Satellite solar panel configuration and control method

Abstract

The invention provides a satellite solar panel configuration. The satellite solar panel configuration comprises a satellite body, a + Y wing and a-Y wing, the + Y wing and the-Y wing are respectively connected with the star body, each of the + Y wing and the-Y wing comprises a two-dimensional driving structure and a solar panel, and the two-dimensional driving structures can drive the solar panels to rotate in two mutually perpendicular directions; when the + Y wing and the-Y wing are initially unfolded, the solar panel is in the initial position and has a zero rotation angle. The method is used for two-dimensional driving solar panel configuration design and control, so that the solar panel always keeps tracking to the sun, and the energy of the whole satellite is ensured.

Description

Technical Field

[0001] This invention belongs to the field of satellite solar panel technology, specifically relating to a satellite solar panel configuration and control method. More particularly, it relates to a satellite solar panel configuration design and control method, and more specifically, a solar panel configuration design and control method suitable for low-inclination orbit satellites with two-dimensional drive control. Background Technology

[0002] Sun-synchronous orbits have an inclination slightly greater than 90 degrees, and the satellite passes by the Earth's North and South Poles on every orbit. This makes them highly efficient for observing polar regions, but less efficient for observing low and mid-latitude areas. Geosynchronous orbits, on the other hand, have an inclination of 0 degrees, making them suitable for observing fixed areas on Earth. To improve the revisit rate of low-latitude or hotspot regions, satellites use low-inclination orbits. For example, the Fengyun-3G satellite has an inclination of 50°, which increases the frequency of monitoring heavy precipitation in tropical and subtropical regions.

[0003] A sun-synchronous orbit satellite's orbital plane rotates around the Earth's axis, and the satellite's orbit is synchronized with the Earth's revolution around the Sun; a geostationary orbit satellite's position relative to the Earth is fixed. Because the solar altitude angle of sun-synchronous and geostationary orbit satellites varies little and exhibits a clear regularity, solar tracking control can be achieved using only one-dimensional actuation. However, the low-inclination orbit satellites, which are the main focus of this invention, have a much larger variation in solar altitude angle, making solar tracking impossible with only one-dimensional solar panel actuation control without attitude maneuvers.

[0004] A search revealed the following shortcomings in existing related patents: Patent document CN115057009B discloses a rotation guidance method and system for a two-dimensional solar panel drive mechanism, which realizes solar panel drive control by recursively calculating the position vector of the sun in the satellite's own system based on the satellite orbit, but does not involve the specific coordinate system and polarity definition of the solar panel; Patent document CN115057010B discloses a tracking planning control method and system for a two-dimensional solar panel drive mechanism. It utilizes the area of ​​the trapezoid formed by the trapezoidal path curve and the deviation of the solar panel's rotation angle to achieve control through the desired rotation angle of the solar panel. However, it does not involve the solar panel configuration or the related design of using a digital solar sensor to obtain the solar vector. Patent document CN105620794B discloses a reliable method for controlling solar panels to autonomously track the sun. By designing angle thresholds and different control regions, the method controls the rotation of the solar panels and the attitude of the satellite so that the normal of the solar panels points to the sun. However, the control method does not involve two-dimensional drive. Patent document CN211207141U discloses a test system for a solar panel drive mechanism, which involves a motor drive control module, drive mechanism, etc., but does not involve two-dimensional drive polarity and solar panel configuration design. Patent document CN111169665B discloses a solar panel deployment test system and its operation method, which is used for ground deployment tests of solar panels, but does not involve the two-dimensional drive control method of the solar panel.

[0005] Patent document CN221660962U discloses a solar panel deployment mechanism, including a first limiting seat, with an extension assembly on each side of the first limiting seat. Each extension assembly includes a first telescopic member and a second telescopic member. The first telescopic member is installed on one side of the first limiting seat and is used to stabilize the extension of the second telescopic member. The second telescopic member can extend and retract via a drive assembly. The first limiting seat is connected to an adjustable solar panel. This invention utilizes a drive assembly to drive the extension and retraction of the second telescopic member, while simultaneously cooperating with the first telescopic member to maintain the stability of the second telescopic member's extension and retraction. Furthermore, the solar panel can be adjusted without affecting the extension and retraction movement. Compared to existing technologies, this reduces space occupation without the need for guide rails, does not affect satellite launch, and still maintains the stability of the solar panel's extension and retraction process, making it more practical.

[0006] However, patent document CN221660962U does not have a two-dimensional drive method and mutually perpendicular solar panel rotation axes, making it unsuitable for low-inclination orbit satellites. Summary of the Invention

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a satellite solar panel configuration and control method.

[0008] According to the present invention, a satellite solar panel configuration includes: a satellite body, a +Y wing, and a -Y wing; The +Y wing and -Y wing are connected to the star body respectively. Each of the +Y wing and -Y wing includes a two-dimensional drive structure and a solar panel. The two-dimensional drive structure can drive the solar panel to rotate in two mutually perpendicular directions. When the +Y and -Y wings are initially deployed, the solar panels are in their initial positions with zero rotation angle.

[0009] Preferably, the two-dimensional drive structure includes: a main shaft, a connecting rod, and a secondary shaft; The main shaft is located at the first end of the connecting rod and is parallel to the axis of the connecting rod. The secondary shaft is located at the second end of the connecting rod, and the main shaft and the secondary shaft are perpendicular to each other. The connecting rod is rotatably connected to the celestial body via the main shaft and rotatably connected to the solar panels via the secondary shaft.

[0010] Preferably, one side surface of the solar panel is provided with a patch surface.

[0011] Preferably, the celestial body has a body coordinate system O. o X o Y o Zo O o X o The axis points in the direction of the satellite's flight; The first end of the connecting rod on the +Y wing is equipped with a local coordinate system O. b1 X b1 Y b1 Z b1 O b1 Y b1 The axis is parallel to the main axis on the +Y wing and points away from the star. b1 X b1 The axis is aligned with the O of the star when the +Y wing is in its initial position. o X o The axes are parallel; -The first end of the connecting rod on the Y-wing is equipped with a local coordinate system O. a1 X a1 Y a1 Z a1 O a1 Y a1 The axis is parallel to the main axis on the -Y wing and points in the direction of the star. a1 X a1 The axis is aligned with the O of the star when the -Y wing is in its initial position. o X o The axes are parallel.

[0012] Preferably, the solar panels on the +Y wing are provided with a local coordinate system O. b2 X b2 Y b2 Z b2 O b2 X b2 Axis and O of celestial bodies o X o Axis parallel, O b2 X b2 The axis of rotation of the shaft coincides with the axis of rotation of the secondary shaft on the +Y wing. b2 Z b2 The axis is perpendicular to the patch surface and points from the substrate of the solar panel to the solar cell; -The Y-wing has a local coordinate system O a2 X a2 Y a2 Z a2 O a2 X a2 O of celestial bodies o X o Axis parallel, O a2 X a2 The axis of rotation of the shaft coincides with that of the secondary shaft on the -Y wing. a2 Z a2 The axis is perpendicular to the patch surface and points from the substrate of the solar panel to the solar cell.

[0013] Preferably, when the solar panel is in the initial position, the local coordinate system O b1 X b1 Y b1 Z b1 O a1 X a1 Y a1 Z a1 O b2 X b2 Y b2 Z b2 And O a2 X a2 Y a2 Z a2 All three axes are aligned with the body coordinate system O of the celestial body. o X o Y o Z o The three axes are parallel.

[0014] Preferably, the rotation range of the connecting rod is 360°, and the rotation speed of the main shaft is maintained within a preset deviation range centered on the track angular velocity; The rotation range of the secondary shaft is [-β0 to +β0], where β0 is the maximum absolute value of the solar altitude angle of the orbit of the satellite.

[0015] Preferably, the length L of the connecting rod satisfies: L>sin(β)×0.5×Z L Z L β is the altitude of the celestial body, and β is the solar altitude angle of the satellite's orbit.

[0016] Preferably, a digital solar sensor is provided on both the +Y wing and the -Y wing, with the optical axis of the solar sensor perpendicular to the patch surface of the solar panel. The connector of the solar sensor on the +Y wing faces the celestial body, while the connector of the solar sensor on the -Y wing faces the cold space.

[0017] A control method for a satellite solar panel according to the present invention, applied to the aforementioned satellite solar panel configuration, includes: S1: Obtain the centroid coordinates (X) of the spot position on the detector using digital solar sensors on the +Y and -Y wings. sc Y sc And transmit it to the drive control computer in the star; S2: After converting the centroid coordinates to decimal using the drive control computer, multiply them by the centroid position resolution to obtain the corrected spot centroid position (X). c Y c Then, using the formula α=arctg((X) c -X sc0 ) / f) and θ=-arctg((Yc -Y sc0 ) / f) calculate the solar incidence angle, where α is the angle of incidence of Y. s The angle of incidence of the sun, θ, is X. s The angle of incidence towards the sun, f is the optical focal length of the solar sensor, and X sc0 Y sc0 This is the detector center deviation value; S3: Drive the main shaft and secondary shaft of the two-dimensional drive structure to rotate, repeat S1 and S2 until the solar incidence angles α and θ are zero, thus realizing the solar panel's solar tracking; S4: Control and protect the main and secondary shafts: The rotation speed of the main shaft is maintained within the deviation range centered on the orbital angular velocity, and the rotation angle of the secondary shaft is maintained within the deviation range centered on the solar altitude angle β; if the deviation range is exceeded, a satellite telemetry parameter alarm is triggered.

[0018] Compared with the prior art, the present invention has the following beneficial effects: The method of this invention is used for the design and control of two-dimensional driven solar panel configurations, so that the solar panels always keep tracking the sun and ensure the energy of the entire satellite. Attached Figure Description

[0019] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 Definition of the windsurfing coordinate system and diagram of negative angle rotation of the secondary axis; Figure 2 Diagram showing the positive angle rotation of the secondary shaft; Figure 3 This is a diagram of the solar incidence angle for a digital solar sensor.

[0020] The diagram shows: Detailed Implementation

[0021] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0022] The preferred embodiments of the present invention are given below with reference to the accompanying drawings to illustrate the technical solution of the present invention in detail.

[0023] The satellite's body coordinate system is O o X o Y o Z oO o X o The axis points in the direction of the satellite's flight. The solar panel consists of two wings: -Y wing 6 and +Y wing 5 (e.g., ...). Figure 1 (As shown). The solar panel 7 adopts a two-dimensional drive method, with two rotation axes perpendicular to each other, one of which is perpendicular to the system O. o Y o One axis is horizontal, and the other axis is parallel to the system's O. o X o The axis is horizontal, enabling the solar panels to track 7 solar pairs. Installed in -O o Y o The side solar panel 7 is located on the -Y wing 6 and is mounted on the +O wing. o Y o The side solar panel 7 is located on the +Y wing 5. The -Y wing 6 is defined with a local coordinate system: O a1 X a1 Y a1 Z a1 and O a2 X a2 Y a2 Z a2 , of which O a1 X a1 Y a1 Z a1 Set on the connecting rod 8 of -Y wing 6, O a2 X a2 Y a2 Z a2 The solar panel 7 is mounted on the -Y wing 6. The +Y wing 5 has a local coordinate system O. b1 X b1 Y b1 Z b1 and O b2 X b2 Y b2 Z b2 O b1 X b1 Y b1 Z b1 Set on the connecting rod 8 of +Y wing 5, O b2 X b2 Y b2 Z b2 It is mounted on the solar panel 7 of the +Y wing 5.

[0024] Preferably, the local coordinate system O a1 X a1 Y a1 Z a1 The mounting flange is located on the first end of the connecting rod 8 of the -Y wing 6, with this first end facing the star 1, in the local coordinate system O. b1 X b1 Y b1 Zb1 The mounting flange is located on the first end of the connecting rod 8 of the +Y wing 5, and this first end also faces the star 1. Local coordinate system O a1 X a1 Y a1 Z a1 O b1 X b1 Y b1 Z b1 Rotating together with the mounting flange, this rotating shaft is the main shaft 2, and the main shaft 2, O a1 Y a1 O b1 Y b1 With O o Y o The axes remain parallel.

[0025] -Y-wing 6 local coordinates O a1 X a1 Y a1 Z a1 O of the coordinate system a1 The mounting flange for the Y-wing 6 solar panel is located at the center of the rotational connection between the connecting rod 8 and the satellite body 1. a1 Y a1 The axis is parallel to the main axis 2 on the -Y wing 6 and points in the direction of star 1. a1 Y a1 Shaft and the system O o Y o The axes are parallel, with the direction from the solar panel to the drive mechanism; O a1 X a1 When the shaft is initially unfolded, it is related to the O system. o X o The axis is parallel, and the direction points towards the satellite's flight direction. a1 Z a1 The axis is determined by the right-hand rule.

[0026] +Y wing 5 local coordinates O b1 X b1 Y b1 Z b1 O of the coordinate system b1 Center O of the flange for mounting the +Y wing 5 solar panel b1 Y b1 O b1 Y b1 The axis is parallel to the main axis 2 on the +Y wing 5 and points away from the direction of star 1. The axis is parallel to the O of the main system. o Y o The axes are parallel, with the direction from the solar panel to the drive mechanism; O b1 X b1 When the shaft is initially unfolded, it is related to the O system. o X oThe axis is parallel, and the direction points towards the satellite's flight direction. b1 Z b1 The axis is determined by the right-hand rule.

[0027] Local coordinate system O a2 X a2 Y a2 Z a2 O b2 X b2 Y b2 Z b2 It is fixed to the end bearing of the second end of the connecting rod 8 of the -Y wing 6 or +Y wing 5 respectively, and rotates together with the solar panel. This shaft is the secondary shaft 3.

[0028] -Y-wing 6 local coordinates O a2 X a2 Y a2 Z a2 Origin of coordinates a2 The center of the bearing at the end of the solar panel connecting rod; O a2 X a2 The rotation axis of the secondary shaft 3 on the -Y wing 6 coincides with that of the main system O. o X o The axis is parallel, and the direction points towards the satellite's flight direction. a2 Z a2 The axis is perpendicular to the patch surface 4 of the -Y wing 6, parallel to the normal of the solar panel array of the -Y wing 6, and its direction is from the substrate to the solar cell. a2 Y a2 The axis is determined by the right-hand rule.

[0029] +Y wing 5 local coordinates O a2 X a2 Y a2 Z a2 Origin of coordinates b2 For the center of the end bearing of the +Y wing 5 solar panel; O b2 X b2 The axis of rotation of the shaft coincides with the axis of rotation of the secondary shaft 3 on the +Y wing 5, and is consistent with the axis of rotation of the system O. o X o The axis is parallel, and the direction points towards the satellite's flight direction. b2 Z b2 The axis is perpendicular to the patch surface 4 of the +Y wing 5, parallel to the normal of the solar panel array of the +Y wing 5, and its direction is from the substrate to the solar cell. b2 Y b2 The axis is determined by the right-hand rule.

[0030] Preferably, after the satellite enters orbit, the positions of the -Y wing 6 and +Y wing 5 after deployment are defined as the zero-position rotation angle of the solar panel drive control. At this time, the local coordinate system O of the -Y wing 6 and +Y wing 5 is... a1 X a1Y a1 Z a1 O a2 X a2 Y a2 Z a2 O b1 X b1 Y b1 Z b1 O b2 X b2 Y b2 Z b2 The three axes and the star body coordinate system O o X o Y o Z o Each of the three axes is parallel. In case of abnormal satellite attitude or energy crisis, the drive controls the solar panels to return to the zero-position rotation angle.

[0031] Preferably, such as Figure 1 As shown, during solar panel drive control, the local coordinate system O... a1 X a1 Y a1 Z a1 and O b1 X b1 Y b1 Z b1 Rotation about the satellite's body axis O0Y0 is defined as rotation about the solar panel's pitch axis; local coordinate system O a2 X a2 Y a2 Z a2 O b2 X b2 Y b2 Z b2 The rotation of the secondary shaft 3 on the respective -Y wing 6 or +Y wing 5 is defined as the rotation of the rolling axis of the solar panel 7.

[0032] Local coordinate system O a1 X a1 Y a1 Z a1 and O b1 X b1 Y b1 Z b1 When rotating around the pitch axis of main axis 2, the rotation angle is positive when the direction of rotation (according to the right-hand rule) is consistent with the Y0 axis of star 1, and negative otherwise.

[0033] such as local coordinate system O a2 X a2 Y a2 Z a2 O b2 X b2 Y b2 Z b2When rotating around the secondary shaft 3, the rotation angle is positive when the direction of rotation (according to the right-hand rule) is consistent with the X0 axis direction of the celestial body 1 (e.g., ...). Figure 2 As shown), the opposite is negative (as shown). Figure 1 (as shown) Figure 1 , Figure 2 In the diagram, the solar panel 7 in working condition is represented by a dashed line, while the solar panel 7 in its initial state is represented by a solid line.

[0034] Preferably, a digital sun sensor is installed on each of the -Y wing 6 and the +Y wing 5, and the installation directions are the same, with their optical axes perpendicular to the patch surface 4 of the solar panel 7 and facing the positive direction of the solar panel. The connector of the digital sun sensor on the +Y wing 5 faces the star 1, and the connector of the digital sun sensor on the -Y wing 6 faces the cold space.

[0035] The control method for satellite solar panels of the present invention includes the following steps: The digital sun sensor outputs the centroid coordinates of the spot position on the detector, which are then calculated by the drive control computer to obtain the sun's incident angle.

[0036] like Figure 3 As shown: O, the origin of the coordinate system of a single digital sun sensor. s At the geometric center of the instrument, Z s The axis is perpendicular to the mounting surface and has the same direction as the optical axis of the digital sun sensor, Y. s The connector for the forward-pointing digital sun sensor, X s The axis is determined using the right-hand rule. The solar vector is represented by O. s A represents...

[0037] X s Towards the Sun: The Sun's vector in the Y direction s O s Z s Projection on the plane and O s Z s The included angle of the axis (i.e. Figure 3 (θ angle); Y s Towards the Sun: The Sun's vector in the X direction s O s Z s Projection on the plane and O s Z s The included angle of the axis (i.e. Figure 3 (α angle).

[0038] Polarity definition: θ angle – facing O s X s The axis, starting from position zero, winds around O. s X s When the axis is rotated counterclockwise, the digital sun sensor displays a positive angle; conversely, rotating counterclockwise displays a negative angle. α angle – facing Os Y s The axis, starting from position zero, winds around O. s Y s When the axis rotates counterclockwise, the digital sun sensor has a positive angle value, and vice versa.

[0039] The above-mentioned drive control computer calculation process is described as follows: Digital sun sensor outputs centroid coordinates (X) sc Y sc The signal is sent to the drive control computer, which first converts it to decimal, multiplies it by the centroid position resolution, and then calculates the corrected centroid position (X). c Y c The centroid position resolution is preferably 1 / 64.

[0040] Using the formula α=arctg((X) c -X sc0 ) / f), θ=-arctg((Y c -Y sc0 ) / f), calculate the angle of incidence of the sun. Where α is the y s The angle of incidence of the sun, θ, is X. s The angle of incidence towards the sun, f is the optical focal length of the solar sensor, and X sc0 Y sc0 X represents the detector center deviation value, assuming no installation error. sc0 =0、Y sc0 =0.

[0041] By driving and controlling the rotation of the two axes of the solar panel to make the solar incidence angles α and θ zero, the solar panel can be controlled to track the sun.

[0042] Preferably, step 7 includes (e.g.) Figure 1 and Figure 2 (As shown): To achieve maximum photoelectric conversion efficiency, it is necessary to ensure that sunlight hits the solar panels perpendicularly. Based on the satellite's orbital parameters, the range of the β angle can be obtained, where β is the solar altitude angle of the satellite's orbit.

[0043] Taking a certain satellite as an example, the orbital inclination is 50°, the orbital altitude is 407km, and the solar altitude angle β varies between [-65°, 65°]. That is to say, the maximum absolute value of the solar altitude angle β0 of the satellite's orbit is 65°. Therefore, the maximum control angle of the secondary axis 3 is 65°, that is, the maximum mechanical rotation angle between the secondary axis 3 and the main axis is designed to be 65°.

[0044] Since sunlight rotates 360° around the solar panel's main axis 2 as the satellite orbits the Earth, the rotation range of the main axis 2 is designed to be 360°. When the solar altitude angle is 65°, to avoid eclipsing by celestial body 1, the length L of the connecting rod 8 is greater than sin(β)*0.5*Z. L Z L The altitude of star 1.

[0045] Preferably, step 8 includes: the drive control computer's control protection of the solar panel includes main shaft angular velocity protection and secondary shaft 3 rotational position protection.

[0046] Main spindle angular velocity protection: Based on the satellite's flight speed, the rotational speed of main spindle 2 is maintained within a preset deviation range centered on the orbital angular velocity. Taking a certain satellite as an example, its flight angular velocity is 0.0647° / s, and the drive control computer controls the solar panel main spindle Y... s The target angular velocity at the sun angle α is 0.0647° / s. If the drive control speed error is 0.005° / s, then the deviation range is [-0.005, 0.005]° / s.

[0047] For the protection of the secondary shaft rotation angle, based on the full field of view of the digital sun sensor, its measurement error is 0.6° and the drive control rotation angle error is 0.8°. Therefore, the rotation angle of the secondary shaft 3 should be within the deviation range centered on the solar altitude angle β, specifically [-1.4°, 1.4°].

[0048] The above deviation range can be corrected on-orbit. If it exceeds the set range, an alarm will be set for the satellite telemetry parameters, indicating a drive control error.

[0049] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0050] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A satellite solar panel configuration, characterized in that, include: Star (1), +Y wing (5) and -Y wing (6); +Y wing (5) and -Y wing (6) are respectively connected to the star (1). +Y wing (5) and -Y wing (6) each include a two-dimensional drive structure and a solar panel (7). The two-dimensional drive structure can drive the solar panel (7) to rotate in two mutually perpendicular directions. When the +Y wing (5) and -Y wing (6) are initially deployed, the solar panels (7) are both in their initial positions with zero rotation angle.

2. The satellite solar panel configuration according to claim 1, characterized in that, The two-dimensional drive structure includes: a main shaft (2), a connecting rod (8), and a secondary shaft (3); The main shaft (2) is located at the first end of the connecting rod (8) and is parallel to the axial direction of the connecting rod (8). The secondary shaft (3) is located at the second end of the connecting rod (8). The main shaft (2) and the secondary shaft (3) are perpendicular to each other. The connecting rod (8) is rotatably connected to the star (1) via the main shaft (2) and rotatably connected to the solar panel (7) via the secondary shaft (3).

3. The satellite solar panel configuration according to claim 2, characterized in that, The solar panel (7) has a patch surface (4) on one side surface.

4. The satellite solar panel configuration according to claim 2, characterized in that, The celestial body (1) has a body coordinate system O o X o Y o Z o O o X o The axis points in the direction of the satellite's flight; The first end of the connecting rod (8) on the +Y wing (5) is equipped with a coordinate system O. b1 X b1 Y b1 Z b1 O b1 Y b1 The axis is parallel to the main axis (2) on the +Y wing (5) and points away from the star (1), O b1 X b1 When the axis is in its initial position, the +Y wing (5) is aligned with the O-axis of the star (1). o X o The axes are parallel; - The first end of the connecting rod (8) on the Y-wing (6) is equipped with a coordinate system O a1 X a1 Y a1 Z a1 O a1 Y a1 The axis is parallel to the main axis (2) on the -Y wing (6) and points in the direction of the star (1), O a1 X a1 When the axis is in its initial position, the Y-wing (6) is aligned with the O-axis of the star (1). o X o The axes are parallel.

5. The satellite solar panel configuration according to claim 3, characterized in that, The solar panel (7) on the +Y wing (5) is equipped with a coordinate system O. b2 X b2 Y b2 Z b2 O b2 X b2 The axis and the O of the star (1) o X o Axis parallel, O b2 X b2 The axis of rotation of the shaft coincides with the axis of rotation of the secondary shaft (3) on the +Y wing (5), O b2 Z b2 The axis is perpendicular to the patch surface (4) and points from the substrate of the solar panel (7) to the cell. -Y wing (6) has a coordinate system O a2 X a2 Y a2 Z a2 O a2 X a2 O of star (1) o X o Axis parallel, O a2 X a2 The axis of rotation of the shaft coincides with the axis of rotation of the secondary shaft (3) on the -Y wing (6), O a2 Z a2 The axis is perpendicular to the patch surface (4) and points from the substrate of the solar panel (7) to the cell.

6. The satellite solar panel configuration according to claim 2, characterized in that, When the solar panel (7) is in the initial position, coordinate system O b1 X b1 Y b1 Z b1 O a1 X a1 Y a1 Z a1 O b2 X b2 Y b2 Z b2 And O a2 X a2 Y a2 Z a2 The three axes are all respectively related to the coordinate system O of the star (1). o X o Y o Z o The three axes are parallel.

7. The satellite solar panel configuration according to claim 2, characterized in that, The rotation range of the connecting rod (8) is 360°, and the rotation speed of the main shaft (2) is maintained within the preset deviation range centered on the track angular velocity; The rotation range of the secondary shaft (3) is [-β0 to +β0], where β0 is the maximum absolute value of the solar altitude angle of the orbit of the satellite.

8. The satellite solar panel configuration according to claim 2, characterized in that, The length L of the connecting rod (8) satisfies: L>sin(β)×0.5×Z L Z L β is the altitude of the star (1), and β is the solar altitude angle of the satellite's orbit.

9. The satellite solar panel configuration according to claim 2, characterized in that, Digital solar sensors are provided on both the +Y wing (5) and the -Y wing (6). The optical axis of the solar sensor is perpendicular to the patch surface (4) of the solar panel (7). The connector of the solar sensor on the +Y wing (5) faces the star (1), and the connector of the solar sensor on the -Y wing (6) faces the cold space.

10. A control method for a satellite solar panel, applied to the satellite solar panel configuration according to any one of claims 1 to 9, characterized in that, include: S1: Obtain the centroid coordinates (X) of the spot position on the detector using digital solar sensors on the +Y wing (5) and -Y wing (6). sc Y sc ) and transmit to the drive control computer in the star (1); S2: After converting the centroid coordinates to decimal using the drive control computer, multiply them by the centroid position resolution to obtain the corrected spot centroid position (X). c Y c Then, using the formula α=arctg((X) c -X sc0 ) / f) and θ=-arctg((Y c -Y sc0 ) / f) calculate the solar incidence angle, where α is the angle of incidence of Y. s The angle of incidence of the sun, θ, is X. s The angle of incidence towards the sun, f is the optical focal length of the solar sensor, and X sc0 Y sc0 This is the detector center deviation value; S3: Drive the main shaft (2) and secondary shaft (3) of the two-dimensional drive structure to rotate, repeat S1 and S2 until the solar incident angles α and θ are zero, and realize the solar panel (7) to track the sun; S4: Control and protect the main shaft (2) and the secondary shaft (3): The rotation speed of the main shaft (2) is maintained within the deviation range centered on the orbital angular velocity, and the rotation angle of the secondary shaft (3) is maintained within the deviation range centered on the solar altitude angle β; if the deviation range is exceeded, the satellite telemetry parameter alarm is triggered.

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