Method for judging orientation of sailboard in abnormal state of satellite sailboard structure

Abstract

The invention discloses a method for judging the orientation of a sailboard in an abnormal state of a satellite sailboard structure, which can comprehensively consider different sunlight incident angles and corresponding generating capacity data, reduce errors and accurately and quickly judge the damage condition of the sailboard and the actual orientation of the sailboard. The method comprises the following steps: in an abnormal state of a satellite sailboard structure, determining whether a satellite sailboard is unfolded and flattened to the maximum extent or not according to a satellite design standard and satellite telemetering, and if so, calculating satellite control parameters and controlling a satellite to adjust the attitude according to a current attitude; in the satellite attitude adjusting process, the sailboard power generation capacity and the sun vector of a satellite body system in the satellite attitude adjusting process are obtained; establishing an equation set among a satellite sun vector matrix, a satellite panel normal vector and a generating capacity vector, and performing linear fitting by using a least square method; and evaluating the normal vector of the sailboard of the satellite by minimizing the sum of squares of errors, and carrying out normalization processing, so that the vector can be regarded as a sailboard pointing representation under a body coordinate system.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft flight control, and particularly to a method for judging the pointing of a satellite solar panel under abnormal conditions of the satellite solar panel structure. Background Art

[0002] The power generation of the solar panel directly determines the energy supply of the satellite. After the satellite is put into orbit, whether the solar panel works properly is the key to the success or failure of subsequent flight missions. With the increase in space missions, it is common for the solar panel to work abnormally after the satellite is put into orbit. Figure 1 Fig. is a schematic diagram of the incident sunlight and the normal vector of the solar panel (when the power generation of the solar panel is zero); when the satellite solar panel structure is in an abnormal state for a long time, the telemetry data characterizing the relevant state of the solar panel may be missing or inaccurate. It is not ideal, or even very difficult, to directly judge the state of the satellite solar panel through relevant telemetry parameters (such as the satellite body-fixed solar vector X, Y, Z, etc.) according to the inherent design mode. Therefore, it is urgent to design a new judgment mode according to the actual abnormal situation to accurately evaluate the attitude and pointing under the abnormal state of the solar panel structure and solve the problem of evaluating the expected damaged state of the solar panel after the satellite is put into orbit.

[0003] The existing solutions generally use the satellite body-fixed solar vector when the power generation of the solar panel is zero directly as the pointing of the satellite solar panel. This is only a special case and cannot comprehensively reflect the relationship between the normal vector of the solar panel, the solar vector, and the power generation. There may be a large error, so it is impossible to accurately and quickly judge the damaged situation of the solar panel and the actual pointing of the solar panel. Summary of the Invention

[0004] In view of this, the present invention provides a method for judging the pointing of a satellite solar panel under abnormal conditions of the satellite solar panel structure, which can comprehensively consider different incident angles of sunlight and the corresponding power generation data, reduce errors, and accurately and quickly judge the damaged situation of the solar panel and the actual pointing of the solar panel.

[0005] To achieve the above object, the technical solution of the present invention is a method for judging the pointing of a satellite solar panel under abnormal conditions of the satellite solar panel structure, including the following steps:

[0006] Step 1. Under the abnormal condition of the satellite solar panel structure, determine whether the satellite solar panel has been fully deployed and flattened according to the satellite design standard and satellite telemetry. If so, enter Step 2.

[0007] Step 2: Calculate the satellite control parameters according to the current attitude, and control the satellite to adjust its attitude. During the satellite attitude adjustment process, obtain the power generation of the solar panel and the satellite body-fixed solar vector during the satellite attitude adjustment process.

[0008] Step 3: Establish a system of equations between the satellite solar vector matrix S, the satellite solar panel normal vector n, and the power generation vector E, and perform linear fitting using the least squares method.

[0009] Step 4: By minimizing the sum of squared errors, evaluate the normal vector n of the satellite solar panel. After normalization, it can be regarded as the representation of the solar panel pointing in the body coordinate system.

[0010] Further, step 2 is specifically as follows:

[0011] S201: Obtain comprehensive data on the solar incidence angle and corresponding power generation, covering the solar incidence angles corresponding to zero actual power generation and maximum power generation under abnormal structures. Specifically: The satellite body coordinate system includes the X-axis, Y-axis, and X-axis; adjust the +Z-axis of the satellite to face the sun, and the +Z-axis direction is the positive direction of the Z-axis of the satellite body coordinate system; control the satellite to be offset relative to the sun around the X-axis, and the offset angle gradually increases from 0 degrees to 90 degrees in a set fixed step; then adjust the -Z-axis of the satellite to face the sun, and control the satellite to be offset relative to the sun around the X-axis, and the offset angle gradually increases from 0 degrees to 90 degrees in a set fixed step; thereby obtain the solar vector S and the corresponding power generation E. A set of obtained solar vectors constitutes a matrix S, and the corresponding power generation E constitutes a vector E.

[0012] Further, after S201 in step 2, the following steps are also included:

[0013] S202: Judge whether the difference between the obtained maximum power generation and the maximum power generation of the inherent design is within the set range. If so, ignore the deviation in the Y-axis dimension and execute S203; otherwise, on the basis of the offset attitude corresponding to the above maximum power generation, continue the offset attitude adjustment process around the Y-axis, that is: control the satellite to be offset relative to the sun around the Y-axis, and the offset angle gradually increases from 0 degrees to 90 degrees in a set fixed step; then adjust the -Z-axis of the satellite to face the sun, and control the satellite to be offset relative to the sun around the Y-axis, and the offset angle gradually increases from 0 degrees to 90 degrees in a set fixed step; thereby update the solar vector S and the corresponding power generation E, and obtain a set of updated solar vector matrix S and updated power generation vector E.

[0014] S203: Continue to judge whether the difference between the new maximum power generation and the maximum power generation of the inherent design is within the set range. If so, continue to execute step 3; otherwise, judge whether the variation law of the solar vector and power generation is consistent with the normal situation. If it is consistent, the method of the present invention is still applicable, but the solar panel is severely damaged and the maximum power generation is limited, and continue to execute step 3; otherwise, the method of the present invention is no longer applicable and the process ends.

[0015] Further, step 3 is specifically as follows:

[0016] S301: The solar vector S(s x ,s y ,s z ) and the solar panel normal n(n x ,ny , n z The dot product S·n of ) and the power generation E has a linear relationship. Since S·n = s x n x+ s y n y+ s z n z , from which a system of equations E = k(s x n x+ s y n y+ s z n z ) is constructed, and the problem is transformed into solving the solution of the system of equations. Where k is a constant, usually related to the sail area, solar cell conversion coefficient, solar constant, and sun-star distance.

[0017] S302: The dimension of the solar vector matrix S is (n, 3), where n is the total number of solar vectors in the matrix, and the dimension of the power generation vector E is (n, 1). The problem is transformed into solving the unknown vector n (n x , n y , n z ) such that the difference between S·n and E is minimized. The least squares method is used to fit the relationship between the feature S·n and the power generation E, by minimizing the sum of squared errors For the value of i from 1 to n, find the optimal solution of the vector n (n x , n y , n z ).

[0018] Furthermore, the sailboard pointing judgment method is applied to a satellite with two-wing sailboards, namely the +Y solar wing and the -Y solar wing, which can rotate 360 degrees around the Y axis. In the normal state, the sailboard is parallel to the satellite XOY plane, and the normal direction of the sailboard points to the z-axis direction of the satellite body.

[0019] Furthermore, the abnormal states of the sailboard structure of the satellite in this method are manifested as: the root connection between the sailboard and the satellite body, abnormal points on the main structure of the sailboard, the sailboard is fully deployed, the inner and outer plates are flattened, and relatively stable; there is one or more abnormal points coexisting.

[0020] Furthermore, the actual impact of the abnormal state of the satellite sailboard structure is manifested as: the telemetry value of the solar vector in the satellite body coordinate system cannot directly and accurately reflect the actual relationship between the normal direction of the sailboard and the incident angle of sunlight, the sailboard and the satellite body xoy plane are not coplanar, and there are deviations in the x and y directions, and this deviation is reflected through the power generation.

[0021] Beneficial effects:

[0022] (1) A method for judging the pointing of a satellite solar panel under abnormal structural conditions provided by the present invention is aimed at the situation where, after the satellite solar panel is fully deployed and flattened, there are still deviations from the normal structure, and there are abnormal structural conditions with degrees of freedom in the x and y axis directions. This method proposes a bias attitude control by sequentially rotating around the x-axis and y-axis under the condition that the Z-axis is facing the sun, so as to obtain the solar vector and power generation data under abnormal structural conditions. This attitude adjustment scheme can maximize the power generation capacity of the solar panel structure under abnormal conditions, thereby exerting the maximum efficiency. This method can comprehensively consider the situation of different incident angles of sunlight, use the data reflecting the complete law for fitting and solving, and reduce errors. This method makes the most use of the variation laws of the relevant flight model telemetry parameters and relevant telemetry data of the satellite solar panel that are not affected by the abnormal points of the solar panel, and is used to judge the situation of the solar panel being deployed and flattened in place, and to define the abnormal structure and the abnormal influence area. Therefore, the present invention realizes the comprehensive consideration of different incident angles of sunlight and the corresponding power generation data, reduces errors, and accurately and quickly judges the damaged situation of the solar panel and the actual pointing of the solar panel.

[0023] (2) A method for judging the pointing of a satellite solar panel under abnormal structural conditions provided by the present invention, the calculated pointing of the solar panel is represented by the body coordinate system, which can be regarded as the basic pointing deviation of the abnormal structural state of the solar panel. In subsequent flight control, the target attitude parameters can be calculated and converted on this basis.

[0024] (3) A method for judging the pointing of a satellite solar panel under abnormal structural conditions provided by the present invention, the abnormal structure of the satellite solar panel is general, so in the face of different abnormal structural situations of the solar panel, this method has strong applicability. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 Schematic diagram of incident sunlight and the normal of the solar panel (when the power generation of the solar panel is zero);

[0026] Figure 2 Schematic diagram of the attitude adjustment profile;

[0027] Figure 3 Schematic diagram of the relative position between the solar panel and the satellite body;

[0028] Figure 4 Flowchart of the method for judging the pointing of the satellite solar panel under abnormal structural conditions;

[0029] Figure 5 Relationship diagram between the power generation of the satellite solar panel and the solar vector in the satellite body coordinate system;

[0030] Figure 6 Diagram of the power generation of the satellite solar panel and the fitted power generation; DETAILED DESCRIPTION OF THE EMBODIMENTS

[0031] The present invention will be described in detail below in conjunction with the accompanying drawings and by way of examples.

[0032] Embodiment 1:

[0033] A method for judging the pointing of a satellite solar panel in an abnormal state of the satellite solar panel structure. The method for judging the pointing of the solar panel is applied to a satellite with double-wing solar panels, namely, the +Y solar wing and the -Y solar wing, which can rotate 360 degrees around the Y-axis. In the normal state, the solar panel is parallel to the XOY plane of the satellite, and the normal direction of the solar panel points to the z-axis direction of the satellite body. The relative position between the solar panel and the satellite body is as Figure 3 shown.

[0034] The present invention provides a method for judging the pointing of a satellite solar panel in an abnormal state of the satellite solar panel structure, and the process is as Figure 4 shown. It should be noted that the steps shown in the flowchart can be executed in a computer system in the form of a set of computer-executable instructions. And although the logical order is shown in the flowchart, in some cases, it can be executed in a different order from here.

[0035] The method includes the following steps:

[0036] Step 1. In the abnormal state of the satellite solar panel structure, based on the satellite design standard and combined with satellite telemetry, determine whether the satellite solar panel has been fully deployed and flattened to the maximum extent through satellite telemetry. If so, enter Step 2;

[0037] Step 2: Calculate the satellite control parameters according to the current attitude, and control the satellite to adjust its attitude; during the satellite attitude adjustment process, obtain the power generation of the solar panel and the solar vector in the satellite body coordinate system during the satellite attitude adjustment process. In the embodiment of the present invention, the specific process of Step 2 is as follows:

[0038] S201: Obtain comprehensive solar incidence angle and corresponding power generation data, covering the solar incidence angles corresponding to zero actual power generation and maximum power generation under abnormal structures. Specifically: The satellite body coordinate system includes the X-axis, Y-axis, and X-axis; adjust the +Z-axis of the whole satellite to face the sun, and the +Z-axis direction is the positive direction of the Z-axis of the satellite body coordinate system; control the satellite to be offset by an angle around the X-axis to face the sun, and the offset angle gradually increases from 0 degrees to 90 degrees in a set fixed step; then adjust the -Z-axis of the whole satellite to face the sun, and control the satellite to be offset by an angle around the X-axis to face the sun, and the offset angle gradually increases from 0 degrees to 90 degrees in a set fixed step; thus obtain the solar vector S and the corresponding power generation E. The obtained set of solar vectors forms a matrix S, and the corresponding power generation E forms a vector E.

[0039] In the embodiment of the present invention, after S201, the following steps are further included:

[0040] S202: Determine whether the maximum power generation value obtained is within the set range from the maximum power generation value of the inherent design. If so, ignore the deviation of the Y-axis dimension and execute S203; otherwise, based on the bias attitude corresponding to the above-mentioned maximum power generation value, continue to perform the bias attitude adjustment process around the Y-axis, that is: control the satellite to be biased around the Y-axis to the sun, and the bias angle gradually increases from 0 degrees to 90 degrees according to the set fixed step size; then adjust the satellite's whole-Z-axis sun state, control the satellite to be biased around the Y-axis to the sun, and the bias angle gradually increases from 0 degrees to 90 degrees according to the set fixed step size; thereby update the solar vector S and the corresponding power generation E, and obtain a set of updated solar vector matrices S and updated power generation vectors E;

[0041] S203: Continue to determine whether the new maximum power generation and the inherent designed maximum power generation are within the set range. If so, continue to execute step 3. Otherwise, determine whether the changing pattern of the solar vector and power generation is consistent with the normal pattern. If they are consistent, continue to execute step 3. Otherwise, the process ends.

[0042] Step 3: Establish a set of equations between the satellite solar vector matrix S, the satellite sailboard normal vector n and the power generation vector E, and use the least squares method for linear fitting; In the embodiment of the present invention, step 4 specifically includes the following steps:

[0043] S301: Sun vector S(s x ,s y ,s z ) and the sailboard normal n(n x ,n y ,n z ) has a linear relationship with the power generation E. Since S·n=s x n x+ s y n y+ s z n z , thus constructing the equation system E = k(s x n x+ s y n y+ s z n z ), the problem is transformed into a solution to a set of equations. Among them, k is usually related to the area of ​​the sailboard, the conversion coefficient of the solar cell, the solar constant, and the distance between the sun and the star. The solar energy conversion coefficient is related to factors such as the temperature, attenuation performance and surface dust of the solar energy. The solar constant refers to the solar radiation energy value received per unit practice and per unit area on a vertical plane. The present invention regards these factors as constants, and finds the data relationship between the solar incidence angle and the power generation under the condition of controlling these factors.

[0044] S302: It is represented by a matrix as follows. The dimension of the solar vector matrix S is (n, 3), where n represents the total number of data sets obtained, which can also be understood as obtaining n sets of continuously changing solar vectors; the power generation vector E has a dimension of (n, 1), and the unknown vector n (n x , n y , n z ) is to be found such that the difference between S·n and E is minimized;

[0045]

[0046] S303: Use the least squares method to fit the relationship between the feature S·n and the power generation E, by minimizing the sum of squared errors For i taking values from 1 to n, find the optimal solution of the vector n (n x , n y , n z ).

[0047] Step 4: By minimizing the sum of squared errors, evaluate the satellite solar panel normal vector n, and after normalization, it can be regarded as the representation of the solar panel pointing in the body coordinate system.

[0048] The abnormal state of the solar panel structure of this method applied to a satellite is manifested as: the root connection between the solar panel and the satellite body, abnormal points on the main structure of the solar panel, the solar panel is fully deployed, the inner and outer panels are flattened, and relatively stable; there is one or more abnormal points coexisting. The actual impact of the abnormal state of the satellite solar panel structure is manifested as: the telemetry value of the solar vector in the satellite body coordinate system cannot directly and accurately reflect the actual relationship between the normal direction of the solar panel and the incident angle of sunlight, the solar panel and the xoy plane of the satellite body are not coplanar, there are deviations in the x and y directions, and this deviation is reflected through the power generation.

[0049] Example 2:

[0050] According to Figure 4 the flowchart shown, taking the case where only the root connection between the solar panel and the satellite body is abnormal as an example, the specific steps of this example are as follows:

[0051] Step S1. Determine whether the satellite solar panel is normally deployed based on the satellite design standard and the satellite telemetry parameters. As a core component of the satellite, telemetry parameters and criteria for monitoring the deployment state of the satellite solar panel are designed, such as the deployment criteria and related voltage, current, and temperature telemetry parameters of a certain satellite solar panel, as shown in Table 1 below. Based on the telemetry parameter of the solar panel deployment indication designed on the satellite, and combined with parameters such as the output current, voltage, and substrate temperature of the solar panel, the deployment situation of the solar panel can be judged. These telemetry parameters are not affected by the abnormal root connection, and the telemetry values reflect the real situation.

[0052] (1) Based on the telemetry voltage signal of the solar panel deployment indication, it can be judged whether the solar panel is deployed in place.

[0053] Table 1 Parameters for the Deployment of the Solar Panel

[0054] Status Reference voltage 3.125V Not unfolded 2.359 Connector frame unfolded 1.623 Inner substrate unfolded 2.187 Outer substrate unfolded 2.292 Connector frame and inner substrate unfolded 0.775 Connector frame and outer substrate unfolded 1.339 Inner substrate and outer substrate unfolded 2.084 Connector frame, inner substrate and outer substrate unfolded 0

[0055] (2) Assume that the maximum value of the designed output current of the solar panel is X, the actual output current value Y of the solar panel when the sun shines directly on it, the inner substrate temperature A, and the outer substrate temperature B. If the maximum value of Y is close to X and the change trends of A and B are the same, it can be judged that the hinges between the connecting frame and the inner substrate and between the inner substrate and the outer substrate are locked, and the inner and outer solar panels are flattened in place. If the output current value of the solar panel when the sun shines directly on it is inconsistent with the maximum value of the designed output current of the solar panel, it can be judged that the solar panel is not flattened and there is an angle between the connecting frame and the inner substrate hinge.

[0056] Table 2 Designed Values of Key Parameters of the Solar Panel

[0057]

[0058] In the abnormal state of the satellite solar panel structure, based on the satellite design standard and combined with satellite telemetry, determine whether the satellite solar panel has been deployed and flattened to the maximum extent through satellite telemetry. If so, proceed to step S2;

[0059] Step S2. After judging that the solar panel is deployed in place, due to the abnormality in the connection at the root of the solar panel, the rotation angles in the x-axis and y-axis dimensions cause the pointing of the solar wing panel to be uncertain. According to the current attitude, analyze the satellite attitude mode, calculate the satellite control parameters, and control the satellite to adjust its attitude. First, adjust the satellite's entire body to face the sun in the positive Z direction, and then control the satellite to have a sun offset, with the offset angle gradually increasing from 0 degrees to 90 degrees; adjust the satellite's entire body to face the sun in the negative Z direction, and then control the satellite to have a sun offset, with the offset angle gradually increasing from 0 degrees to 90 degrees. Figure 2 It is a schematic diagram of the attitude adjustment profile.

[0060] During the satellite adjustment process, obtain the telemetry parameter values related to the power generation of the solar panel and the satellite body system solar vector during the satellite attitude adjustment process, and obtain a relationship diagram of the power generation of the satellite solar panel and the satellite body system solar vector as shown in Figure 5 The relationship diagram. They respectively form the solar vector matrix S and the power generation vectors E1 and E2 of the positive Y and negative Y solar panels. At this time, the maximum value of the power generation obtained is already close to the inherent design maximum value, so the attitude adjustment control around the y-axis is not carried out temporarily.

[0061] Step S3. Read the satellite solar vector matrix S and the power generation vectors E1 and E2 of the positive Y and negative Y solar panels, and sequentially perform linear fitting using the least squares method.

[0062] Step S4. Obtain the pointing of the positive Y solar panel as n + (-4.21426, 15.52592, 0.79583), and the pointing of the negative Y solar panel as n -(-4.62844, 16.47254, 1.01022), after normalization, they are n respectively + (-0.26164, 0.96390, 0.04941), n - (-0.27003, 0.96105, 0.05894). Without considering the constant coefficient k, multiply the solar vector matrix S with the vectors n + 、n - respectively for dot product calculation to obtain the fitted power generation. The comparison between the actual power generation and the fitted power generation is as Figure 6 shown. It can be seen from the figure that the variation laws of the fitted power generation and the actual power generation are consistent, indicating that the obtained normal vectors n + 、n - of the sailboard are effective.

[0063] The technical key points of the present invention are as follows:

[0064] (1) For the situation where the sailboard of the satellite is unfolded and flattened as much as possible, and there are deviations in the sailboard structure from the normal state and it can maintain relative stability, the present invention proposes an attitude control scheme, which analyzes the influence of the abnormal sailboard structure as deviations in the x-axis and y-axis dimensions, and then realizes the quantification and characterization of this deviation.

[0065] (2) The present invention emphasizes using the telemetry data and the variation laws of relevant data that are not affected by abnormal points as much as possible to judge the unfolding and flattening conditions of the sailboard, and realize the definition of the abnormal sailboard structure and the analysis of the influence domain.

[0066] (3) The attitude control scheme proposed by the present invention is as follows: First, when facing the sun along the +Z and -Z axes of the body in turn, set the offset angle around the x-axis for attitude control to obtain a set of solar vector and power generation data; if there is a certain gap between the maximum power generation at this time and the maximum power generation of the inherent design, then at the offset attitude of this maximum power generation, continue to set the offset angle around the y-axis for attitude control, and update the solar vector and power generation data. This attitude control scheme can maximize the power generation ability in the case of abnormal sailboard structure.

[0067] (4) The variation laws of the solar vector and power generation data obtained through the attitude adjustment control scheme of the present invention are consistent with those in the case of the normal sailboard structure.

[0068] (5) The present invention uses the solar vector reflecting the complete law and the corresponding power generation data for linear fitting to effectively reduce errors. That is, using the solar vector matrix S (dimension (n, 3)) covering any incident angle and the corresponding power generation vector E (dimension (n, 1)) data to construct a linear equation system s·n = kE, and using the least squares method to solve the unknown vector n (n x , n y , n z ), so that S·n As close as possible to E, and finally normalize the obtained vector n (n x , n y , n z ), which is used as the pointing of the sailboard in the body coordinate system under abnormal structures.

[0069] In summary, the above are only the preferred embodiments of the present invention and are not intended to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A method for determining the direction of a satellite sailboard when the structure of the sailboard is abnormal, characterized in that: The steps include: Step 1. When the satellite sailboard structure is abnormal, determine whether the satellite sailboard has been fully unfolded and flattened according to the satellite design standard and satellite telemetry. If so, proceed to step 2; Step 2: According to the current attitude, calculate the satellite control parameters and control the satellite to adjust its attitude; during the satellite attitude adjustment process, obtain the power generation of the sailboard and the solar vector of the satellite system; Step 3: Establish a set of equations between the satellite solar vector matrix S, the satellite sailboard normal vector n and the power generation vector E, and use the least squares method for linear fitting; Step 4: Evaluate the satellite panel normal vector n by minimizing the sum of squared errors, and after normalization, it can be regarded as a representation of the panel pointing in the body coordinate system.

2. A method for determining the direction of a satellite sailboard when the structure of the satellite sailboard is abnormal as claimed in claim 1, characterized in that: The step 2 is specifically: S201: Obtain comprehensive solar incidence angle and corresponding power generation data, covering the solar incidence angle corresponding to the actual power generation of zero and the maximum power generation under abnormal structure, specifically: the satellite body coordinate system includes X-axis, Y-axis and X-axis; adjust the satellite's +Z-axis state facing the sun, and the +Z-axis direction is the positive direction of the Z-axis of the satellite body coordinate system; control the satellite's X-axis sun offset, and the offset angle gradually increases from 0 degrees to 90 degrees according to the set fixed step size; then adjust the satellite's -Z-axis sun state, control the satellite's X-axis sun offset, and the offset angle gradually increases from 0 degrees to 90 degrees according to the set fixed step size; thereby obtain the solar vector S and the corresponding power generation E, and the obtained set of solar vectors constitutes a matrix S, and the corresponding power generation E constitutes a vector E.

3. A method for determining the direction of a satellite sailboard when the structure of the sailboard is abnormal as claimed in claim 2, characterized in that: The step 2, after S201, further includes the following steps: S202: Determine whether the maximum power generation value obtained is within the set range from the maximum power generation value of the inherent design. If so, ignore the deviation of the Y-axis dimension and execute S203; otherwise, based on the bias attitude corresponding to the above-mentioned maximum power generation value, continue to perform the bias attitude adjustment process around the Y-axis, that is: control the satellite to be biased around the Y-axis to the sun, and the bias angle gradually increases from 0 degrees to 90 degrees according to the set fixed step size; then adjust the satellite's whole-Z-axis sun state, control the satellite to be biased around the Y-axis to the sun, and the bias angle gradually increases from 0 degrees to 90 degrees according to the set fixed step size; thereby update the solar vector S and the corresponding power generation E, and obtain a set of updated solar vector matrices S and updated power generation vectors E; S203: Continue to determine whether the new maximum power generation and the inherent designed maximum power generation are within the set range. If so, continue to execute step 3. Otherwise, determine whether the changing pattern of the solar vector and power generation is consistent with the normal pattern. If they are consistent, continue to execute step 3. Otherwise, the process ends.

4. A method for determining the direction of a satellite sailboard when the structure of the satellite sailboard is abnormal as claimed in claim 3, characterized in that: The determination is as to whether the difference between the obtained maximum power generation and the inherently designed maximum power generation is within a set range, and the set range is within 5% of the inherently designed maximum power generation.

5. A method for determining the direction of a satellite sailboard when the structure of the sailboard is abnormal as claimed in claim 3, characterized in that: The step 3 is specifically: S301: Sun vector S(s x ,s y ,s z ) and the sailboard normal n(n x ,n y ,n z ) has a linear relationship with the power generation E. Since S·n=s x n x+ s y n y+ s z n z , thus constructing the equation system E = k(s x n x+ s y n y+ s z n z ), the problem is transformed into solving the solution of the system of equations, where k is a constant; S302: The dimension of the solar vector matrix S is (n, 3), where n is the total number of solar vectors in the matrix, and the dimension of the power generation vector E is (n, 1). The problem is transformed into solving the unknown vector n(n x ,n y ,n z ), so that the difference between S·n and E is minimized; the relationship between the characteristic S·n and the power generation E is fitted using the least squares method, and the error sum is minimized. The value of i ranges from 1 to n, and we need to find the vector n(n x ,n y ,n z ) is the best solution.

6. A method for determining the direction of a satellite sailboard when the structure of the sailboard is abnormal as claimed in any one of claims 1 to 5, characterized in that: The sailboard pointing judgment method is applied to a satellite whose sailboard is a double-wing, i.e., a +Y solar wing and a -Y solar wing, which can rotate 360 ​​degrees around the Y axis. In a normal state, the sailboard is parallel to the XOY plane of the satellite, and the sailboard normal points to the z-axis direction of the satellite body.

7. A method for determining the direction of a satellite sailboard when the structure of the sailboard is abnormal according to claims 1 to 5, characterized in that: The abnormal state of the sailboard structure of the satellite applied by this method is manifested as: the root connection between the sailboard and the satellite body, the abnormal points of the sailboard main structure, the sailboard is maximally unfolded, the inner and outer plates are flattened, and remain relatively stable; one or more structural abnormal points exist together.

8. The method for determining the direction of a satellite sailboard when the structure of the sailboard is abnormal according to claim 7, characterized in that: The actual impact of the abnormal state of the satellite sailboard structure is manifested as follows: the telemetry value of the solar vector in the satellite body coordinate system cannot directly and accurately reflect the actual relationship between the sailboard normal and the incident angle of the sunlight, the sailboard and the satellite body xoy plane are not coplanar, and there are deviations in the x and y directions, and this deviation is reflected in the power generation.

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