Solar panel rotation optimization method based on measurement and control link availability measurement

Abstract

The present invention relates to a solar panel rotation optimization method based on a measurement and control link availability metric, comprising: S100, obtaining a measurement and control tracking window set based on a measurement and control link budget; S200, pre-planning a solar panel rotation strategy based on the measurement and control tracking window set to obtain a solar panel shielding window set for the measurement and control link; S300, monitoring the measurement and control link signal quality in real time based on the solar panel shielding window set and in combination with a solar panel shielding signal historical trend atlas to obtain a solar panel signal trend atlas; S400, dynamically adjusting the solar panel rotation strategy if the solar panel signal trend is consistent or identical with a trend in the solar panel shielding signal historical trend atlas; S500, entering the next measurement and control tracking window after the current tracking arc ends based on the measurement and control tracking window set, and repeating steps S200 to S500. This method can significantly improve the long-term operational control efficiency of a space mission during its on-orbit period, achieving a balance between complexity and accuracy.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft control technology, and in particular to a spacecraft solar sail panel rotation optimization method based on measurement and control link availability measurement. Background Art

[0002] During the in-orbit flight of large, multi-module spacecraft, external objects such as rotating solar panels, robotic arm movements, and extravehicular activities can potentially obstruct signal transmission between the ground and space wireless tracking and control links. This can degrade channel quality and introduce bit errors, or even lead to link interruption and loss of ground-to-space communication. Given the importance of tracking and control links for spacecraft status monitoring and flight control, signal obstruction caused by the spacecraft itself should be minimized to improve tracking and control link availability.

[0003] Generally speaking, robotic arm movements are executed according to program using path planning, and obstruction of the TT&C link can be minimized through pre-planning. Extravehicular activities are scheduled in fixed areas, and interference with the spacecraft's TT&C antennas is largely eliminated. Solar panels rotate to meet the energy balance requirements of the entire cabin, using heliocentric orientation. The impact on the TT&C link is often not taken into account. However, mathematical simulations and the execution of some space missions have shown that this rotation strategy has already caused obstruction of the TT&C link. Therefore, to further improve the availability of the TT&C link, it is necessary to further explore optimization methods to minimize the signal obstruction caused by solar panel rotation on the TT&C link while meeting energy requirements. Summary of the Invention

[0004] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a spacecraft solar panel rotation optimization method based on the measurement and control link availability measurement, which can greatly improve the long-term operation and control efficiency of the space mission during the on-orbit period and achieve a balance between the complexity and accuracy of the method.

[0005] In order to achieve the above-mentioned object of the invention, the technical solution of the present invention is:

[0006] The present invention provides a spacecraft solar panel rotation optimization method based on measurement and control link availability measurement, comprising:

[0007] S100, obtaining a measurement and control tracking window set through a measurement and control link budget;

[0008] S200, pre-planning a rotation strategy of the solar panel according to the measurement and control tracking window set, and obtaining a panel shielding window set of the solar panel to the measurement and control link;

[0009] S300, monitoring the signal quality of the measurement and control link in real time according to the solar panel shielding window set and in combination with the solar panel shielding signal historical trend atlas to obtain a solar panel signal trend atlas;

[0010] S400, if the solar panel signal trend is consistent with or identical to the trend of the solar panel shielding signal historical trend atlas, dynamically adjust the rotation strategy of the solar panel;

[0011] S500 , based on the measurement, control and tracking window set, after the current tracking arc segment ends, enter the next measurement, control and tracking window, and repeat S200 to S500 .

[0012] According to one aspect of the present invention, the tracking and control link in S100 is a relay link formed between the spacecraft and the relay satellite, in which the spacecraft relay antenna tracks the relay satellite.

[0013] According to one aspect of the present invention, S100 includes: performing measurement, control and tracking calculations based on the constraint information of the relay satellite orbital position, the spacecraft orbital attitude and the relay antenna installation position in combination with orbital dynamics to obtain a measurement, control and tracking window set.

[0014] According to one aspect of the present invention, the process of pre-planning the rotation strategy of the solar panel according to the measurement, control and tracking window set in S200 includes:

[0015] Based on the spacecraft orbital attitude, the relay antenna installation position, the relay satellite orbital position constraint information, the measurement and control tracking window set and the solar panel rotation parameters, combined with the spacecraft cabin energy balance constraint requirements, a deviation angle is preset for the solar panel in advance to increase the working angle between the solar panel and the relay antenna;

[0016] After completing the measurement, control and tracking, the angle deviation of the solar panels can be compensated in time.

[0017] According to one aspect of the present invention, the process of pre-planning the rotation strategy of the solar panel according to the measurement, control and tracking window set in S200 includes:

[0018] Based on the spacecraft's orbital attitude, the relay antenna installation position, the relay satellite's orbital position constraints, the measurement and control tracking window set, and the solar panel's rotation parameters, the GNC issues a stop control command to the solar panel before entering the relay protection area, causing the solar panel to stop control for a period of time in advance to achieve an angle deviation that meets energy balance requirements;

[0019] After completing the measurement, control and tracking, the angle deviation of the solar panels can be compensated in time.

[0020] According to one aspect of the present invention, the S300 includes:

[0021] According to the constraints of the spacecraft orbit attitude, the relay antenna installation position, the EIRP and G / T value of the spacecraft relay terminal, the relay satellite orbit position, the EIRP and G / T value of the relay satellite and the sailboard shielding window set, the tracking and control link relay signal V is monitored in real time on orbit. AGC The quality of the solar panel relay signal is obtained.

[0022] According to one aspect of the present invention, the real-time monitoring further includes recording the monitoring parameters of the return link ground terminal station C / N0 in real time.

[0023] According to one aspect of the present invention, the process of obtaining the solar panel relay signal trend atlas includes:

[0024] Before and after each relay link signal interruption event, the corresponding angle between the solar panel and the relay link and the corresponding relay signal V are constructed. AGC After a long period of observation and accumulation of a large number of line types, a two-dimensional curve between them is obtained through machine learning to screen out typical line types and construct a training set of signal trend graphs as a reference for the occlusion ratio test;

[0025] During the on-orbit test, the signal line shape of the training set was further screened and updated by combining machine learning methods to cover the angle range between the solar panels and the relay links.

[0026] According to one aspect of the present invention, the least square method is used in S400 to fit the curve of the solar panel relay signal trend atlas to determine whether the trend of the solar panel relay signal is consistent with or completely identical to the trend of the solar panel shielding relay signal historical trend atlas.

[0027] According to one aspect of the present invention, the rotation strategy of the solar panel dynamically adjusted in S400 includes: immediately sending an instruction to adjust the rotation rate to the solar panel so that the solar panel deviates from the obstruction area it is about to enter and avoids interruption of the measurement and control link signal.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] According to the present invention, a set of solar panel obstruction windows is first obtained through pre-planning. Then, a corresponding set of panel obstruction signal trend graphs is obtained during each tracking cycle through real-time monitoring. The impact of panel rotation on link communications is predicted using historical data, and the solar panel rotation strategy is dynamically optimized and addressed. Combining pre-planning with real-time monitoring, the solar panel rotation strategy is optimized from preliminary to precise, achieving a balance between complexity and accuracy. This ensures that the solar panels operate according to established rules most of the time, providing the necessary energy support, and ensuring the availability of the measurement and control link to safeguard flight control missions. Therefore, this method can significantly improve the long-term operational control efficiency of space missions while on orbit, offering significant benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] To more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be derived from these drawings without inventive effort.

[0031] Figure 1 A flowchart schematically illustrates an implementation of a method for optimizing spacecraft solar panel rotation based on measurement and control link availability measurement disclosed in an embodiment of the present invention;

[0032] Figure 2 A mathematical model schematically illustrates a relay tracking scenario for a multi-compartment spacecraft with rotating solar panels, as disclosed in an embodiment of the present invention;

[0033] Figure 3 Schematically showing the azimuth and elevation angles of the solar panel during rotation according to an embodiment of the present invention in the coordinate system of the relay antenna in compartment C;

[0034] Figure 4 Schematically represents the intersection curve between the visible range of the relay antenna disclosed in an embodiment of the present invention and the solar sail disk of compartment A;

[0035] Figure 5 Schematically represents the intersection curve between the visible range of the relay antenna disclosed in an embodiment of the present invention and the solar sail disk of compartment B;

[0036] Figure 6 Schematically showing the vector of a spacecraft disclosed in an embodiment of the present invention Typical changes over time t;

[0037] Figure 7 Schematic representation of the relay link angle δ and the relay AGC signal variable V disclosed in the embodiment of the present invention AGCThe fitting curve of the changing trend of

[0038] Figure 8 The following schematically illustrates an implementation example of a spacecraft solar panel rotation optimization method based on measurement and control link availability measurement disclosed in an embodiment of the present invention. DETAILED DESCRIPTION

[0039] The description of the embodiments in this specification should be combined with the corresponding drawings, which should be considered a complete part of this specification. In the drawings, the shapes and thicknesses of the embodiments may be exaggerated and indicated for simplicity or convenience. Furthermore, the various structural components in the drawings will be described separately. It is worth noting that components not shown in the drawings or not described in words are known to those of ordinary skill in the art.

[0040] The description of the embodiments herein and any references to directions and orientations are for ease of description only and are not to be construed as limiting the scope of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination. The present invention is not specifically limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0041] like Figure 1 and Figure 8 As shown, according to the concept of the present invention, in order to further improve the availability of the ground-to-space wireless measurement and control link and minimize the signal shielding effect of solar panel rotation on the measurement and control link while meeting energy requirements, this embodiment conducts in-depth research on related methods for optimizing spacecraft solar panel rotation and discloses a spacecraft solar panel rotation optimization method based on measurement of measurement and control link availability. The implementation of this method specifically includes the following steps:

[0042] S100, obtaining a measurement and control tracking window set through a measurement and control link budget;

[0043] S200, pre-planning a rotation strategy of the solar panel according to the measurement and control tracking window set, and obtaining a panel shielding window set of the solar panel to the measurement and control link;

[0044] S300, monitoring the signal quality of the measurement and control link in real time based on the solar panel shielding window set and in combination with the solar panel shielding signal historical trend atlas to obtain a solar panel signal trend atlas;

[0045] S400, if the solar panel signal trend is consistent with or identical to the trend of the solar panel shielding signal historical trend atlas, dynamically adjust the rotation strategy of the solar panel;

[0046] S500 , based on the measurement, control and tracking window set, after the current tracking arc segment ends, enter the next measurement, control and tracking window, and repeat S200 to S500 .

[0047] In this embodiment, the tracking window set refers to the set of start and end time periods during which a tracking link can be established between the spacecraft relay terminal and the relay satellite. This can also be referred to as a tracking arc set, specifically in the form of {[t1, t2], [t3, t4], …,}. The solar panel shielding window set refers to the set of start and end time periods during which a solar panel shields the tracking link.

[0048] This embodiment is as follows Figure 2 The method of the present invention is described in detail using a typical case of a solar panel rotation process based on the measurement and control link availability metric. The typical case is a relay tracking scenario when a multi-cabin spacecraft solar panel rotates. The mathematical model of the scenario takes the relay antenna of compartment C as the origin O, the x-axis is positive towards the direction of quadrant IV, the y-axis is positive towards the center of mass of compartment M, and the coordinates of the center of mass of compartment M are (0, L ksa ), the center of mass coordinates of the sailboard in cabin A is (-L mt ,L ksa ), where L mt Indicates the length of compartment A, L ksa represents the distance between the relay antenna in module C and the center of mass of module M. In this case, the TT&C link availability metric is assessed using relay tracking performance. Therefore, in this embodiment, the TT&C link in S100 is the relay link formed between the spacecraft and the relay satellite, in which the spacecraft relay antenna tracks the relay satellite.

[0049] Assuming that the radius of the sailboard in compartment A is R and the rotation angle of the sailboard is β, the Cartesian coordinates of the intersection point G in the relay antenna coordinate system of compartment C are as shown in formula (1):

[0050]

[0051] The intersection point G represents the intersection of the field of view of the relay antenna in compartment C and the disk area formed by the rotation of the solar sail in compartment A. The intersection point is an open curve located in the upper hemisphere in three-dimensional space. Let the observation azimuth angle in the coordinate system of the relay antenna in compartment C be φ G (The positive y-axis direction is 0°, and the positive z-axis changes to a right-handed system), the pitch angle is θ G (parallel to the xOy plane is 0°, and the positive z axis is 90°), such as Figure 2 As shown, we have:

[0052]

[0053] Combining formula (1) and formula (2), we can know that the azimuth angle φ G , pitch angle θ GThe sailboard rotation angle is a function of β. As β rotates in the upper half space, the azimuth and pitch angle change curves can be obtained as follows: Figure 3 shown.

[0054] It can be further obtained that as the solar sail panel rotates, the intersection curve between the visible range of the relay antenna and the solar sail panel disk (expressed in azimuth and pitch angle) is as follows Figure 4 As shown, the area enclosed by the curve and the horizontal coordinate (azimuth) (i.e., the gray shaded area in the figure) has potential sailboard shielding events, which requires attention and investigation in the flight procedure arrangement; other areas do not have sailboard shielding situations and can be used as preferred arc segments for the key flight control process.

[0055] Since compartment A and compartment B are mirror-symmetric with respect to the y-axis, the above analysis is also applicable to compartment B located in quadrant II, where the intersection curve between the visible range of the relay antenna and the solar sail disk is as follows: Figure 5 As shown, the area enclosed by the curve and the abscissa (ie, the grey shaded area in the figure) has potential windsurfing event.

[0056] The above S100 includes: performing measurement, control and tracking calculations based on the relay satellite orbital position, spacecraft orbital attitude, and relay antenna installation position constraint information in combination with orbital dynamics to obtain a measurement, control and tracking window set.

[0057] The rotation strategy of the solar panels of a typical multi-compartment spacecraft is to orient toward the sun. During the forward flight of the orbital system, the solar panels will return to their initial position after accompanying the spacecraft in one orbital flight. The typical operating parameters are shown in Table 1.

[0058] Table 1 Typical operating parameters of solar panels on multi-compartment spacecraft

[0059]

[0060] Furthermore, to ensure the scalability of solar array operations, the spacecraft will reduce strong constraints on solar orientation under energy balance conditions. Initial consideration is to maintain a safety margin of 0° to 30°, providing design input for strategy optimization. It should be noted that the specific safety margin depends on the GNC control strategy of different spacecraft models and does not limit the scope of protection of this invention.

[0061] Since the relay satellite is located in the geosynchronous orbit, the number of orbital elements remains basically unchanged during the long-term operation of the spacecraft in orbit. Therefore, the visible vector between the spacecraft relay antenna and the relay satellite is a predictable time-varying variable, which is set as in represents the spatial coordinate of the spacecraft relay antenna i, r j Represents the spatial coordinates of relay satellite j. Further, this vector can be used to represent the relay antenna azimuth φG , pitch angle θ G The spatial distance r is expressed as function Where r is irrelevant to the analysis of the present invention, it can be simplified to The origin of the coordinate system is located at the center of mass of the relay antenna.

[0062] This embodiment takes the case of the relay antenna in the spacecraft compartment C tracking the relay satellite as an example. In this coordinate system, the vector Typical changes over time t are as follows Figure 6 As shown. Assuming that the solar panel of the spacecraft is about 6m wide and about 23m long, the resulting shielding angle is about 15°. It can be seen that for effective communication, the angle between the direction of the relay antenna and the plane where the panel is located should be no less than 15°. For other embodiments, the specific angle range between the direction of the relay antenna and the plane where the solar panel is located is related to the orbital position of the spacecraft and the position of the relay satellite, and does not limit the scope of protection of the present invention. Figure 6 It can be seen that within the visible range of the relay (when the right vertical axis value corresponding to the light gray curve is less than 0°), there is a situation where the solar sail enters the angle between the two 15° (the left vertical axis value used by the dark black curve is less than 15°), that is, Figure 6 In the area shown in the box, the solar panels will block the relay tracking, and reasonable control is required to ensure the reliable implementation of measurement, control and tracking.

[0063] Therefore, in some embodiments, the process of pre-planning the rotation strategy of the solar panel based on the measurement, control, and tracking window set in S200 includes: pre-setting a deviation angle for the solar panel to increase the working angle between the solar panel and the relay antenna based on the spacecraft orbital attitude, the relay antenna installation position, the relay satellite orbital position constraint information, the measurement, control, and tracking window set, and the solar panel rotation parameters, in combination with the spacecraft cabin energy balance constraint requirements; and compensating for the angle deviation of the solar panel in a timely manner after the measurement, control, and tracking are completed to ensure that it does not affect subsequent mission operations. This compensation algorithm should meet relevant dynamic constraints.

[0064] In other embodiments, during long-term on-orbit flight, the process of pre-planning the solar panel rotation strategy based on the measurement, control, and tracking window set in S200 includes: based on the spacecraft's orbital attitude, the relay antenna installation position, the relay satellite's orbital position constraints, the measurement, control, and tracking window set, and the solar panel rotation parameters; before entering the relay protection zone, the GNC issues a stop control command to the solar panel, causing the solar panel to stop control for a period of time in advance to achieve an angular deviation that meets energy balance requirements; and after the measurement, control, and tracking are completed, timely compensating for the solar panel angular deviation to ensure that it does not affect subsequent mission operations. This compensation algorithm should meet relevant dynamic constraints.

[0065] The above two processes of pre-planning the rotation strategies of the solar panels achieve a balance between measurement and control and energy.

[0066] However, due to varying degrees of accuracy deviation in spacecraft orbit and attitude predictions, and the uncertainty of time delays in starting, rotating, and stopping solar panels, there may be discrepancies between planned and actual operations, potentially leading to the loss of effective tracking and control segments and unpredictable risks for ground-based flight control. Therefore, it is necessary to monitor the impact of panel rotation on the signal quality of the tracking and control link online, and dynamically adjust subsequent rotation strategies based on orbital attitude predictions to further improve the reliability of the tracking and control link.

[0067] In some embodiments, the above S300 includes: monitoring the tracking link relay signal V in real time on orbit based on the spacecraft orbit attitude, the relay antenna installation position, the EIRP and G / T value of the spacecraft relay terminal, the relay satellite orbit position, the EIRP and G / T value constraints of the relay satellite, and the sail shielding window set. AGC The system monitors the quality of the solar panel relay signal and generates a trend chart of the solar panel relay signal. In addition to real-time monitoring of the forward link relay signal, it also records the C / N0 monitoring parameters of the return link ground terminal station. When C / N0 falls below a certain threshold, the return link is considered unavailable. When VAGC falls below a certain threshold, the forward link is considered unavailable.

[0068] Specifically, the solar panel relay signal trend atlas is obtained through on-orbit real-time monitoring, that is, the (δ, V AGC ) constructs the corresponding two-dimensional curve, namely the angle δ between the solar panel and the relay link and its corresponding relay forward AGC signal V AGC After accumulating a large number of line types through long-term observation, typical line types are screened through machine learning to construct a training set of signal trend graphs as a reference for subsequent occlusion ratio judgment tests.

[0069] During the on-orbit test, the signal line shape of the training set was further screened and updated by combining machine learning methods, striving to cover the value range of the angle δ between the solar panel and the relay link [0°, 15°].

[0070] The least squares method is used to fit the curve of the solar panel relay signal trend atlas to determine whether the trend of the solar panel relay signal is consistent with or completely identical to the trend of the panel shielding relay signal historical trend atlas. Furthermore, a second-order polynomial fitting is used, and the judgment parameters are the quadratic term coefficient, the first-order term coefficient, and the constant term obtained after fitting. The judgment method is as follows: the constant term is used for base judgment. Under normal circumstances, the shielding event process occurs under the premise that the AGC voltage is lower than the set threshold; the first-order term and the second-order term are used for trend judgment. The minimum square error of the corresponding coefficients of each standard curve is calculated by weighting. If the result is less than the threshold, it can be considered to be convergent. By comparing the relay link angle δ with the relay forward signal V AGC Example V of a two-variable quadratic function AGC =-0.0118·δ 2 +0.356·δ-0.0095 was analyzed and verified, and the results were as follows Figure 7 The fitting curve of the solar panel relay signal trend shown in FIG. 1 shows that as the angle variable δ becomes smaller, the AGC signal variable V AGC The value of is also getting smaller and smaller, reflecting that the quality of the received signal is declining and the impact of the sailboard blocking is getting bigger and bigger until the signal is interrupted.

[0071] Real-time monitoring requires high processing power from the spacecraft on-orbit, thus increasing the complexity of on-orbit processing. This invention combines pre-planning with real-time monitoring to optimize the rotation of the solar panels from preliminary to precise, achieving a balance between complexity and accuracy.

[0072] In some embodiments, if the solar panel relay signal trend is determined to be consistent with or identical to the trend in the historical trend atlas of the solar panel shielding relay signal, it is determined that the current solar panel rotation strategy is about to or has already caused an obstruction to the communication of the relay link and needs to be optimized. The dynamically adjusted solar panel rotation strategy in S400 includes immediately sending a rotation rate adjustment instruction to the solar panel, thereby accelerating, decelerating, or stopping the solar panel to deviate from the obstruction area it is about to enter, thereby avoiding the interruption of the measurement and control link signal that may be caused by the original rotation strategy. The specific operational measures are coupled with the line type of the fitted solar panel relay signal trend atlas, that is, different line types correspond to different operational strategies.

[0073] In some embodiments, before entering the next tracking window in the above S500 , the rotation parameters of the solar panel need to be switched to an initial state.

[0074] The serial numbers of the above-mentioned steps involved in the method of the present invention do not necessarily mean the order of execution of the method. The execution order of each step should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiment of the present invention.

[0075] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A solar panel rotation optimization method based on measurement and control link availability measurement, comprising: S100, obtaining a measurement and control tracking window set through a measurement and control link budget; S200, pre-planning a rotation strategy of the solar panel according to the measurement and control tracking window set, and obtaining a panel shielding window set of the solar panel to the measurement and control link; S300, monitoring the signal quality of the measurement and control link in real time according to the solar panel shielding window set and in combination with the solar panel shielding signal historical trend atlas to obtain a solar panel signal trend atlas; S400, if the solar panel signal trend is consistent with or identical to the trend of the solar panel shielding signal historical trend atlas, dynamically adjust the rotation strategy of the solar panel; S500 , based on the measurement, control and tracking window set, after the current tracking arc segment ends, enter the next measurement, control and tracking window, and repeat S200 to S500 .

2. The method according to claim 1, characterized in that The tracking and control link in S100 is a relay link formed between the spacecraft and the relay satellite, in which the spacecraft relay antenna tracks the relay satellite.

3. The method according to claim 2, characterized in that The S100 includes: performing measurement, control and tracking calculations based on the relay satellite orbital position, the spacecraft orbital attitude and the relay antenna installation position constraint information in combination with orbital dynamics to obtain a measurement, control and tracking window set.

4. The method according to claim 2, characterized in that The process of pre-planning the rotation strategy of the solar panel according to the measurement, control and tracking window set in S200 includes: Based on the spacecraft orbital attitude, the relay antenna installation position, the relay satellite orbital position constraint information, the measurement and control tracking window set and the solar panel rotation parameters, combined with the spacecraft cabin energy balance constraint requirements, a deviation angle is preset for the solar panel in advance to increase the working angle between the solar panel and the relay antenna; After completing the measurement, control and tracking, the angle deviation of the solar panels can be compensated in time.

5. The method according to claim 2, characterized in that The process of pre-planning the rotation strategy of the solar panel according to the measurement, control and tracking window set in S200 includes: Based on the spacecraft's orbital attitude, the relay antenna installation position, the relay satellite's orbital position constraints, the measurement and control tracking window set, and the solar panel's rotation parameters, the GNC issues a stop control command to the solar panel before entering the relay protection area, causing the solar panel to stop control for a period of time in advance to achieve an angle deviation that meets energy balance requirements; After completing the measurement, control and tracking, the angle deviation of the solar panels can be compensated in time.

6. The method according to claim 2, characterized in that The S300 includes: According to the constraints of the spacecraft orbit attitude, the relay antenna installation position, the EIRP and G / T value of the spacecraft relay terminal, the relay satellite orbit position, the EIRP and G / T value of the relay satellite and the sailboard shielding window set, the tracking and control link relay signal V is monitored in real time on orbit. AGC The quality of the solar panel relay signal is obtained.

7. The method according to claim 6, characterized in that The real-time monitoring also includes real-time recording of monitoring parameters of the return link ground terminal station C / N0.

8. The method according to claim 6, characterized in that The process of obtaining the solar panel relay signal trend atlas includes: Before and after each relay link signal interruption event, the corresponding angle between the solar panel and the relay link and the corresponding relay signal V are constructed. AGC After a long period of observation and accumulation of a large number of line types, a two-dimensional curve between them is obtained through machine learning to screen out typical line types and construct a training set of signal trend graphs as a reference for the occlusion ratio test; During the on-orbit test, the signal line shape of the training set was further screened and updated by combining machine learning methods to cover the angle range between the solar panels and the relay links.

9. The method according to claim 8, characterized in that In S400, the least square method is used to fit the curve of the solar panel relay signal trend atlas to determine whether the trend of the solar panel relay signal is consistent with or completely identical to the trend of the solar panel shielding relay signal historical trend atlas.

10. The method according to claim 1 or 2, characterized in that The dynamic adjustment of the rotation strategy of the solar panel in S400 includes: immediately sending a command to adjust the rotation rate to the solar panel, so that the solar panel deviates from the shielding area it is about to enter, and avoids interruption of the measurement and control link signal.

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