to the satellite link is determined, and the satellite link is adjusted according to the target adjustment method.

[0013] Based on the same inventive concept, the present application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the method described above when executing the program.

[0014] From the above, it can be seen that the satellite link adjustment method and electronic device in dynamic scenarios provided by the present application can determine the rainfall attenuation information of the space channel, the antenna star scanning angle, and the antenna gain value according to the parameter data of the communication terminal and the satellite link monitored in real time in the dynamic scenario, as well as the atmospheric environment data and the position and attitude information of the communication terminal carrier, and then determine various attenuation functions within a predetermined time period, and then obtain the link quality change trend function after weighted summation of these attenuation functions. In this way, the link quality change trend value at the current moment determined according to the link quality change trend function is compared with the first threshold. If it is greater than, it proves that the quality of the satellite link is at risk of degrading to the point where communication cannot be achieved, and adjustment is required. The most appropriate target adjustment method will be determined according to the current situation of the satellite link. After adjusting the satellite link according to the target adjustment method, the adjustment cost can be minimized while ensuring the link quality. The link adjustment is performed before the quality of the satellite link deteriorates, thereby ensuring the continuous stability and reliability of the satellite link. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions in the present application or related technologies, the drawings required for use in the embodiments or related technical descriptions are briefly introduced below. Obviously, the drawings described below are only embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0016] Figure 1 A flowchart of a method for adjusting a satellite link in a dynamic scenario according to an embodiment of the present application;

[0017] Figure 2 A schematic diagram of determining the angle between the carrier plane, antenna and satellite in an embodiment of the present application;

[0018] Figure 3A schematic diagram of the azimuth deviation of the antenna corresponding to the satellite of an embodiment of the present application;

[0019] Figure 4 A schematic diagram of the structure of a satellite link adjustment device in a dynamic scenario according to an embodiment of the present application;

[0020] Figure 5 A schematic diagram of the structure of an electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0021] In order to make the objectives, technical solutions and advantages of the present application more clearly understood, the present application is further described in detail below in combination with specific embodiments and with reference to the accompanying drawings.

[0022] It should be noted that, unless otherwise defined, the technical terms or scientific terms used in the embodiments of the present application should be the usual meanings understood by people with ordinary skills in the field to which the present application belongs. The "first", "second" and similar words used in the embodiments of the present application do not represent any order, quantity or importance, but are only used to distinguish different components. "Including" or "comprising" and similar words mean that the elements or objects appearing in front of the word cover the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0023] The embodiment of the present application proposes a method for adjusting a satellite link in a dynamic scenario, such as Figure 1 As shown, including:

[0024] Step 101, real-time monitoring of parameter data of the communication terminal and the satellite link, as well as atmospheric environment data and position and attitude information of the communication terminal carrier in a dynamic scene.

[0025] In some embodiments, real-time monitoring in a dynamic scene:

[0026] 1. Collect through directly connected communication terminals: basic parameter data of the communication terminal, basic parameter data of the satellite beam to which the communication terminal is connected, and link performance index data (including carrier-to-noise ratio C / N0).

[0027] 2. Atmospheric environment data, specifically including: obtaining ambient temperature through temperature sensors, obtaining air relative humidity through humidity sensors, obtaining atmospheric pressure through pressure sensors, and obtaining rainfall through rainfall sensors.

[0028] 3. The position and attitude information of the communication terminal carrier specifically includes: real-time position information and altitude information obtained by the GPS positioning module installed in the communication terminal carrier, and the heading angle, pitch angle and roll angle collected by the gyroscope and compass installed on the communication terminal carrier.

[0029] Step 102, determining, based on the parameter data of the communication terminal and the satellite link, the rainfall attenuation information, the gas loss information, the cloud attenuation information, the free space path loss information and the cross polarization loss information of the space channel under the atmospheric environment data.

[0030] In specific implementation, the parameter data of the communication terminal and satellite link monitored above, the collected atmospheric environment data, and the frequency band information of the satellite beam are combined to perform spatial channel attenuation calculation to determine the rainfall attenuation information A. rain 、Gas loss information A gas , Cloud attenuation information A cloud , free space path loss information A path , cross-polarization loss information A xpd , add up to get the total free space channel attenuation A space .

[0031] A space =A rain +A gas +A cloud +A path +A xpd .

[0032] Step 103, determining the antenna-to-star scanning angle of the line connecting the satellite and the antenna origin and the antenna normal according to the position and attitude information of the communication terminal carrier and the orbital position of the satellite.

[0033] During specific implementation, the communication terminal carrier (for example, an airplane, vehicle, ship, etc.) is determined, and the positive direction of the X-axis of the communication carrier coordinate system is determined to be the forward direction of the communication terminal carrier, the Y-axis (for example, the direction of the right wing of the aircraft's fuselage is the positive direction of the Y-axis) is perpendicular to the X-axis on the plane, and the positive direction of the Z-axis is the vertical upward direction (for example, perpendicular to the upward direction of the aircraft's fuselage plane), forming a left-handed coordinate system.

[0034] For example, taking the communication terminal carrier as an aircraft, the heading angle, pitch angle, and roll angle of the position attitude information are specifically described:

[0035] The heading angle is the angle between the projection of the nose direction on the horizontal plane and true north, with north-east being positive and ranging from 0 to 360°;

[0036] The pitch angle is the angle between the nose direction and the horizontal plane, with the nose up being positive, and the range is -90° to 90°;

[0037] Roll angle refers to the angle of rotation of the aircraft around its longitudinal axis, with right roll being positive and the range is -180° to 180°.

[0038] In some embodiments, step 103 specifically includes:

[0039] Step 1031, determine the longitude and latitude coordinates (lon, lat, height) of the communication terminal, and perform coordinate transformation on the longitude and latitude coordinates based on the first coordinate transformation matrix A1 to obtain the first coordinate (X e , Y e , Z e ).

[0040] In specific implementation, the first coordinate (X e , Y e , Z e ) belongs to the coordinate value of the earth coordinate system (WGS84 coordinate system).

[0041] Step 1032, determine the second coordinate (X′) of the satellite in the earth coordinate system e , Y′ e , Z′ e ).

[0042] Similarly, the method for obtaining the first coordinate is used to determine the longitude and latitude coordinates of the satellite, and then perform coordinate transformation to obtain the second coordinate (X′ e , Y′ e , Z′ e ).

[0043] Step 1033, with the north direction of the earth's tangent plane as the X direction and the east direction as the Y direction, a navigation coordinate system that satisfies the left-hand coordinate system rule is established. After the second coordinate conversion matrix A2, the coordinates of the line connecting the satellite and the communication terminal are determined as (X′ e -X e , Y′ e -Y e , Z′ e -Z e ).

[0044] Step 1034: In the navigation coordinate system, taking the position of the communication terminal as the origin, based on the coordinates of the line connecting the satellite and the communication terminal, convert the satellite coordinates into the third coordinates (X n , Y n , Z n ).

[0045] Step 1035, establish a carrier coordinate system of the communication terminal carrier that satisfies the left-hand coordinate system rule, and transform the third coordinate according to the third coordinate transformation matrix A3 according to the heading angle, pitch angle and roll angle in the position and attitude information of the communication terminal carrier to obtain the fourth coordinate (X b, Y b , Z b ).

[0046] Step 1036, construct an antenna coordinate system with the center of the antenna plane as the origin, the antenna plane as the plane, and the normal of the antenna horizontal plane as the vertical axis, and transform the fourth coordinate according to the fourth coordinate transformation matrix A4 to obtain the fifth coordinate (X a , Y a , Z a ).

[0047] Step 1037, determine the antenna scanning angle θ s for

[0048] Through the above solution, the antenna star scanning angle can be accurately determined.

[0049] Step 104, determining the antenna scanning angle deviation based on the antenna scanning angle, and determining the antenna azimuth deviation, and then determining the antenna gain value of the antenna scanning angle deviation and the antenna azimuth deviation according to the antenna gain pattern.

[0050] In some embodiments, step 104 includes:

[0051] Step 1041, setting the maximum adjustment angle θ0 of the antenna in the direction of the antenna star scanning angle (such as Figure 2 shown).

[0052] In a specific implementation, when the direction of the antenna star scanning angle (ie, the antenna star scanning angle) deviates from the antenna normal line within the range of ±θ0, the antenna can be automatically adjusted to face the antenna normal line direction.

[0053] Step 1042, in response to determining the antenna scanning angle θ s >θ0 (there will be a pointing deviation between the antenna formation direction and the antenna normal direction), the antenna star scanning angle deviation Δθ is determined to be Δθ=θ s -θ0(such as Figure 2 shown).

[0054] Step 1043, determine if the line connecting the satellite and the antenna origin is in the antenna plane (e.g., Figure 3 As shown, the angle between the projection of the antenna coordinate system XOY plane) and the set direction (for example, the X-axis direction) is used as the antenna azimuth deviation to the satellite. (like Figure 3 As shown), the two angles of the antenna scanning angle deviation and the antenna azimuth angle deviation are recorded as

[0055] Step 1044: Determine the antenna scanning angle deviation and the antenna azimuth angle deviation according to the antenna gain pattern. The antenna gain value G under .

[0056] In a specific implementation, the antenna gain pattern of the antenna gain value corresponding to each angle is pre-stored, so that the antenna gain pattern corresponding to each angle can be obtained according to the first angle. Determine the corresponding antenna gain value G.

[0057] Step 105, determining within a predetermined time period: a rainfall attenuation function A formed by the rainfall attenuation information rain (t), the satellite scanning angle function θ(t) formed by the antenna satellite scanning angle, the carrier-to-noise ratio function (C / N0)(t) formed by the carrier-to-noise ratio, and the antenna gain function G(t) formed by the antenna gain value. Where t is time, C / N0 is the ratio of the carrier average power C to the noise average power N0.

[0058] Step 106, determining the rainfall attenuation variation trend function, the star scanning angle variation trend function, the carrier-to-noise ratio variation trend function and the antenna gain variation trend function and performing weighted summation to obtain a link quality variation trend function.

[0059] In some embodiments, step 106 includes:

[0060] Step 1061, determine the rainfall attenuation function A rain (t), the satellite scanning angle function θ(t), the carrier-to-noise ratio function (C / N0)(t) and the first derivative A′ of the antenna gain function G(t) rain (t), θ′(t), (C / N0)′(t) and G′(t), the second derivative A″ rain (t), θ″(t), (C / N0)''(t) and G″(t).

[0061] Step 1062, the rainfall attenuation change trend function is expressed as:

[0062] T rain (t) = a1A rain (t)+b1A′ rain (t)+c1A″ rain (t) 其中 , a.

[0063] b1 and c1 are both preset rainfall attenuation variation coefficients.

[0064] Step 1063, the star scanning angle variation trend function is expressed as:

[0065] T θ (t)=a2θ(t)+b2θ(t)+c2θ(t), wherein a2, b2 and c2 are all preset star scanning angle variation coefficients.

[0066] Step 1064, the carrier-to-noise ratio variation trend function is expressed as:

[0067] T cn (t)=a3(C / N0)(t)+b3(C / N0)(t)+c3(C / N0)(t), wherein a3, b3 and c3 are all preset carrier-to-noise ratio variation coefficients.

[0068] Step 1065, the antenna gain change trend function is expressed as:

[0069] T G (t) = a4G(t) + b4G′(t) + c4G"(t) where a4, b4 and c4 are all preset antenna gain variation coefficients.

[0070] Step 1066, the link quality change trend function T(t) is:

[0071] T(t)=αT rain (t)+βT θ (t)+γT cn (t)+δT G (t) where α is the influence factor of rainfall attenuation, β is the influence factor of the change of the star scanning angle, γ is the influence factor of the carrier-to-noise ratio, and δ is the influence factor of the antenna gain.

[0072] Step 107, in response to determining that the link quality change trend value at the current moment determined according to the link quality change trend function is greater than the first threshold, determining a target adjustment method corresponding to the satellite link, and adjusting the satellite link according to the target adjustment method.

[0073] In some embodiments, step 107 includes:

[0074] Step 1071, in response to the link quality change trend value T(t0) at the current time t0 being greater than the first threshold TH (at this time, the satellite link quality has the risk of decreasing to affect the communication quality, and the communication link needs to be adjusted immediately), according to the rainfall attenuation change trend function T rain (t) Determine the rainfall attenuation change trend value T at the current moment rain (t0).

[0075] In specific implementation, when T(t0) is greater than the first threshold TH, it is considered that the satellite link quality has the risk of decreasing to affect the communication quality, and the communication link needs to be adjusted immediately to ensure the stability of the subsequent link quality. At this time, by judging the impact of the change trend of different indicators on the overall change trend, different link adjustment schemes are decided. If T(t0) is less than or equal to the first threshold TH, the above process from 1061 to 1066 is repeated. The current link quality change trend value T(t0) is continuously monitored in real time.

[0076] Step 1072, in response to the rainfall attenuation change trend value T at the current time t0 rain (t0) is greater than the rainfall attenuation change trend threshold TH rain When determining that the target adjustment method is ACM (Adaptive Modulation and Coding) adaptive coding adjustment.

[0077] During specific implementation, the anti-interference performance of the satellite link is enhanced through ACM adaptive coding adjustment.

[0078] Step 1073, in response to determining that the target adjustment mode is ACM adaptive coding adjustment, adjusting the modulation mode and coding rate of the wireless link transmission for the satellite link, and obtaining the adjusted satellite link parameters.

[0079] Step 1074: Determine the satellite link margin according to the adjusted satellite link parameters.

[0080] In some embodiments, the satellite link margin determination process in step 1074 is:

[0081] Step 10741, rainfall attenuation information A rain 、Gas loss information A gas , Cloud attenuation information A cloud , free space path loss information A path , cross-polarization loss information A xpd , add up to get the total free space channel attenuation A space , the total attenuation information of the spatial channel A is accumulated space , and determine the spatial gain G.

[0082] Step 10742, based on the total attenuation A of the spatial channel space and spatial gain G, determine the satellite link adjusted link carrier-to-noise ratio C / N0, and the transmission threshold value of the link carrier-to-noise ratio (C / N0) th .

[0083] Among them, (C / N0) th =(E b / N0) th +10lgR,(E b / N0) th is the threshold value of the ratio of energy per bit to noise power spectrum density, R is the required transmission data rate, (E b / N0) th It is the minimum value that the link must reach, according to the bit error rate P of data transmission b Depends on the requirements. b YesE b / N0 is a function of the coding modulation / demodulation decoding method adopted and the equipment performance loss. In general, the equipment performance (such as demodulation, decoding, despreading) loss is less than 1dB.

[0084] Step 10743, the satellite link adjusted link margin M is: the satellite link adjusted link carrier-to-noise ratio minus the transmission threshold. The formula is: M = C / N0-(C / N0) th .

[0085] Step 1075: In response to determining that the satellite link margin M is less than or equal to a margin threshold, the target adjustment mode is changed to a satellite switching processing mode.

[0086] Step 1076: In response to the satellite link margin being greater than a margin threshold, determining that satellite link adjustment is completed.

[0087] In some embodiments, step 107 includes:

[0088] Step 1071′, in response to the link quality change trend value T(t0) at the current time t0 being greater than the first threshold, according to the carrier-to-noise ratio change trend function T cn (t) Determine the carrier-to-noise ratio change trend value T at the current moment cn (t0), and according to the antenna gain variation trend function T G (t) Determine the antenna gain change trend value T at the current moment G (t0), and according to the trend function of the star scanning angle change T θ (t) Determine the current scanning angle change trend value T θ (t0);

[0089] Step 1072', determine T cn (t0)>TH cn , and T G (t0)≤TH G , and T θ (t0)≤TH θ (This indicates that the link quality may be degraded due to obstruction, and satellite switching processing is required), determining the target adjustment method as the satellite switching processing method, determining the satellite switching plan, and calculating the satellite link margin corresponding to the satellite switching plan. In response to the satellite link margin being greater than the margin threshold, performing satellite switching processing according to the satellite switching plan.

[0090] In some embodiments, in step 1072', determining a satellite switching scheme, calculating a satellite link margin corresponding to the satellite switching scheme, and performing satellite switching processing according to the satellite switching scheme in response to the satellite link margin being greater than a margin threshold, includes:

[0091] Step 10721', calculate the current visible range of the communication terminal in combination with the terrain.

[0092] Step 10722', traverse the visible satellites within the visible range in the satellite database, and determine the corresponding switching satellite according to the visible satellites.

[0093] During the specific implementation, if the frequency (center point of satellite communication frequency) and polarization mode (polarization mode of satellite antenna) of the current moment of the satellite switching plan changes compared with the previous moment, the relevant equipment of the ground station needs to be adjusted.

[0094] Step 10723', determining a satellite switching cost function according to the switching satellite.

[0095] In the specific implementation, the difference in the remaining available resources of different satellites, the time cost of switching different satellites and other factors will affect the specific satellite switching plan. Based on this, in order to ensure the minimum cost of switching satellites, a satellite switching cost function C is constructed.

[0096] The formula is: C = α1C polor +α2C freq +α3C resource +α4C time , where C polor The cost of changing the polarization mode. If the polarization mode is changed, C polor is 1, otherwise it is 0; C freq The cost of frequency change; C resource is the cost of available resources, which is positively correlated with the remaining resources; C time is the overall time efficiency cost of switching satellites; α1 to α6 are the influencing factors of each item.

[0097] Step 10724': Calculate the satellite switching cost values ​​of various satellite switching solutions according to the satellite switching cost function, and sort the various satellite switching solutions according to the satellite switching cost values.

[0098] Step 10725', continuously and sequentially determine the satellite link margins corresponding to the corresponding satellite switching solutions in the order of the satellite switching generation values ​​from small to large, until the satellite link margin is greater than the margin threshold, and then stop sequentially determining.

[0099] During specific implementation, starting from the satellite switching scheme with the smallest satellite switching value, if the corresponding satellite link margin is greater than the margin threshold, the satellite switching scheme with the smallest satellite switching value is selected; if the corresponding satellite link margin is less than or equal to the margin threshold, the next satellite switching scheme is selected in the order of the satellite switching value from small to large, until the satellite link margin is greater than the margin threshold, and the satellite switching scheme corresponding to the satellite link margin greater than the margin threshold is used as the final execution scheme.

[0100] Step 10726', performing satellite switching processing according to the satellite switching solution corresponding to the satellite link margin being greater than the margin threshold.

[0101] In some embodiments, step 107 includes:

[0102] Step I, in response to the link quality change trend value T(t0) at the current moment determined according to the link quality change trend function T(t) being greater than a first threshold, according to the antenna gain change trend function T G (t) Determine the antenna gain change trend value T at the current moment G (t0), and according to the trend function of the star scanning angle change T θ (t) Determine the current scanning angle change trend value T θ (t0).

[0103] Step II, determine T G (t0)>TH G , and T θ (t0)>TH θ (It is believed that the deflection of the communication terminal carrier's attitude may cause the antenna's star scanning angle to deviate too much, resulting in a decrease in gain, and attitude adjustment is required at this time), and the target adjustment method is determined to be the attitude adjustment plan.

[0104] Step III, according to the antenna scanning angle deviation and the antenna azimuth angle deviation The attitude adjustment scheme is determined to adjust the attitude of the communication terminal carrier downward by Δθ and adjust it toward the target direction (for example, due west) by

[0105] The solution of the present invention can calculate the changing trend of the current satellite link indicators in real time under the dynamic scenario of terminal movement, and predict the moment when the satellite link quality may deteriorate, so as to adjust the satellite link in advance and ensure the continuous stability of the satellite link quality.

[0106] The solution of the present invention can adaptively select the optimal adjustment solution according to different situations to ensure the optimal satellite link optimization effect and reduce the cost caused by satellite link adjustment.

[0107] It should be noted that the method of the embodiment of the present application can be performed by a single device, such as a computer or server. The method of this embodiment can also be applied to a distributed scenario and completed by multiple devices cooperating with each other. In the case of such a distributed scenario, one of the multiple devices can only perform one or more steps in the method of the embodiment of the present application, and the multiple devices will interact with each other to complete the described method.

[0108] It should be noted that the above describes some embodiments of the present application. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in an order different from that in the above embodiments and still achieve the desired results. In addition, the processes depicted in the accompanying drawings do not necessarily require the specific order or continuous order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0109] Based on the same inventive concept, corresponding to any of the above-mentioned embodiment methods, the present application also provides a satellite link adjustment device in a dynamic scenario.

[0110] refer to Figure 4 , the device comprises:

[0111] The data monitoring module 201 is configured to monitor parameter data of the communication terminal and the satellite link, as well as atmospheric environment data and position and attitude information of the communication terminal carrier in real time in a dynamic scene;

[0112] The attenuation determination module 202 is configured to determine, based on the parameter data of the communication terminal and the satellite link, the rainfall attenuation information, the gas loss information, the cloud attenuation information, the free space path loss information and the cross polarization loss information of the space channel under the atmospheric environment data;

[0113] The antenna-to-satellite scanning angle determination module 203 is configured to determine the antenna-to-satellite scanning angle of the line connecting the satellite and the antenna origin and the antenna normal according to the position attitude information of the communication terminal carrier and the orbital position of the satellite;

[0114] The antenna gain determination module 204 is configured to determine the antenna-to-star scanning angle deviation based on the antenna-to-star scanning angle, and determine the antenna-to-star azimuth angle deviation, and then determine the antenna gain value of the antenna-to-star scanning angle deviation and the antenna-to-star azimuth angle deviation according to the antenna gain pattern;

[0115] The function determination module 205 determines within a predetermined time period: a rainfall attenuation function formed by rainfall attenuation information, a satellite scanning angle variation function formed by an antenna satellite scanning angle, a carrier-to-noise ratio function formed by a carrier-to-noise ratio, and an antenna gain function formed by an antenna gain value;

[0116] The variation trend determination module 206 is configured to determine a rainfall attenuation variation trend function, a star scanning angle variation trend function, a carrier-to-noise ratio variation trend function, and an antenna gain variation trend function, and perform weighted summation to obtain a link quality variation trend function;

[0117] The satellite link adjustment module 207 is configured to determine a target adjustment method corresponding to the satellite link in response to determining that the link quality change trend value at the current moment determined according to the link quality change trend function is greater than a first threshold, and adjust the satellite link according to the target adjustment method.

[0118] In some embodiments, the antenna star scanning angle determination module 203 is specifically configured to:

[0119] Determine the longitude and latitude coordinates of the communication terminal, and transform the longitude and latitude coordinates based on the first coordinate transformation matrix A1 to obtain the first coordinate (X e , Y e , Z e );

[0120] Determine the second coordinate (X′) of the satellite in the Earth coordinate system e , Y′ e , Z′ e );

[0121] With the north direction of the earth's tangent plane as the X direction and the east direction as the Y direction, a navigation coordinate system that satisfies the left-hand coordinate system rule is established. After the second coordinate conversion matrix A2, the coordinates of the line connecting the satellite and the communication terminal are determined as (X′ e -X e , Y′ e -Y e , Z′ e -Z e );

[0122] In the navigation coordinate system, the position of the communication terminal is taken as the origin, and based on the coordinates of the line connecting the satellite and the communication terminal, the satellite coordinates are converted into the third coordinate (X n , Y n , Z n );

[0123] Establish a carrier coordinate system of the communication terminal carrier that satisfies the left-hand coordinate system rule. According to the heading angle, pitch angle and roll angle in the position and attitude information of the communication terminal carrier, the third coordinate is transformed according to the third coordinate transformation matrix A3 to obtain the fourth coordinate (X) of the satellite in the carrier coordinate system. b , Y b , Z b );

[0124] The antenna plane center is taken as the origin, the antenna plane is taken as the plane, and the normal line of the antenna horizontal plane is taken as the vertical axis to construct the antenna coordinate system. The fourth coordinate is transformed according to the fourth coordinate transformation matrix A4 to obtain the fifth coordinate (X a , Y a , Z a );

[0125] Determine the antenna scanning angle θ s for

[0126] In some embodiments, the antenna gain determination module 204 is specifically configured to:

[0127] Set the maximum adjustment angle θ0 of the antenna in the direction of the antenna star scanning angle;

[0128] In response to determining the antenna scanning angle θ s When θ>θ0, the antenna scanning angle deviation Δθ is determined to be Δθ=θ s -θ0;

[0129] Determine the angle between the projection of the line connecting the satellite and the antenna origin on the antenna plane and the set direction as the antenna azimuth deviation The two angles obtained, namely, the antenna scanning angle deviation and the antenna azimuth angle deviation, are recorded as

[0130] Determine the antenna-to-satellite scanning angle deviation and the antenna-to-satellite azimuth angle deviation according to the antenna gain pattern The antenna gain value G under .

[0131] In some embodiments, the change trend determination module 206 is specifically configured to:

[0132] Determine the A of the rainfall attenuation function rain (t), the satellite scanning angle function θ(t), the carrier-to-noise ratio function (C / N0)(t) and the first derivative A′ of the antenna gain function G(t) rain (t), θ′(t), (C / N0)′(t) and G′(t), the second derivative A″ rain (t), θ″(t), (C / N0)″(t) and G″(t), where t is time and C / N0 is the ratio of the carrier average power C to the noise average power N0;

[0133] The rainfall attenuation trend function is expressed as:

[0134] T rain (t) = a 11 A rain (t)+b1A′ rain (t)+c1A″ rain (t) where a1, b1 and c1 are the preset rainfall attenuation variation coefficients;

[0135] The trend function of the star scanning angle change is expressed as:

[0136] T θ(t) = a2θ(t) + b2θ′(t) + c2θ″(t), where a2, b2 and c2 are all preset star scanning angle variation coefficients;

[0137] The carrier-to-noise ratio change trend function is expressed as:

[0138] T cn (t)=a3(C / N0)(t)+b3(C / N0)′(t)+c3(C / N0)″(t), where a3, b3 and c3 are all preset carrier-to-noise ratio variation coefficients;

[0139] The antenna gain variation trend function is expressed as:

[0140] T G (t) = a4G(t) + b4G′(t) + c4G"(t) where a4, b4 and c4 are all preset antenna gain variation coefficients;

[0141] The link quality change trend function T(t) is:

[0142] T(t)=αT rain (t)+βT θ (t)+γT cn (t)+δT G (t) where α is the influence factor of rainfall attenuation, β is the influence factor of the change of the star scanning angle, γ is the influence factor of the carrier-to-noise ratio, and δ is the influence factor of the antenna gain.

[0143] In some embodiments, the satellite link adjustment module 207 is specifically configured to:

[0144] In response to the link quality change trend value T(t0) at the current time t0 determined according to the link quality change trend function T(t) being greater than the first threshold, according to the rainfall attenuation change trend function T rain (t) Determine the rainfall attenuation change trend value T at the current moment rain (t0);

[0145] In response to the rainfall attenuation change trend value T at the current moment rain (t0) is greater than the rainfall attenuation change trend threshold TH rain When determining that the target adjustment mode is ACM adaptive coding adjustment;

[0146] In response to determining that the target adjustment mode is ACM adaptive coding adjustment, adjusting the modulation mode and coding rate of the wireless link transmission for the satellite link, and acquiring adjusted satellite link parameters;

[0147] Determining a satellite link margin according to the adjusted satellite link parameters;

[0148] In response to determining that the satellite link margin is less than or equal to a margin threshold, changing the target adjustment mode to a switching satellite processing mode;

[0149] In response to the satellite link margin being greater than a margin threshold, it is determined that satellite link adjustment is completed.

[0150] In some embodiments, the satellite link adjustment module 207 is specifically configured to:

[0151] In response to the link quality change trend value T(t0) at the current time t0 determined according to the link quality change trend function T(t) being greater than the first threshold, the carrier-to-noise ratio change trend value T at the current time t0 is determined according to the carrier-to-noise ratio change trend function cn (t0), and according to the antenna gain variation trend function T G (t) Determine the antenna gain change trend value T at the current moment G (t0), and according to the trend function of the star scanning angle change T θ (t) Determine the current scanning angle change trend value T θ (t0);

[0152] Determine T cn (t0)>TH cn , and T G (t0)≤TH G , and T θ (t0)≤TH θ , determine that the target adjustment method is a switching satellite processing method, determine a switching satellite plan, and calculate the satellite link margin corresponding to the switching satellite plan. In response to the satellite link margin being greater than the margin threshold, perform satellite switching processing according to the switching satellite plan.

[0153] In some embodiments, the satellite link adjustment module 207 is further configured to:

[0154] Calculate the current visible range of the communication terminal in combination with the terrain;

[0155] Traversing the visible satellites within the visible range in the satellite database, and determining the corresponding switching satellite according to the visible satellites;

[0156] Determine the satellite switching cost function according to the switching satellite;

[0157] Calculating satellite switching cost values ​​of various satellite switching solutions according to the satellite switching cost function, and sorting the various satellite switching solutions according to the satellite switching cost values;

[0158] The satellite link margins corresponding to the corresponding satellite switching solutions are continuously determined in sequence according to the satellite switching generation values ​​from small to large, until the satellite link margins are greater than the margin threshold, and the sequential determination is stopped;

[0159] Satellite switching processing is performed according to a satellite switching scheme corresponding to a satellite link margin being greater than a margin threshold.

[0160] In some embodiments, the satellite link adjustment module 207 is specifically configured to:

[0161] In response to the link quality change trend value T(t0) at the current time t0 determined according to the link quality change trend function T(t) being greater than the first threshold, according to the antenna gain change trend function T G (t) Determine the antenna gain change trend value T at the current moment G (t0), and according to the trend function of the star scanning angle change T θ (t) Determine the current scanning angle change trend value T θ (t0);

[0162] Determine T G (t0)>TH G , and T θ (t0)>TH θ , determine the target adjustment method as the attitude adjustment scheme;

[0163] According to the antenna scanning angle deviation and the antenna azimuth angle deviation The attitude adjustment scheme is to adjust the attitude of the communication terminal carrier downward by Δθ and adjust it toward the target direction.

[0164] In some embodiments, the apparatus further comprises a satellite link margin determination module configured to:

[0165] The rainfall attenuation information, gas loss information, cloud attenuation information, free space path loss information and cross-polarization loss information of the space channel of the adjusted satellite link are accumulated to obtain the total attenuation information of the space channel;

[0166] determining an antenna gain value of a spatial channel of the satellite link after the adjustment;

[0167] Determine the adjusted link carrier-to-noise ratio of the satellite link and the transmission threshold value of the link carrier-to-noise ratio based on the total attenuation information of the spatial channel and the antenna gain value;

[0168] The adjusted link margin of the satellite link is: the adjusted link carrier-to-noise ratio of the satellite link minus the transmission threshold.

[0169] For the convenience of description, the above device is described in terms of functions divided into various modules. Of course, when implementing the present application, the functions of each module can be implemented in the same or multiple software and / or hardware.

[0170] The device of the above embodiment is used to implement the corresponding method in any of the above embodiments, and has the beneficial effects of the corresponding method embodiment, which will not be described in detail here.

[0171] Based on the same inventive concept, corresponding to any of the above-mentioned embodiments and methods, the present application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the method described in any of the above embodiments when executing the program.

[0172] Figure 5 A more specific schematic diagram of the hardware structure of an electronic device provided in this embodiment is shown, and the device may include: a processor 1010, a memory 1020, an input / output interface 1030, a communication interface 1040, and a bus 1050. The processor 1010, the memory 1020, the input / output interface 1030, and the communication interface 1040 are connected to each other through the bus 1050 in the device.

[0173] The processor 1010 can be implemented by a general-purpose CPU (Central Processing Unit), a microprocessor, an application-specific integrated circuit (ASIC), or one or more integrated circuits, and is used to execute relevant programs to implement the technical solutions provided in the embodiments of this specification.

[0174] The memory 1020 may be implemented in the form of ROM (Read Only Memory), RAM (Random Access Memory), static storage device, dynamic storage device, etc. The memory 1020 may store an operating system and other application programs. When the technical solutions provided in the embodiments of this specification are implemented by software or firmware, the relevant program codes are stored in the memory 1020 and are called and executed by the processor 1010.

[0175] The input / output interface 1030 is used to connect the input / output module to realize information input and output. The input / output module can be configured in the device as a component (not shown in the figure), or it can be externally connected to the device to provide corresponding functions. The input device may include a keyboard, a mouse, a touch screen, a microphone, various sensors, etc., and the output device may include a display, a speaker, a vibrator, an indicator light, etc.

[0176] The communication interface 1040 is used to connect a communication module (not shown) to realize communication interaction between the device and other devices. The communication module can realize communication through a wired mode (such as USB, network cable, etc.) or a wireless mode (such as mobile network, WIFI, Bluetooth, etc.).

[0177] The bus 1050 includes a path that transmits information between the various components of the device (eg, the processor 1010, the memory 1020, the input / output interface 1030, and the communication interface 1040).

[0178] It should be noted that, although the above device only shows the processor 1010, the memory 1020, the input / output interface 1030, the communication interface 1040 and the bus 1050, in the specific implementation process, the device may also include other components necessary for normal operation. In addition, it can be understood by those skilled in the art that the above device may also only include the components necessary for implementing the embodiments of the present specification, and does not necessarily include all the components shown in the figure.

[0179] The electronic device of the above embodiment is used to implement the corresponding method in any of the above embodiments, and has the beneficial effects of the corresponding method embodiment, which will not be described in detail here.

[0180] Based on the same inventive concept, corresponding to any of the above-mentioned embodiments, the present application also provides a non-transitory computer-readable storage medium, wherein the non-transitory computer-readable storage medium stores computer instructions, and the computer instructions are used to enable the computer to execute the method described in any of the above embodiments.

[0181] The computer-readable medium of this embodiment includes permanent and non-permanent, removable and non-removable media, and information storage can be implemented by any method or technology. Information can be computer-readable instructions, data structures, modules of programs, or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technology, read-only compact disk read-only memory (CD-ROM), digital versatile disk (DVD) or other optical storage, magnetic cassettes, magnetic tape magnetic disk storage or other magnetic storage devices or any other non-transmission media that can be used to store information that can be accessed by a computing device.

[0182] The computer instructions stored in the storage medium of the above embodiments are used to enable the computer to execute the method described in any of the above embodiments, and have the beneficial effects of the corresponding method embodiments, which will not be repeated here.

[0183] Those skilled in the art should understand that the discussion of any of the above embodiments is merely illustrative and is not intended to imply that the scope of the present application (including the claims) is limited to these examples. In line with the concept of the present application, the technical features in the above embodiments or different embodiments may be combined, the steps may be implemented in any order, and there are many other variations of the different aspects of the embodiments of the present application as described above, which are not provided in detail for the sake of simplicity.

[0184] In addition, to simplify the description and discussion, and in order not to make the embodiments of the present application difficult to understand, the known power supply / ground connection with the integrated circuit (IC) chip and other components may or may not be shown in the provided drawings. In addition, the device can be shown in the form of a block diagram to avoid making the embodiments of the present application difficult to understand, and this also takes into account the fact that the details of the implementation of these block diagram devices are highly dependent on the platform to be implemented in the embodiments of the present application (that is, these details should be fully within the scope of understanding of those skilled in the art). In the case of elaborating specific details (e.g., circuits) to describe exemplary embodiments of the present application, it is obvious to those skilled in the art that the embodiments of the present application can be implemented without these specific details or when these specific details are changed. Therefore, these descriptions should be considered to be illustrative rather than restrictive.

[0185] Although the present application has been described in conjunction with specific embodiments of the present application, many replacements, modifications and variations of these embodiments will be apparent to those skilled in the art from the foregoing description. For example, other memory architectures (e.g., dynamic RAM (DRAM)) may use the embodiments discussed.

[0186] The embodiments of the present application are intended to cover all such substitutions, modifications and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the embodiments of the present application should be included in the scope of protection of the present application.

Claims

1. A method for adjusting a satellite link in a dynamic scenario, characterized in that: include: Real-time monitoring of communication terminal and satellite link parameter data, atmospheric environment data and position and attitude information of communication terminal carrier in dynamic scenes; Determine the rainfall attenuation information, gas loss information, cloud attenuation information, free space path loss information and cross polarization loss information of the space channel under the atmospheric environment data according to the parameter data of the communication terminal and the satellite link; According to the position and attitude information of the communication terminal carrier and the orbital position of the satellite, the antenna-to-star scanning angle of the line connecting the satellite and the antenna origin and the antenna normal is determined; Determine the antenna scanning angle deviation based on the antenna scanning angle, and determine the antenna azimuth deviation, and then determine the antenna gain value of the antenna scanning angle deviation and the antenna azimuth deviation according to the antenna gain pattern; Determine within a predetermined time period: a rainfall attenuation function formed by rainfall attenuation information, a satellite scanning angle function formed by an antenna satellite scanning angle, a carrier-to-noise ratio function formed by a carrier-to-noise ratio, and an antenna gain function formed by an antenna gain value; Determine the rainfall attenuation variation trend function, the satellite scanning angle variation trend function, the carrier-to-noise ratio variation trend function and the antenna gain variation trend function and perform weighted summation to obtain the link quality variation trend function; In response to determining that the link quality change trend value at the current moment determined according to the link quality change trend function is greater than a first threshold, a target adjustment method corresponding to the satellite link is determined, and the satellite link is adjusted according to the target adjustment method.

2. The method according to claim 1, characterized in that The method of determining the antenna-to-star scanning angle of the line connecting the satellite and the antenna origin and the antenna normal line according to the position and attitude information of the communication terminal carrier in combination with the orbital position of the satellite comprises: Determine the longitude and latitude coordinates of the communication terminal, and transform the longitude and latitude coordinates based on the first coordinate transformation matrix A1 to obtain the first coordinate (X e , Y e , Z e ); Determine the second coordinate (X′) of the satellite in the Earth coordinate system e , Y′ e , Z′ e ); With the north direction of the earth's tangent plane as the X direction and the east direction as the Y direction, a navigation coordinate system that satisfies the left-hand coordinate system rule is established. After the second coordinate conversion matrix A2, the coordinates of the line connecting the satellite and the communication terminal are determined as (X′ e -X e , Y′ e -Y e , Z′ e -Z e ); In the navigation coordinate system, the position of the communication terminal is taken as the origin, and based on the coordinates of the line connecting the satellite and the communication terminal, the satellite coordinates are converted into the third coordinate (X n , Y n , Z n ); Establish a carrier coordinate system of the communication terminal carrier that satisfies the left-hand coordinate system rule. According to the heading angle, pitch angle and roll angle in the position and attitude information of the communication terminal carrier, the third coordinate is transformed according to the third coordinate transformation matrix A3 to obtain the fourth coordinate (X) of the satellite in the carrier coordinate system. b , Y b , Z b ); The antenna plane center is taken as the origin, the antenna plane is taken as the plane, and the normal line of the antenna horizontal plane is taken as the vertical axis to construct the antenna coordinate system. The fourth coordinate is transformed according to the fourth coordinate transformation matrix A4 to obtain the fifth coordinate (X a , Y a , Z a ); Determine the antenna scanning angle θ s for 3. The method according to claim 1, characterized in that The method of determining the antenna-to-star scanning angle deviation based on the antenna-to-star scanning angle and determining the antenna-to-star azimuth angle deviation, and then determining the antenna gain value of the antenna-to-star scanning angle deviation and the antenna-to-star azimuth angle deviation according to the antenna gain pattern, includes: Set the maximum adjustment angle θ0 of the antenna in the direction of the antenna star scanning angle; In response to determining the antenna scanning angle θ s When θ>θ0, the antenna scanning angle deviation Δθ is determined to be Δθ=θ s -θ0; Determine the angle between the projection of the line connecting the satellite and the antenna origin on the antenna plane and the set direction as the antenna azimuth deviation The two angles obtained, namely, the antenna scanning angle deviation and the antenna azimuth angle deviation, are recorded as Determine the antenna-to-satellite scanning angle deviation and the antenna-to-satellite azimuth angle deviation according to the antenna gain pattern The antenna gain value G under .

4. The method according to claim 3, characterized in that: The step of determining the rainfall attenuation variation trend function, the star scanning angle variation trend function, the carrier-to-noise ratio variation trend function, and the antenna gain variation trend function and performing weighted summation to obtain the link quality variation trend function includes: Determine the A of the rainfall attenuation function rain (t), the first derivative A′ of the satellite scanning angle function θ(t), the carrier-to-noise ratio function (C / N0)(t) and the antenna gain function G(t) rain (t), θ′(t), (C / N0)′(t) and G′(t), the second derivative A″ rain (t), θ″(t), (C / N0)″(t) and G″(t), where t is time and C / N0 is the ratio of the carrier average power C to the noise average power N0; The rainfall attenuation trend function is expressed as: T rain (t) = a1A rain (t)+b1A rain (t)+c1A rain (t), where a1, b1 and c1 are the preset rainfall attenuation variation coefficients; The trend function of the star scanning angle change is expressed as: T θ (t) = a2θ(t) + b2θ′(t) + c2θ″(t), where a2, b2 and c2 are all preset star scanning angle variation coefficients; The carrier-to-noise ratio change trend function is expressed as: T cn (t) = a3(C / N0)(t) + b3(C / N0)′(t) + c3(C / N0)″(t), where a3, b3 and c3 are all preset carrier-to-noise ratio variation coefficients; The antenna gain variation trend function is expressed as: T G (t) = a4G(t) + b4G′(t) + c4G″(t), where a4, b4 and c4 are all preset antenna gain variation coefficients; The link quality change trend function T(t) is: T(t)=αT rain (t)+βT θ (t)+γT cn (t)+δT G (t), where α is the influence factor of rainfall attenuation, β is the influence factor of the change of the star scanning angle, γ is the influence factor of the carrier-to-noise ratio, and δ is the influence factor of the antenna gain.

5. The method according to claim 4, characterized in that In response to determining that the link quality change trend value at the current moment determined according to the link quality change trend function is greater than a first threshold, determining a target adjustment mode corresponding to the satellite link, and adjusting the satellite link according to the target adjustment mode, including: In response to the link quality change trend value T(t0) at the current time t0 determined according to the link quality change trend function T(t) being greater than the first threshold, according to the rainfall attenuation change trend function T rain (t) Determine the rainfall attenuation change trend value T at the current moment rain (t0); In response to the rainfall attenuation change trend value T at the current moment rain (t0) is greater than the rainfall attenuation change trend threshold TH rain When determining that the target adjustment mode is ACM adaptive coding adjustment; In response to determining that the target adjustment mode is ACM adaptive coding adjustment, adjusting the modulation mode and coding rate of the wireless link transmission for the satellite link, and acquiring adjusted satellite link parameters; Determining a satellite link margin according to the adjusted satellite link parameters; In response to determining that the satellite link margin is less than or equal to a margin threshold, changing the target adjustment mode to a switching satellite processing mode; In response to the satellite link margin being greater than a margin threshold, it is determined that satellite link adjustment is completed.

6. The method according to claim 4, characterized in that In response to determining that the link quality change trend value at the current moment determined according to the link quality change trend function is greater than a first threshold, determining a target adjustment mode corresponding to the satellite link, and adjusting the satellite link according to the target adjustment mode, including: In response to the link quality change trend value T(t0) at the current time t0 determined according to the link quality change trend function T(t) being greater than the first threshold, according to the carrier-to-noise ratio change trend function T cn (t) Determine the carrier-to-noise ratio change trend value T at the current moment cn (t0), and according to the antenna gain variation trend function T G (t) Determine the antenna gain change trend value T at the current moment G (t0), and according to the trend function of the star scanning angle change T θ (t) Determine the current scanning angle change trend value T θ (t0); Determine T cn (t0)>TH cn , and T G (t0)≤TH G , and T θ (t0)≤TH θ , determine that the target adjustment method is a switching satellite processing method, determine a switching satellite plan, and calculate the satellite link margin corresponding to the switching satellite plan. In response to the satellite link margin being greater than the margin threshold, perform satellite switching processing according to the switching satellite plan.

7. The method according to claim 6, characterized in that The determining of the satellite switching scheme, calculating the satellite link margin corresponding to the satellite switching scheme, and performing satellite switching processing according to the satellite switching scheme in response to the satellite link margin being greater than a margin threshold, includes: Calculate the current visible range of the communication terminal in combination with the terrain; Traversing the visible satellites within the visible range in the satellite database, and determining the corresponding switching satellite according to the visible satellites; Determine the satellite switching cost function according to the switching satellite; Calculating satellite switching cost values ​​of various satellite switching solutions according to the satellite switching cost function, and sorting the various satellite switching solutions according to the satellite switching cost values; The satellite link margins corresponding to the corresponding satellite switching solutions are continuously determined in sequence according to the satellite switching generation values ​​from small to large, until the satellite link margins are greater than the margin threshold, and the sequential determination is stopped; Satellite switching processing is performed according to a satellite switching scheme corresponding to a satellite link margin being greater than a margin threshold.

8. The method according to claim 4, characterized in that In response to determining that the link quality change trend value at the current moment determined according to the link quality change trend function is greater than a first threshold, determining a target adjustment mode corresponding to the satellite link, and adjusting the satellite link according to the target adjustment mode, including: In response to the link quality change trend value T(t0) at the current time t0 determined according to the link quality change trend function T(t) being greater than the first threshold, according to the antenna gain change trend function T G (t) Determine the antenna gain change trend value T at the current moment G (t0), and according to the trend function of the star scanning angle change T θ (t) Determine the current scanning angle change trend value T θ (t0); Determine T G (t0)>TH G , and T θ (t0)>TH θ , determine the target adjustment method as the attitude adjustment scheme; According to the antenna scanning angle deviation and the antenna azimuth angle deviation The attitude adjustment scheme is to adjust the attitude of the communication terminal carrier downward by Δθ and adjust it toward the target direction.

9. The method according to any one of claims 5 to 7, characterized in that: The determination process of the satellite link margin is as follows: The rainfall attenuation information, gas loss information, cloud attenuation information, free space path loss information and cross-polarization loss information of the space channel of the adjusted satellite link are accumulated to obtain the total attenuation information of the space channel; determining an antenna gain value of a spatial channel of the satellite link after the adjustment; Determine the adjusted link carrier-to-noise ratio of the satellite link and the transmission threshold value of the link carrier-to-noise ratio based on the total attenuation information of the spatial channel and the antenna gain value; The adjusted link margin of the satellite link is: the adjusted link carrier-to-noise ratio of the satellite link minus the transmission threshold.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the program, the method according to any one of claims 1 to 9 is implemented.

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