A method for judging the direction of a satellite sailboard when its structure is abnormal

Abstract

The present invention discloses a method for judging the direction of a satellite sailboard when its structure is abnormal. The method can comprehensively consider different sunlight incident angles and corresponding power generation data, reduce errors, and accurately and quickly judge the damage condition of the sailboard and the actual direction of the sailboard. The method includes the following steps: when the satellite sailboard structure is abnormal, according to the satellite design standard combined with satellite telemetry, determine whether the satellite sailboard has been maximally unfolded and flattened by satellite telemetry; if so, 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 sailboard and the solar vector of the satellite system during the satellite attitude adjustment process; establish a set of equations between the satellite solar vector matrix, the satellite sailboard normal vector and the power generation vector, and use the least squares method for linear fitting; by minimizing the sum of squared errors, evaluate the satellite sailboard normal vector, and after normalization, it can be regarded as the sailboard pointing representation in the body coordinate system.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft flight control, and in particular to a method for judging the direction of a satellite sailboard when the sailboard structure is in an abnormal state. Background Art

[0002] The power generation of the windsurfing board directly determines the energy supply of the satellite. After the satellite enters orbit, whether the windsurfing board works normally is the key to the success or failure of the subsequent flight mission. With the increase in space missions, the situation of windsurfing board working abnormally after the satellite enters orbit often occurs. Figure 1 Schematic diagram of incident sunlight and the normal line of the sailboard (when the power generation of the sailboard is zero); when the satellite sailboard structure is in an abnormal state for a long time, the telemetry data representing the relevant state of the sailboard may be missing or inaccurate. The method of directly judging the state of the satellite sailboard through relevant telemetry parameters (such as the satellite's own system solar vector X, Y, Z, etc.) according to the inherent design mode is not ideal and may even be very difficult. Therefore, it is urgent to design a new judgment mode according to the actual abnormal situation to accurately evaluate the attitude and orientation of the sailboard structure in the abnormal state, and solve the problem of evaluating the expected state of the sailboard after the satellite enters orbit.

[0003] Existing solutions generally use the solar vector of the satellite system when the panel's power generation is zero as the direction of the satellite panel. This is only a special case and cannot fully reflect the relationship between the panel normal, solar vector and power generation. There may be large errors, so it is impossible to accurately and quickly judge the damage to the panel and the actual direction of the panel. Summary of the Invention

[0004] In view of this, the present invention provides a method for judging the direction of a satellite sailboard when its structure is abnormal, which can comprehensively consider different sunlight incident angles and corresponding power generation data, reduce errors, and accurately and quickly judge the damage condition of the sailboard and the actual direction of the sailboard.

[0005] To achieve the above-mentioned purpose, the technical solution of the present invention is a method for determining the direction of a satellite sailboard when the sailboard structure is in an abnormal state, comprising the following steps:

[0006] 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 standards and satellite telemetry. If so, proceed to step 2.

[0007] Step 2: Calculate the satellite control parameters based on the current attitude and control the satellite to adjust its attitude. During the satellite attitude adjustment process, obtain the windshield power generation and the satellite's own solar vector.

[0008] 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.

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

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

[0011] 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 +Z-axis solar state of the satellite, and the +Z-axis direction is the positive direction of the Z-axis of the satellite body coordinate system; control the satellite's solar offset around the X-axis, 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 solar state, control the satellite's solar offset around the X-axis, 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, the obtained set of solar vectors constitutes a matrix S, and the corresponding power generation E constitutes a vector E.

[0012] Furthermore, step 2, after S201, further includes the following steps:

[0013] S202: Determine whether the difference between the obtained maximum power generation and the inherently designed maximum power generation is within the set range. If so, ignore the deviation in the Y-axis dimension and execute S203; otherwise, based on the bias attitude corresponding to the above-mentioned maximum power generation, continue the bias attitude adjustment process around the Y-axis, that is: control the satellite to be biased towards the sun around the Y-axis, and the bias angle gradually increases from 0 degrees to 90 degrees according to the set fixed step size; then adjust the satellite's entire star-Z-axis state towards the sun, control the satellite to be biased towards the sun around the Y-axis, and the bias angle gradually increases from 0 degrees to 90 degrees according to the set fixed step size; thereby updating the solar vector S and the corresponding power generation E, and obtaining a set of updated solar vector matrices S and updated power generation vectors E.

[0014] S203: Continue to determine whether the difference between the new maximum power generation and the inherent designed maximum power generation is within the set range. If so, continue to execute step 3; otherwise, determine whether the change pattern of the solar vector and power generation is consistent with the pattern under normal circumstances. If they are consistent, the method of the present invention is still applicable, but the windsurfing board is seriously damaged and the maximum power generation is limited, so continue to execute step 3; otherwise, the method of the present invention is no longer applicable and the process ends.

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

[0016] S301: Sun vector S(s x ,s y ,s z ) and the sailboard normal n(n x ,ny ,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 a set of equations. Where k is a constant, usually related to the sail panel area, solar cell conversion coefficient, solar constant, and the distance between the sun and the star.

[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. 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.

[0018] Furthermore, the sailboard pointing judgment method is applied to satellites with double-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 XOY plane of the satellite, and the sailboard normal points to the z-axis direction of the satellite body.

[0019] Furthermore, when this method is applied to the abnormal state of the satellite's sailboard structure, it 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 panels are flattened, and remain relatively stable; one or more structural abnormal points exist together.

[0020] Furthermore, the actual impact of the abnormal state of the satellite sail panel 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 sail panel normal and the incident angle of sunlight. The sail panel and the satellite body xoy plane are not coplanar, and there are deviations in the x and y directions. This deviation is reflected in the power generation.

[0021] Beneficial effects:

[0022] (1) The present invention provides a method for judging the direction of a satellite sailboard under abnormal structural conditions. For the situation where the satellite sailboard still deviates from the normal structure after being unfolded and flattened as much as possible, and there are abnormal structural conditions with degrees of freedom in the x- and y-axis directions, the present method proposes a method for biasing the attitude control around the x- and y-axes in sequence when the Z-axis is facing the sun, so as to obtain the solar vector and power generation data under the abnormal structure. The attitude adjustment scheme can maximize the power generation capacity under abnormal sailboard structure conditions, thereby maximizing efficiency. The present method can comprehensively examine the conditions of different solar incident angles, use data that embodies complete laws for fitting and solving, and reduce errors. The present method makes maximum use of the changing laws of satellite sailboard-related positive sample telemetry parameters and related telemetry data that are not affected by the abnormal position of the sailboard, to judge the situation of the sailboard being unfolded and flattened, and to define the abnormal structure and abnormal influence domain. Therefore, the present invention realizes the comprehensive consideration of different solar incident angles and corresponding power generation data, reduces errors, and accurately and quickly judges the damage condition of the sailboard and the actual direction of the sailboard.

[0023] (2) The present invention provides a method for determining the sailboard pointing direction when the satellite sailboard structure is in an abnormal state. The calculated sailboard pointing direction is expressed using the body coordinate system and can be regarded as the basic pointing deviation in the abnormal state of the sailboard structure. In subsequent flight control, the target attitude parameters can be calculated and converted on this basis.

[0024] (3) The present invention provides a method for determining the direction of a satellite sailboard under an abnormal structure. The abnormal structure of the satellite sailboard is general, so the method is highly applicable to sailboards with different abnormal structures. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0026] Figure 2 It is a schematic diagram of the posture adjustment section;

[0027] Figure 3 Schematic diagram of the relative positions of the sailboard and the satellite body;

[0028] Figure 4 This is a flow chart of a method for determining the direction of a satellite sailboard when its structure is abnormal;

[0029] Figure 5 This is the relationship diagram between the power generation of the satellite sailboard and the solar vector of the satellite system;

[0030] Figure 6 The diagram shows the power generation of satellite panels and the fitted power generation. DETAILED DESCRIPTION

[0031] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0032] Example 1:

[0033] A method for determining the orientation of a satellite sailboard when its sailboard structure is abnormal is applied to a satellite with a double-wing sailboard, 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. The relative position of the sailboard and the satellite body is as follows: Figure 3 shown.

[0034] The present invention provides a method for determining the direction of a satellite sailboard when the sailboard structure is abnormal. The process is as follows: Figure 4 It should be noted that the steps shown in the flowchart can be executed in a computer system as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps can be executed in an order different from that shown here.

[0035] The method comprises the following steps:

[0036] Step 1. When the satellite sailboard structure is abnormal, determine whether the satellite sailboard has been fully deployed and flattened according to satellite design standards and satellite telemetry. If so, proceed to step 2.

[0037] Step 2: Calculate satellite control parameters based on the current attitude and control the satellite to adjust its attitude; during the satellite attitude adjustment process, obtain the windsurfing power generation and the satellite's own solar vector during the satellite attitude adjustment process; In this 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 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 +Z-axis solar state of the satellite, and the +Z-axis direction is the positive direction of the Z-axis of the satellite body coordinate system; control the satellite's solar offset around the X-axis, 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 solar state, control the satellite's solar offset around the X-axis, 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, the obtained set of solar vectors constitutes a matrix S, and the corresponding power generation E constitutes a vector E.

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

[0040] S202: Determine whether the difference between the obtained maximum power generation and the inherently designed maximum power generation is within a set range. If so, ignore the deviation in the Y-axis dimension and execute S203; otherwise, based on the bias attitude corresponding to the above-mentioned maximum power generation, continue the bias 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 bias angle gradually increases from 0 degrees to 90 degrees according to a set fixed step size; then adjust the satellite's entire -Z axis relative to the sun state, control the satellite to be offset relative to the sun around the Y-axis, and the bias angle gradually increases from 0 degrees to 90 degrees according to a set fixed step size; thereby updating the solar vector S and the corresponding power generation E, and obtaining a set of updated solar vector matrices S and updated power generation vectors E;

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

[0042] Step 3: Establish a system of equations between the satellite solar vector matrix S, the satellite panel normal vector n, and the power generation vector E, and perform linear fitting using the least squares method. In this 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 solving a system of equations. k is typically related to the panel area, the solar cell conversion coefficient, the solar constant, and the distance between the sun and the sun. The solar conversion coefficient is related to factors such as solar temperature, attenuation, and surface dust. The solar constant refers to the amount of solar radiation energy received per unit area per unit time on a vertical plane. The present invention treats these factors as constants and, while controlling them, seeks a numerical relationship between the solar incidence angle and power generation.

[0044] S302: The matrix is ​​expressed as follows: the solar vector matrix S has a dimension of (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 ), so that the difference between S·n and E is minimized;

[0045]

[0046] S303: Use the least squares method to fit the relationship between the characteristic S·n and the power generation E, by minimizing the sum of squared errors. 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.

[0047] Step 4: Evaluate the satellite panel normal vector n by minimizing the sum of squared errors. After normalization, it can be regarded as the panel pointing representation in the body coordinate system.

[0048] This method is applied to satellite sailboard structural anomalies, manifested as abnormalities at the root link between the sailboard and the satellite body, or at the main sailboard structure. The sailboard is fully extended, with the inner and outer panels flattened and relatively stable. These abnormalities can occur at one or more points. The practical impact of these abnormalities is that the telemetered solar vector in the satellite coordinate system cannot directly and accurately reflect the actual relationship between the sailboard normal and the incident angle of sunlight. The sailboard and satellite body's xoy planes are not coplanar, and there are deviations in the x and y directions. This deviation is reflected in the power generation.

[0049] Example 2:

[0050] according to Figure 4 The flowchart shown takes the case where only the root connection between the sailboard 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's panels are deployed properly based on satellite design standards and telemetry parameters. As core satellite components, panels are designed with telemetry parameters and criteria to monitor their deployment status. For example, the panel deployment criteria and related voltage, current, and temperature telemetry parameters for a particular satellite are shown in Table 1 below. Panel deployment indication telemetry parameters are designed onboard, and combined with parameters such as panel output current, voltage, and panel baseplate temperature, panel deployment status can be determined. These telemetry parameters are unaffected by root link anomalies; the telemetry values ​​reflect the actual situation.

[0052] (1) Based on the telemetry voltage signal indicating the sailboard deployment, it can be determined whether the sailboard is deployed in place.

[0053] Table 1 Windsurfing board deployment parameters

[0054] state Reference voltage 3.125V Not expanded 2.359 Connecting frame expansion 1.623 Inner base plate expansion 2.187 External base plate expansion 2.292 Connecting frame and inner base plate unfold 0.775 Connecting frame and external base plate unfolded 1.339 Inner and outer base boards 2.084 Connecting frame, inner base plate, outer base plate unfolded 0

[0055] (2) Assuming the maximum designed output current of the sailboard is X, the actual output current value of the sailboard when the sun is shining directly on the sailboard is Y, and the inner base plate temperature is A and the outer base plate temperature is B. If the maximum value of Y is close to X, and the change trends of A and B are consistent, it can be determined that the hinges between the connecting frame and the inner base plate and the inner base plate and the outer base plate are locked, and the inner and outer sailboards are flattened. If the output current value of the sailboard when the sun is shining directly on the sailboard is inconsistent with the maximum designed output current of the sailboard, it can be determined that the sailboard is not flattened and there is an angle between the hinges of the connecting frame and the inner base plate.

[0056] Table 2 Design values ​​of key parameters of sailboard

[0057]

[0058] 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 S2.

[0059] Step S2: After the solar panel is deployed, it is determined that an anomaly in the solar panel's base connection causes the solar panel's rotation in the x- and y-axis dimensions to cause uncertainty in its orientation. Based on the current attitude, the satellite's attitude mode is analyzed, satellite control parameters are calculated, and the satellite is controlled to adjust its attitude. First, the satellite's positive Z-sun position is adjusted, and then the satellite's sun bias is controlled, gradually increasing from 0 degrees to 90 degrees. The satellite's negative Z-sun position is adjusted, and then the satellite's sun bias is controlled, gradually increasing from 0 degrees to 90 degrees. Figure 2 It is a schematic diagram of the posture adjustment section.

[0060] During the satellite adjustment process, the power generation of the sailboard and the telemetry parameter values ​​related to the solar vector of the satellite system are obtained, as shown in the following example: Figure 5 The diagram showing the relationship between the satellite's panel power generation and the satellite's own solar vector forms the solar vector matrix S and the positive Y and negative Y panel power generation vectors E1 and E2, respectively. The maximum power generation achieved at this point is close to the inherent design maximum, so attitude control around the y-axis is not currently performed.

[0061] Step S3: Read the satellite solar vector matrix S and the positive Y and negative Y windsurfing panel power generation vectors E1 and E2, and perform linear fitting using the least squares method in turn.

[0062] Step S4. Obtain the positive Y direction of the sailboard as n + (-4.21426,15.52592,0.79583), the negative Y sailboard is pointing to n -(-4.62844, 16.47254, 1.01022), after normalization, they are n + (-0.26164,0.96390,0.04941),n - (-0.27003, 0.96105, 0.05894). Without considering the constant coefficient k, the solar vector matrix S is combined with the vector n + 、n - The fitted power generation is obtained by performing dot multiplication calculations respectively. The actual power generation is compared with the fitted power generation. Figure 6 As shown in the figure, the fitted power generation is consistent with the actual power generation, which shows that the obtained sailboard normal n + 、n - efficient.

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

[0064] (1) Aiming at the situation where the satellite sailboard structure deviates from the normal state and can remain relatively stable after it is unfolded and flattened as much as possible, the present invention proposes an attitude control scheme to analyze the impact of the abnormal sailboard structure as deviations in the x-axis and y-axis dimensions, thereby quantifying and characterizing the deviation.

[0065] (2) The present invention emphasizes the use of telemetry data and related data change patterns that are not affected by abnormal points as much as possible to judge the deployment and flattening of the sailboard, and to achieve the definition of the abnormal structure of the sailboard and the analysis of the impact domain.

[0066] (3) The attitude control scheme proposed in this invention is as follows: first, when the +Z and -Z axes of the main body are aligned with the sun, an offset angle is set around the x-axis to perform attitude control and obtain a set of solar vector and power generation data. If the maximum power generation at this time is slightly different from the inherent design maximum power generation, then, in the offset attitude at this maximum power generation, an offset angle is further set around the y-axis to perform attitude control and update the solar vector and power generation data. This attitude control scheme can maximize the power generation capacity under abnormal conditions of the sailboard structure.

[0067] (4) The variation patterns of the solar vector and power generation data obtained by the attitude control scheme of the present invention are consistent with those under the normal structure of the sailboard.

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

[0069] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent replacements, 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 method for determining the direction of a satellite sailboard when its structure 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 deployed and flattened according to satellite design standards and satellite telemetry. If so, proceed to step 2. Step 2: Calculate the satellite control parameters based on the current attitude and control the satellite to adjust its attitude. During the satellite attitude adjustment process, obtain the windshield power generation and the satellite's own solar vector. Step 3: Create the satellite sun vector matrix , satellite sailboard normal vector and the power generation vector The system of equations between is linearly fitted using the least squares method; Step 4: Evaluate the satellite panel normal vector by minimizing the sum of squared errors , and after normalization, it can be regarded as the sailboard pointing representation in the body coordinate system; The step 2 is specifically as follows: 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 Z-axis; adjust the satellite's +Z-axis solar state, 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 solar 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 solar state, control the satellite's X-axis solar offset, and the offset angle gradually increases from 0 degrees to 90 degrees according to the set fixed step size; thereby obtaining the solar vector And the corresponding power generation , the obtained set of solar vectors constitutes a matrix , the corresponding power generation Composition vector .

2. The method for determining the direction of a satellite sailboard when the sailboard structure is abnormal as claimed in claim 1, characterized in that: S201 and subsequent steps include: S202: Determine whether the difference between the maximum power generation obtained and the maximum power generation of the inherent design is within the set range. 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, continue the bias attitude adjustment process around the Y-axis, that is: control the satellite to be offset around the Y-axis with respect 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 entire star-Z axis state with respect to the sun, control the satellite to be offset around the Y-axis with respect to the sun, and the bias angle gradually increases from 0 degrees to 90 degrees according to the set fixed step size; thereby updating the solar vector And the corresponding power generation , get a set of updated sun vector matrices and the updated power generation vector ; S203: Continue to determine whether the difference between the new maximum power generation and the inherent designed maximum power generation is within the set range. If so, continue to step 3. Otherwise, determine whether the change pattern of the solar vector and power generation is consistent with the normal pattern. If they are consistent, continue to step 3. Otherwise, the process ends.

3. The method for determining the direction of a satellite sailboard when the sailboard structure is abnormal as claimed in claim 2, characterized in that: The determination as to whether the difference between the obtained maximum power generation amount and the inherently designed maximum power generation amount is within a set range is within 5% of the inherently designed maximum power generation amount.

4. A method for determining the direction of a satellite sailboard when its structure is abnormal according to any one of claims 1 to 3, characterized in that: The sailboard pointing judgment method is applied to satellites with double-wing sailboards, i.e., +Y solar wing and -Y solar wing, which can rotate 360 ​​degrees around the Y axis. In the 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.

5. The method for determining the direction of a satellite sailboard when the sailboard structure is abnormal according to any one of claims 1 to 3, 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 deployed, the inner and outer panels are flattened, and remain relatively stable; the abnormal structural points exist at one or more points.

6. The method for determining the direction of a satellite sailboard when the sailboard structure is abnormal according to claim 5, characterized in that: The actual impact of the abnormal state of the satellite sail panel 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 sail panel normal and the incident angle of sunlight. The sail panel and the satellite body xoy plane are not coplanar, and there are deviations in the x and y directions. This deviation is reflected in the power generation.

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