Two-dimensional tracking control method and system for sun observation load of stationary meteorological satellite

Abstract

The invention provides a two-dimensional tracking control method and system for a sun observation load of a stationary meteorological satellite. The two-dimensional tracking control method comprises the steps that a satellite service management unit receives the attitude and orbit data of a current information control computer, the measurement data of a sensor and the rotation angle data of a driving mechanism; the east-west solar angle and the south-north solar angle are calculated, and a driving mechanism is driven to complete initial sun capture in the east-west direction and the south-north direction of the optical axis of the EUV imager; when initial sun capture is completed, the sun enters the digital too sensitive field of view; and when the sun enters the field of view of the guide mirror, the data of the guide mirror in the measured data is used as input, and the south-north dimension driving mechanism and the solar array driving mechanism are fed back and controlled in real time, so that two-dimensional coarse alignment and tracking to the sun are realized. The problem of east-west, south-north two-dimensional tracking of the sun observation load is solved, a two-dimensional tracking control method and a control strategy are provided, the sun observation load can accurately point to the sun in real time, and the method can be applied to the research and development process of a stationary meteorological satellite.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of space vehicle control technology, in particular, to a two-dimensional tracking control method and system for a sun observation load of a geostationary meteorological satellite. BACKGROUND

[0002] In space weather, the solar wind from a coronal hole constitutes the basic environment of space weather, while intense events in the solar atmosphere such as flares and coronal mass ejections are the main factors leading to space weather anomalies. Such intense activities often occur in the upper atmosphere of the sun, especially in the transition region and corona. Imaging the sun using extreme ultraviolet (EUV) band imaging instruments can obtain information on solar flares, coronal mass ejections and other intense activities, provide early warning of solar activity, and thus predict catastrophic space weather events, providing accurate predictions for human space activities and national defense construction.

[0003] Due to the influence of satellite orbital motion, the sun will appear periodic motion in the satellite body coordinate system. In order to ensure that the sun observation load obtains the required sun observation image within the exposure time range, it is necessary to adjust the spatial pointing of the sun observation load optical axis in real time to accurately point to the sun and track. The pointing accuracy of the sun observation load reaches 1', which puts high requirements on the control accuracy and stability of the pointing system.

[0004] After searching:

[0005] Patent No. ZL200410031462.6, entitled "Solar tracking system and two-dimensional solar tracking stepper motor control interface", introduces a solar tracking system and two-dimensional solar tracking stepper motor control interface, which can be used for observation of direct solar radiation and split radiation, controls 2 stepper motors to move in forward and reverse directions, and is suitable for other similar occasions, but does not elaborate on the two-dimensional tracking control method of the sun observation load of a geostationary meteorological satellite.

[0006] Patent No. ZL201010509198.8, entitled "Dual-axis sailboard control method for non-solar synchronous orbit satellite", introduces a dual-axis sailboard control method, which includes the control method of each single-axis sailboard in the dual-axis sailboard, and the implementation method when the dual-axis sailboard works together, which not only ensures the supply of energy on the satellite, but also meets the demand of the satellite for three-axis stabilization, but does not elaborate on the two-dimensional tracking control method of the sun observation load of a geostationary meteorological satellite.

[0007] Patent No. ZL201610081893.6, entitled "A reliable solar sailboard autonomous tracking solar control method", introduces a solar sailboard autonomous tracking solar control method, controls the sailboard to rotate in different working modes, avoids the influence of frequent stopping and switching of the sailboard in different modes on the attitude and the service life of the driving mechanism, but does not elaborate the two-dimensional tracking control method of the solar observation load of the stationary meteorological satellite.

[0008] Patent No. ZL201610423963.1, entitled "A large inclination orbit satellite solar sailboard pointing method under simple attitude control", introduces a solar sailboard autonomous tracking solar control method, which overcomes the defects in the prior art that the satellite using a single-degree-of-freedom solar sailboard driving mechanism is always controlled in yaw angle to meet the requirement that the sunlight is perpendicular to the satellite solar sailboard, and the rotation speed of the solar sailboard is large, which is not conducive to the stability of the satellite payload, and three solar sailboard pointing adjustment modes are designed according to the angle θ between the direction of the sunlight vector and the direction of the satellite orbit normal line to meet the pointing requirements of the large inclination orbit satellite solar sailboard, but the two-dimensional tracking control method of the solar observation load of the stationary meteorological satellite is not elaborated.

[0009] Patent application No. 201610081893.6, entitled "Solar cell array control strategy method suitable for yaw maneuvering satellite", introduces a yaw maneuvering satellite solar sailboard pointing method, determines the satellite yaw maneuvering scheme according to the illumination condition, obtains the solar cell array control strategy according to the satellite yaw maneuvering scheme, and solves the energy problem of the inclined orbit satellite in flight, but the two-dimensional tracking control method of the solar observation load of the stationary meteorological satellite is not elaborated.

[0010] The method of the present application is practical for engineering, and proposes a two-dimensional tracking control method for the solar observation load of a stationary meteorological satellite. The present application can be applied to the development process of a stationary meteorological satellite.

[0011] Unlike general communication and remote sensing satellites, the infrared earth remote sensing instrument carried by the stationary meteorological satellite needs a stable heat dissipation surface. The satellite + Y surface cannot be installed with a two-dimensional pointing mechanism as a heat dissipation surface. The solar array has been installed on the satellite body-Yb surface, and the installation of a two-dimensional pointing mechanism will cause interference and obstruction problems. The ±Xb surface and the ±Zb surface are all back to the sun and cannot be used for observation, so they cannot be used for installation of a two-dimensional pointing mechanism. Therefore, the commonly used two-dimensional adjustment pointing mechanism scheme cannot be applied to the stationary meteorological satellite.

[0012] Therefore, there is a need in the market for a two-dimensional tracking control method and system for the solar observation load of a stationary meteorological satellite. SUMMARY

[0013] Aiming at the defects in the prior art, the present application aims to provide a two-dimensional tracking control method and system for a sun observation load of a geostationary meteorological satellite.

[0014] The two-dimensional tracking control method for a sun observation load of a geostationary meteorological satellite provided by the present application comprises the following steps:

[0015] Step S1: a star management unit receives attitude, orbit data of a current computer, measurement data of a sensor and rotation angle data of a driving mechanism;

[0016] Step S2: the star management unit calculates east-west sun angle and north-south sun angle according to the attitude, orbit data and the rotation angle data, and drives the driving mechanism to complete initial sun capture in the east-west and north-south directions of the optical axis of the EUV imager.

[0017] Step S3: when the initial sun capture is completed, the sun enters the field of view of the digital sun sensor.

[0018] Step S4: when the sun enters the field of view of the guide mirror, the guide mirror data in the measurement data is taken as input to realize real-time feedback control of the north-south driving mechanism and the sun array driving mechanism, so as to realize two-dimensional coarse alignment and tracking.

[0019] Preferably, the sensor comprises a digital sun sensor (DSS) and a sun observation guide mirror (FSS).

[0020] The digital sun sensor (DSS) and the sun observation guide mirror (FSS) are installed on the same reference, and the included angle between the optical axes of the two is not greater than 15".

[0021] The driving mechanism comprises a sun array driving mechanism (SADA) and a north-south driving mechanism (SEGA).

[0022] The rotation angle data comprises SADA rotation angle information and SEGA rotation angle information.

[0023] Preferably, the initial sun capture comprises calculating east-west and north-south sun angles according to the orbit attitude, and rapidly capturing the east-west and north-south sun angles to the vicinity of 0° by adjusting the SADA rotation angle and the SEGA rotation angle.

[0024] During the initial sun capture, the limit cycle control law is adopted in the east-west and north-south directions, and only the speed gear is different.

[0025] Preferably, the step S3 comprises digital sun sensor sun capture by taking the digital sun sensor data in the measurement data as input, so that the digital sun sensor outputs the east-west and north-south sun angles to the vicinity of 0°.

[0026] The control law of the digital sun sensor sun capture adopts the limit cycle control law.

[0027] Preferably, the control law of the solar tracking mode includes: using the east-west and north-south solar angles measured by the guiding mirror as control inputs, adjusting the rotation angles of the solar cell array drive mechanism and the north-south dimension drive mechanism to keep the control accuracy of the east-west and north-south solar angles within the index range; when the sun enters the field of view of the guiding mirror, the satellite autonomously switches to the solar tracking mode.

[0028] In solar tracking mode, the east-west direction uses limit cycle control law, and the north-south direction uses PI controller for continuous control.

[0029] A two-dimensional tracking and control system for a geostationary meteorological satellite solar observation payload, provided by the present invention, includes:

[0030] Module M1: The satellite management unit receives attitude and orbit data from the current data control computer, sensor measurement data, and rotation angle data from the drive mechanism;

[0031] Module M2: The satellite management unit calculates the east-west solar angle and north-south solar angle based on the attitude, orbit data and the rotation angle data, and drives the drive mechanism to complete the initial solar capture in the east-west and north-south directions of the EUV imager's optical axis;

[0032] Module M3: When the initial solar capture is complete, the sun enters the digital solar sensitive field of view;

[0033] Module M4: When the sun enters the field of view of the navigation mirror, the navigation mirror data in the measurement data is used as input to provide real-time feedback control of the north and south dimension drive mechanism and the solar array drive mechanism, so as to realize two-dimensional coarse alignment and tracking of the sun.

[0034] Preferably, the sensor includes a digital solar sensor (DSS) and a solar observation guide mirror (FSS);

[0035] The digital solar sensor (DSS) and the solar observation guide mirror (FSS) are mounted on the same reference, and the angle between their optical axes is no greater than 15″.

[0036] The drive mechanism includes the solar array drive mechanism SADA and the north-south axis drive mechanism SEGA.

[0037] The corner data includes SADA corner information and SEGA corner information.

[0038] Preferably, the initial solar capture includes calculating the east-west and north-south solar angles based on the orbital attitude, and rapidly capturing the east-west and north-south solar angles to around 0° by adjusting the SADA rotation angle of the solar array drive mechanism and the SEGA rotation angle of the north-south dimension drive mechanism.

[0039] During the initial solar capture, the limit cycle control law was used in both the east-west and north-south directions, with only the speed level differing.

[0040] Preferably, the module M3 comprises digital sun-seeking solar capture taking digital sun-seeking data in the measurement data as input, making digital sun-seeking output east-west, north-south solar angles to approach 0°;

[0041] The control law of the digital sun-seeking solar capture adopts a limit cycle control law.

[0042] Preferably, the sun tracking mode control law comprises: taking the east-west, north-south solar angles measured by the guide mirror as control input, and continuously controlling the east-west, north-south solar angles by adjusting the solar cell array driving mechanism and the north-south orientation driving mechanism angle, so as to keep the east-west, north-south solar angles within the index range; when the sun enters the field of view of the guide mirror, the satellite autonomously switches to the sun tracking mode.

[0043] In the sun tracking mode, the east-west direction adopts a limit cycle control law, and the north-south direction adopts a PI controller for continuous control.

[0044] Compared with the prior art, the present application has the following beneficial effects:

[0045] The two-dimensional tracking control method for the sun observation load of the geostationary meteorological satellite provided by the present application solves the east-west, north-south two-dimensional tracking problem of the sun observation load through SADA and SEGA two-dimensional control, and provides a two-dimensional tracking control method and control strategy, so that the sun observation load can be accurately pointed to the sun in real time, and can be applied to the development process of the geostationary meteorological satellite. BRIEF DESCRIPTION OF DRAWINGS

[0046] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0047] Figure 1 Fig. 1 is a schematic diagram of the two-dimensional tracking closed-loop control scheme for the sun observation load of the geostationary meteorological satellite of the present application;

[0048] Figure 2 Fig. 2 is a schematic diagram of the two-dimensional tracking sun for the sun observation load of the geostationary meteorological satellite of the present application, in which O b -X b Y b Z b is the satellite body coordinate system;

[0049] Figure 3 Fig. 3 is a schematic diagram of the two-dimensional tracking control flow for the sun observation load of the geostationary meteorological satellite of the present application;

[0050] Figure 4 Fig. 4 is a schematic diagram of the sun capture control law in the present application;

[0051] Figure 5 Fig. 5 is a schematic diagram of the east-west direction sun tracking control law in the present application;

[0052] Figure 6 Figure 1 is a schematic diagram of a north-south direction sun tracking control law in the present application;

[0053] wherein, Figure 2 Figure 1 is a schematic diagram of a north-south direction sun tracking control law in the present application; DETAILED DESCRIPTION

[0054] The present application will be described in detail below with specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present application. These are within the scope of the present application.

[0055] The two-dimensional tracking control method for the sun observation load of the geostationary meteorological satellite provided by the present application takes the satellite integrated electronic subsystem star service management unit as a closed-loop driving controller, takes the digital sun sensor (DSS) and the sun observation guide mirror (FSS) as sensors, and takes the sun array driving mechanism (SADA) and the north-south driving mechanism (SEGA) as an execution mechanism, to form a closed-loop control circuit to control the sun observation load to point to the sun in real time, as shown in Figure 1 , which can be applied to the development process of the new generation of geostationary meteorological satellites in China.

[0056] Embodiment 1

[0057] According to the two-dimensional tracking control method for the sun observation load of the geostationary meteorological satellite provided by the present application, as shown in Figures 1 to 3 , it comprises:

[0058] Step S1: The star service management unit receives the attitude and orbit data of the current resource control computer, the measurement data of the sensor, and the rotation angle data of the driving mechanism. The sensor includes a digital sun sensor DSS and a sun observation guide mirror FSS. The driving mechanism includes a sun array driving mechanism SADA and a north-south driving mechanism SEGA. The rotation angle data includes SADA rotation angle information and SEGA rotation angle information.

[0059] Step S2: The star service management unit calculates the east-west sun angle and the north-south sun angle according to the attitude and orbit data and the rotation angle data, and drives the driving mechanism to complete the initial sun capture of the EUV imager optical axis in the east-west and north-south directions, that is, autonomously calculates the east-west and north-south sun angles to reach about 0°.

[0060] The initial solar capture mode control principles include calculating the east-west and north-south solar angles based on orbital attitude, and rapidly capturing the east-west and north-south solar angles to near 0° by adjusting the rotation angles of the solar array drive mechanism and the north-south dimensional drive mechanism. In the initial solar capture mode, both the east-west and north-south directions utilize... Figure 4 The limit cycle control law shown differs only in the speed range. The speed range switching thresholds R1, R2, and R3 for the east-west and north-south directions are 0.1°, 2.0°, and 4.0°, respectively. The speed ranges ω1, ω2, and ω3 for the east-west direction are 0.02° / s, 0.05° / s, and 0.60° / s, respectively. The speed ranges ω1, ω2, and ω3 for the north-south direction are 0.02° / s, 0.05° / s, and 0.20° / s, respectively.

[0061] Step S3: Due to the deviation (±0.5°~±1°) in the self-calculated solar angle and the small field of view of the guiding mirror (±0.2°×±0.2°), the sun generally cannot directly enter the field of view of the guiding mirror. However, the digital solar sensor has a larger field of view (±5.5°×±5.5°). When the initial solar capture is completed, the sun should enter the digital solar sensor's field of view. At this time, the digital solar sensor data from the measurement data is first used as input for digital solar sensor solar capture, so that the solar angles of the east, west, south, and north output by the digital solar sensor reach near 0°. The control law is the same as that of the initial solar capture, as shown in the attached figure. Figure 4 Because the digital solar sensor and the solar observation guide mirror are installed with the same reference, and the angle between their optical axes is no greater than 15″, when the output of the digital solar sensor is near 0°, the sun enters the field of view of the guide mirror.

[0062] Step S4: When the sun enters the field of view of the navigation mirror, the navigation mirror data in the measurement data is used as input. That is, the east-west and north-south solar angles obtained by the navigation mirror are used as input to provide real-time feedback control of the north-south dimension drive mechanism and the solar array drive mechanism to achieve two-dimensional coarse alignment and tracking of the sun.

[0063] The control principles of solar tracking mode include: using the east-west and north-south solar angles measured by the navigation mirror as control inputs, and adjusting the rotation angles of the solar array drive mechanism and the north-south dimensional drive mechanism to maintain the control accuracy of the east-west and north-south solar angles within the specified range. When the sun enters the field of view of the navigation mirror, the satellite autonomously switches to solar tracking mode. In solar tracking mode, the east-west direction uses a limit cycle control law, while the north-south direction uses a PI controller for continuous control.

[0064] The east-west direction uses a limit cycle control law, as shown in the attached figure. Figure 5The control speed gear switching threshold R1, R2, R3 is 20", 40", 60" respectively, and the SADA speed gear used is 0.00404° / s, 0.00412° / s, 0.00416° / s, 0.00417° / s, 0.00421° / s, 0.00429° / s respectively. The rotation speed of the sun in the XOZ plane of the star is 0.004167° / s, and the SADA mainly works at the two speed gears of 0.00416° / s and 0.00417° / s.

[0065] The PI control law is used in the north-south direction, as shown in the accompanying drawings. Figure 6 The measurement value of the sun observation guide mirror is taken as the input, and the command rotation angle of the north-south direction driving mechanism SEGA is taken as the output to form a feedback control, so that the control accuracy in the north-south direction is always kept within the index range.

[0066] Embodiment 2

[0067] The application also provides a two-dimensional tracking control system for a sun observation load of a geostationary meteorological satellite, which can be realized by executing the flow steps of the two-dimensional tracking control method for the sun observation load of the geostationary meteorological satellite, that is, the two-dimensional tracking control method for the sun observation load of the geostationary meteorological satellite can be understood as a preferred embodiment of the two-dimensional tracking control system for the sun observation load of the geostationary meteorological satellite by those skilled in the art.

[0068] The application provides a two-dimensional tracking control system for a sun observation load of a geostationary meteorological satellite.

[0069] Module M1: The attitude, orbit data of the current resource management computer, the measurement data of the sensor and the rotation angle data of the driving mechanism are received. The sensor includes a digital sun sensor DSS and a sun observation guide mirror FSS. The digital sun sensor DSS and the sun observation guide mirror FSS are installed with a common reference, and the included angle between the optical axes of the two is not greater than 15". The driving mechanism includes a sun array driving mechanism SADA and a north-south direction driving mechanism SEGA. The rotation angle data includes SADA rotation angle information and SEGA rotation angle information.

[0070] Module M2: The east-west sun angle and the north-south sun angle are calculated according to the attitude, orbit data and the rotation angle data, and the driving mechanism is driven to complete the initial sun capture of the optical axis of the EUV imager in the east-west and north-south directions. The initial sun capture includes calculating the east-west and north-south sun angles according to the orbit attitude, and quickly capturing the east-west and north-south sun angles to the vicinity of 0° by adjusting the SADA rotation angle and the SEGA rotation angle. During the initial sun capture, the limit cycle control law is used in the east-west and north-south directions, and only the speed gear is different.

[0071] Module M3: when the initial sun capture is completed, the sun enters the digital sun field of view. The module M3 includes digital sun sun capture with digital sun data in the measurement data as input, and makes the digital sun output east-west, north-south sun angle to near 0°. The control law of the digital sun sun capture adopts a limit cycle control law.

[0072] Module M4: when the sun enters the guide mirror field of view, the guide mirror data in the measurement data is taken as input, and the north-south orientation driving mechanism and the sun array driving mechanism are controlled in real time to realize two-dimensional coarse alignment and tracking. The sun tracking mode control law includes: taking the east-west, north-south sun angle measured by the guide mirror as the control input, adjusting the sun cell array driving mechanism and the north-south orientation driving mechanism angle, and keeping the east-west, north-south sun angle control accuracy within the index range. When the sun enters the guide mirror field of view, the satellite autonomously switches to the sun tracking mode. In the sun tracking mode, the east-west direction adopts a limit cycle control law, and the north-south direction adopts a PI controller for continuous control.

[0073] Those skilled in the art know that, in addition to implementing the system provided by the present application and each device, module and unit thereof in a pure computer readable program code manner, the system provided by the present application and each device, module and unit thereof can also be realized in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers and embedded microcontrollers by logically programming the method steps to achieve the same functions. Therefore, the system provided by the present application and each device, module and unit thereof can be considered as a hardware component, and the devices, modules and units included therein for achieving various functions can also be considered as structures within the hardware component; the devices, modules and units for achieving various functions can also be considered as both software modules for implementing methods and structures within the hardware component.

[0074] The specific embodiments of the present application are described above. It needs to be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. In the case of no conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A two-dimensional tracking control method for a sun observation payload of a geostationary meteorological satellite, characterized by, Comprising: Step S1: the star management unit receives the current attitude, orbit data, sensor measurement data and the angle data of the driving mechanism; Step S2: the star management unit calculates the east-west solar angle and the north-south solar angle according to the attitude, orbit data and the angle data, and drives the driving mechanism to complete the initial solar capture of the EUV imager optical axis in the east-west and north-south directions; Step S3: when the initial solar capture is completed, the sun enters the digital sun sensor field of view; Step S4: when the sun enters the field of view of the sun observation guide mirror, the navigation mirror data in the measurement data is taken as the input to realize the real-time feedback control of the north-south driving mechanism and the sun array driving mechanism, so as to realize the two-dimensional coarse alignment and tracking of the sun.

2. The two-dimensional tracking control method for a sun observation payload of a geostationary meteorological satellite according to claim 1, characterized by, The sensor comprises a digital sun sensor DSS and a sun observation guide mirror FSS; The digital sun sensor DSS and the sun observation guide mirror FSS are installed on the same reference, and the included angle between the optical axes of the two is not greater than 15"; The driving mechanism comprises a sun array driving mechanism SADA and a north-south driving mechanism SEGA; The angle data comprises SADA angle information and SEGA angle information.

3. The two-dimensional tracking control method for a sun observation payload of a geostationary meteorological satellite according to claim 1, characterized by, The initial solar capture comprises calculating the east-west and north-south solar angles according to the orbit attitude, and rapidly capturing the east-west and north-south solar angles to the vicinity of 0° by adjusting the SADA angle and the SEGA angle. During the initial solar capture, the limit cycle control law is adopted in the east-west and north-south directions, and only the speed gear is different.

4. The two-dimensional tracking control method for a sun observation payload of a geostationary meteorological satellite according to claim 1, characterized by, Step S3 comprises taking the digital sun sensor data in the measurement data as the input to perform the digital sun sensor solar capture, so that the output east-west and north-south solar angles of the digital sun sensor reach the vicinity of 0°. The control law of the digital sun sensor solar capture adopts the limit cycle control law.

5. The two-dimensional tracking control method for a sun observation payload of a geostationary meteorological satellite according to claim 1, characterized by, The sun tracking mode control law comprises: taking the east-west and north-south solar angles measured by the guide mirror as the control input, adjusting the SADA angle and the SEGA angle, and keeping the control precision of the east-west and north-south solar angles within the index range; when the sun enters the field of view of the guide mirror, the satellite autonomously switches to the sun tracking mode; In the sun tracking mode, the limit cycle control law is adopted in the east-west direction, and the PI controller is adopted in the north-south direction for continuous control.

6. A two-dimensional tracking control system for a solar observation payload of a geostationary meteorological satellite, characterized in that, Comprising: Module M1: the star management unit receives the current attitude, orbit data, sensor measurement data and the angle data of the driving mechanism; Module M2: the star management unit calculates the east-west solar angle and the north-south solar angle according to the attitude, orbit data and the angle data, and drives the driving mechanism to complete the initial solar capture of the EUV imager optical axis in the east-west and north-south directions; Module M3: when the initial solar capture is completed, the sun enters the digital sun sensor field of view; Module M4: when the sun enters the field of view of the sun observation guide mirror, the navigation mirror data in the measurement data is taken as the input to realize the real-time feedback control of the north-south driving mechanism and the sun array driving mechanism, so as to realize the two-dimensional coarse alignment and tracking of the sun.

7. The two-dimensional tracking control system for a sun-synchronous meteorological satellite solar observation payload of claim 6, wherein, The sensor comprises a digital sun sensor DSS and a sun observation guide mirror FSS; The digital sun sensor DSS and the sun observation guide mirror FSS are installed on the same reference, and the included angle between the optical axes of the two is not greater than 15"; The driving mechanism comprises a sun array driving mechanism SADA and a north-south driving mechanism SEGA; The driving mechanism comprises a sun array driving mechanism SADA and a north-south driving mechanism SEGA. The angle data comprises SADA angle data and SEGA angle data.

8. The two-dimensional tracking control system for a sun-synchronous meteorological satellite payload according to claim 6, characterized in that, The initial sun capture comprises calculating east-west and north-south sun angles in an orbit attitude, and rapidly capturing the east-west and north-south sun angles to the vicinity of 0° by adjusting the SADA angle and the SEGA angle. In the initial sun capture, the east-west and north-south directions are controlled by a limit cycle control law, and only the speed range is different.

9. The two-dimensional tracking control system for a sun-synchronous meteorological satellite solar observation payload of claim 6, wherein, The module M3 comprises a digital sun-sensing sun capture, which takes digital sun-sensing data in the measurement data as input, and outputs the east-west and north-south sun angles to the vicinity of 0°. The control law of the digital sun-sensing sun capture is a limit cycle control law.

10. The two-dimensional tracking control system for a sun-synchronous meteorological satellite payload according to claim 6, characterized in that, The sun tracking mode control law comprises taking the east-west and north-south sun angles measured by the guide mirror as control input, and continuously controlling the east-west and north-south sun angles to keep the control precision within the index range by adjusting the SADA angle and the SEGA angle, and when the sun enters the field of view of the guide mirror, the satellite is autonomously switched to the sun tracking mode. In the sun tracking mode, the east-west direction is continuously controlled by a limit cycle control law, and the north-south direction is continuously controlled by a PI controller.

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