Two-dimensional pointing method and system for sun observation of stationary meteorological satellite

Abstract

The invention provides a two-dimensional pointing method and system for sun observation of a stationary meteorological satellite. The method comprises the following steps: 1, designing the composition of the two-dimensional pointing system for sun observation of the stationary meteorological satellite; 2, designing a solar observation two-dimensional pointing scheme of the stationary meteorological satellite; 3, calculating a sun pointing angle in the east-west direction; 4, calculating a sun pointing angle in the north-south direction; 5, designing a sun search strategy; 6, designing a closed-loop driving control rule in the east-west direction; and 7, designing a closed-loop driving control rule in the north-south direction. According to the invention, an on-satellite computer is used as a controller, east-west, south-north sun pointing angles calculated by the on-satellite computer are used as control input, and a solar array driving mechanism and a south-north dimension driving mechanism are used as execution mechanisms, so that an on-satellite autonomous feedback closed-loop control system is formed, and a sun observation load can point to the sun accurately in real time; the method can be applied to the research and development process of a new generation of stationary meteorological satellites in China.

Description

Technical Field

[0001] The present invention relates to the general technical field of spacecraft, and in particular to a two-dimensional pointing method and system for solar observation of a geostationary meteorological satellite. Background Art

[0002] Solar wind originating from coronal holes constitutes the fundamental environment for space weather, while violent solar atmospheric events such as solar flares and coronal mass ejections (CMEs) are the primary drivers of space weather anomalies. These events typically occur in the Sun's upper atmosphere, particularly the transition region and corona. Using extreme ultraviolet (EUV) imaging instruments to observe the Sun, we can obtain information on these events, including solar flares and CMEs. This allows for early forecasts of solar activity and, consequently, for the prediction of potentially devastating space weather events, providing accurate predictions for human space activities and national defense development.

[0003] Due to the influence of the satellite's orbital motion, the Sun exhibits periodic motion within the satellite's coordinate system. To ensure that the solar observer captures satisfactory solar observation images within the required exposure time, real-time two-dimensional adjustment of the solar observer's optical axis is required for precise solar pointing and tracking. The solar observation payload's solar pointing accuracy reaches 1′, placing high demands on the control precision and stability of the pointing system.

[0004] Since the infrared earth remote sensing instrument carried by meteorological satellites requires a stable heat dissipation surface, the satellite's +Y plane cannot be used to install a two-dimensional pointing mechanism as it is a heat dissipation surface. The satellite's -Yb plane already has a solar array installed, so installing a two-dimensional pointing mechanism will cause interference and obstruction. The ±Xb and ±Zb planes both have the problem of being unable to observe when facing away from the sun, and therefore cannot be used to install a two-dimensional pointing mechanism. Aiming at engineering practice, the present invention proposes a two-dimensional pointing method and system for geostationary meteorological satellite solar observation. By installing a north-south drive mechanism on the solar array connecting frame, the north-south drive control is added to the closed-loop control of the east-west solar array, thus solving the problem of precise solar pointing of the solar observation system. The present invention can be applied to the research and development process of geostationary meteorological satellites.

[0005] Patent document CN100388143C (application number: 200410031462.6) discloses a solar tracker system and a two-dimensional solar tracker stepper motor control interface. The system and two-dimensional solar tracker stepper motor control interface can be used to observe direct solar radiation and spectroscopic radiation, control two stepper motors to move in forward and reverse directions, and are applicable to other similar situations. However, the system and method for two-dimensional solar pointing of a geostationary satellite are not described.

[0006] Patent document CN102004492B (application number: 201010509198.8) discloses a dual-axis sailboard control method for a non-sun-synchronous orbit satellite. The dual-axis sailboard control method includes a control method for each single-axis sailboard in the dual-axis sailboard, as well as a method for implementing the dual-axis joint operation of the sailboard. This method not only ensures the energy supply on the satellite, but also meets the three-axis stabilization requirements of the satellite's orientation to the earth. However, it does not explain the two-dimensional solar pointing method and system for geostationary orbit satellites.

[0007] Patent document CN105620794B (application number: 201610081893.6) discloses a reliable solar panel autonomous tracking sun control method, introducing a solar panel autonomous tracking sun control method, controlling the panel to rotate in different working modes, avoiding the frequent stopping of the panel and the impact of switching between different modes of the panel on the attitude and life of the drive mechanism, but does not explain the two-dimensional solar pointing method and system of the geostationary orbit satellite.

[0008] Patent document CN106096148A (application number: 201610423963.1) discloses a method for pointing solar panels on high-inclination orbit satellites under simple attitude control, and introduces a method for controlling solar panels to autonomously track the sun. This method overcomes the defects of satellites in the prior art that use single-degree-of-freedom solar panel drive mechanisms to meet the requirement that sunlight is perpendicular to the satellite solar panels, in which the satellite yaw angle is always controlled and the solar panel rotation speed is large, which is not conducive to the stability of the satellite payload. By designing three solar panel pointing adjustment modes based on the angle θ between the direction of the sunlight vector and the direction of the satellite orbit normal, the pointing requirements of solar panels on high-inclination orbit satellites are met. However, the two-dimensional solar pointing method and system for geostationary orbit satellites are not described.

[0009] Patent document CN106364702A (application number: 201610810977.9) discloses a solar array control strategy method adapted for yaw maneuvering satellites, and introduces a method for pointing solar panels on yaw maneuvering satellites. Based on the lighting conditions, a satellite yaw maneuvering plan is determined, and based on the satellite yaw maneuvering plan, a solar array control strategy is obtained, thereby solving the energy problem of inclined orbit satellites in orbit. However, it does not describe a two-dimensional solar pointing method and system for geostationary orbit satellites. Summary of the Invention

[0010] In view of the defects in the prior art, the purpose of the present invention is to provide a two-dimensional pointing method and system for solar observation of a geostationary meteorological satellite.

[0011] A two-dimensional pointing method for solar observation of a geostationary meteorological satellite provided by the present invention comprises:

[0012] Step S1: constructing a two-dimensional pointing system for solar observation of a geostationary meteorological satellite;

[0013] Step S2: using the constructed geostationary meteorological satellite solar observation two-dimensional pointing system to perform solar capture, solar search, and solar tracking;

[0014] Step S3: During the sun capture, sun search and sun tracking processes, the closed-loop sun pointing of the solar array in the east-west and north-south directions is realized based on the closed-loop driving control rules in the east-west and north-south directions.

[0015] Preferably, the geostationary meteorological satellite solar observation two-dimensional pointing system comprises: an onboard computer, a solar array drive mechanism, a north-south drive mechanism, and a solar observation guide mirror;

[0016] The onboard computer serves as a controller to control the solar array drive mechanism and the north-south drive mechanism;

[0017] The solar array drive mechanism serves as an east-west actuator;

[0018] The north-south driving mechanism serves as an actuator in the north-south direction;

[0019] The solar observation guide mirror serves as a sensor and is used to control the solar array drive mechanism and the north-south drive mechanism in a feedback closed-loop control manner.

[0020] Preferably, step S2 includes: capturing and controlling the east-west solar pointing angle and the north-south solar pointing angle calculated using the satellite attitude, orbit information, solar array drive mechanism, and north-south drive mechanism rotation angle information as inputs, and observing whether the east-west and north-south solar pointing angles enter the field of view of the solar observation guide mirror after they reach near 0°; if they enter the field of view of the solar observation guide mirror, directly entering the solar tracking process; if they do not enter the solar observation guide mirror, performing a solar search; during the solar search process, when the sun appears in the field of view of the solar observation guide mirror, entering the solar tracking process.

[0021] Preferably, the east-west sun pointing angle includes:

[0022] Step S2.1: Calculate the sun vector in the J2000.0 inertial coordinate system And according to the satellite attitude and orbit, the vector is converted to the satellite celestial coordinate system to obtain the sun vector in the celestial coordinate system The sun vector is a vector pointing from the satellite's mass center to the sun's mass center;

[0023] Step S2.2: Based on the sun vector in the stellar coordinate system Solar array drive mechanism angle A ew and the north-south driving mechanism angle A ns Calculate the sun vector in the solar observation payload coordinate system

[0024]

[0025] Step S2.3: Based on the solar vector in the solar observation payload coordinate system Calculate the sun's pointing angle θ in the east-west direction s ;

[0026]

[0027] Where r ssx Sun vector Component in the X direction; is a vector In X s O s Z s Projection of a surface r ssz is a vector Component in the Z direction; Z is the solar observation load coordinate system s axis,

[0028] Preferably, the north-south direction sun pointing angle includes: according to the sun vector in the solar observation load coordinate system Calculate the sun's pointing angle in the north-south direction

[0029]

[0030] Where r ssy Sun vector Component in the Y direction; is a vector In Y s O s Z s Projection of a surface

[0031] Preferably, the solar search includes: taking the sun pointing angle in the east-west direction and the sun pointing angle in the north-south direction as input, performing a two-dimensional search using a right-angle involute method, and the search stop point interval is the effective field of view range of the solar observation guide mirror. If the sun is not found within ±1°, the search is contracted toward the center.

[0032] Preferably, step S3 includes:

[0033] The solar capture and solar search modes use the calculated east-west solar pointing angle data as input, and the solar tracking mode uses the east-west solar pointing angle measured by the solar observation guide mirror as input. The solar array drive mechanism acts as an actuator to form a feedback control loop, switching the solar cell array speed gear according to the east-west solar pointing angle threshold to adjust the east-west solar pointing angle, thereby realizing closed-loop solar array pointing.

[0034] Preferably, step S3 includes:

[0035] The solar capture and solar search modes use the calculated north-south solar pointing angle data as input, and the solar tracking mode uses the north-south solar pointing angle measured by the solar observation guide mirror as input. The north-south dimensional drive mechanism serves as the actuator to form a feedback control loop. The solar cell array speed gear is switched according to the north-south solar pointing angle threshold to adjust the north-south solar pointing angle, thereby realizing closed-loop solar array pointing.

[0036] A two-dimensional pointing system for solar observation of a geostationary meteorological satellite provided by the present invention comprises:

[0037] Module M1: Construction of a two-dimensional pointing system for solar observation of geostationary meteorological satellites;

[0038] Module M2: Using the constructed geostationary meteorological satellite solar observation two-dimensional pointing system to perform solar capture, solar search and solar tracking;

[0039] Module M3: During the solar capture, solar search, and solar tracking processes, the closed-loop solar array pointing in the east-west and north-south directions is realized based on the closed-loop drive control rules in the east-west and north-south directions.

[0040] Preferably, the geostationary meteorological satellite solar observation two-dimensional pointing system comprises: an onboard computer, a solar array drive mechanism, a north-south drive mechanism, and a solar observation guide mirror;

[0041] The onboard computer serves as a controller to control the solar array drive mechanism and the north-south drive mechanism;

[0042] The solar array drive mechanism serves as an east-west actuator;

[0043] The north-south driving mechanism serves as an actuator in the north-south direction;

[0044] The solar observation guide mirror is used as a sensor to control the solar array drive mechanism and the north-south drive mechanism in a feedback closed-loop control manner;

[0045] The module M2 includes: using the east-west solar pointing angle and the north-south solar pointing angle calculated from the satellite attitude, orbit information, solar array drive mechanism, and north-south drive mechanism rotation angle information as inputs for capture control; after the east-west and north-south solar pointing angles are near 0°, observing whether they enter the field of view of the solar observation guide mirror; if they enter the field of view of the solar observation guide mirror, directly entering the solar tracking process; if they do not enter the field of view of the solar observation guide mirror, performing a solar search; during the solar search process, when the sun appears in the field of view of the solar observation guide mirror, entering the solar tracking process;

[0046] The module M3 includes:

[0047] The solar capture and solar search modes use the calculated east-west solar pointing angle data as input, while the solar tracking mode uses the east-west solar pointing angle measured by the solar observation guide mirror as input. The solar array drive mechanism acts as an actuator to form a feedback control loop. The solar array speed gear is switched according to the east-west solar pointing angle threshold to adjust the east-west solar pointing angle, thus achieving closed-loop solar array solar pointing.

[0048] The module M3 includes:

[0049] The solar capture and solar search modes use the calculated north-south solar pointing angle data as input, and the solar tracking mode uses the north-south solar pointing angle measured by the solar observation guide mirror as input. The north-south dimensional drive mechanism serves as the actuator to form a feedback control loop. The solar cell array speed gear is switched according to the north-south solar pointing angle threshold to adjust the north-south solar pointing angle, thereby realizing closed-loop solar array pointing.

[0050] Compared with the existing technology, the present invention has the following beneficial effects: Unlike general communication and remote sensing satellites, the infrared earth remote sensing instrument carried by the geostationary meteorological satellite requires a stable heat dissipation surface. The satellite +Y surface is used as a heat dissipation surface and cannot be installed with a two-dimensional pointing mechanism; the solar array is already installed on the -Yb surface of the satellite body, and installing a two-dimensional pointing mechanism will cause interference and obstruction problems; the ±Xb and ±Zb surfaces both have the problem of being unable to observe when facing away from the sun, and cannot be used to install a two-dimensional pointing mechanism. Therefore, the commonly used two-dimensional adjustment pointing mechanism solution cannot be applied to geostationary meteorological satellites. The present invention provides a geostationary meteorological satellite solar observation two-dimensional pointing method and system, which solves the problem of two-dimensional pointing of solar observation in east-west and north-south by installing a one-dimensional drive mechanism on the solar array, and provides a two-dimensional drive control method and solar search strategy to achieve real-time and precise pointing of the solar observation payload to the sun, which can be applied to the research and development process of geostationary meteorological satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0052] Figure 1 Schematic diagram of two-dimensional pointing to the sun for geostationary meteorological satellite solar observation.

[0053] Figure 2 This is a diagram showing the composition of the two-dimensional pointing system for solar observation of a geostationary meteorological satellite.

[0054] Figure 3 Schematic diagram of the two-dimensional pointing control scheme for solar observation of a geostationary meteorological satellite.

[0055] Figure 4 Schematic diagram of the east-west and north-south sun pointing angles.

[0056] Figure 5 Schematic diagram of the relationship between the solar observation payload coordinates and the stellar coordinate system.

[0057] Figure 6 Schematic diagram of the two-dimensional search strategy for the right-angle involute sun.

[0058] Figure 7 Schematic diagram of the two-dimensional reverse search strategy for the right-angle involute sun.

[0059] Figure 8 It is the closed-loop driving control law in the east-west and north-south directions. DETAILED DESCRIPTION

[0060] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0061] Example 1

[0062] A two-dimensional pointing method for solar observation of a geostationary meteorological satellite provided by the present invention comprises the following steps:

[0063] Step 1: Design of the composition of the two-dimensional pointing system for geostationary meteorological satellite solar observation;

[0064] Step 2: Calculate the sun's pointing angle in the east-west direction;

[0065] Step 3: Calculate the sun's pointing angle in the north-south direction;

[0066] Step 4: Design of closed-loop driving control law in the east-west direction;

[0067] Step 5: Design of closed-loop driving control law in the north-south direction;

[0068] Step 6: Design of solar search strategy.

[0069] This method is designed for geostationary meteorological satellites operating 36,000 km above the equator. The sun is in the satellite's celestial coordinate system O b X b Y b Z b There is a daily periodic motion in the east-west direction and an annual periodic motion in the north-south direction, such as Figure 1 As shown;

[0070] Since the infrared earth remote sensing instrument carried by the meteorological satellite requires a stable heat dissipation surface, the satellite +Yb surface cannot be installed with a two-dimensional pointing mechanism as a heat dissipation surface; the satellite body -Yb surface has already been installed with a solar array, and installing a two-dimensional pointing mechanism will cause interference and obstruction problems; the ±Xb and ±Zb surfaces both have the problem of being unable to observe when facing away from the sun, and cannot be used to install a two-dimensional pointing mechanism. Therefore, the payload and the north-south driving mechanism are installed on the solar array connecting frame, and the solar array driving mechanism realizes the east-west direction of the sun, and the north-south driving mechanism realizes the north-south direction of the sun to achieve the two-dimensional pointing of the payload optical axis to the sun, such as Figure 1 The two-dimensional pointing system for solar observation of geostationary meteorological satellites consists of onboard computers, solar array drive mechanisms, north-south drive mechanisms, solar observation guide mirrors and other individual components, as shown in Figure 1. Figure 2 The onboard computer serves as the controller, the solar array drive mechanism serves as the east-west actuator, and the north-south drive mechanism serves as the north-south actuator. Feedback closed-loop control is used to control the solar observation payload to align with the sun in real time.

[0071] The east-west solar pointing angle is the solar vector in the solar observation load coordinate system X s O s Z s Projection within the plane and -Z s The angle between the axes, such as Figure 4 Middle θ s The solar vector is the vector from the satellite mass center to the sun mass center, and the solar observation payload coordinate system is defined as: origin O s Defined as the center of the solar observation payload detector, O s X s The axis is parallel to the north-south drive mechanism, O s Z s Axis and O s X s The axis is vertical and points in the opposite direction of the principal optical axis of the solar observation payload, O s Y s The axis follows the right-hand rule, as shown in the attached Figure 5 When the solar array drive mechanism and the north-south drive mechanism are both at 0°, the solar observation load coordinate system O s X s Ys Z s With the stellar coordinate system O b X b Y b Z b parallel;

[0072] The north-south solar pointing angle is the solar vector in the solar observation load coordinate system Y s O s Z s Projection within the plane and -Z s The angle between the axes, such as Figure 4 middle As shown;

[0073] Due to the influence of ground installation errors, on-orbit forces, and thermal deformation, there are large deviations in the east-west and north-south solar pointing angles calculated by the onboard computer according to the nominal installation matrix. The field of view of the solar observation payload is small, which may result in the sun still not entering the effective field of view of the payload even after precise control has been completed using the calculated value of the onboard computer as the control input. It is necessary to perform a solar search to make the sun enter the field of view of the solar observation payload (because the solar observation payload and the solar observation guide mirror are installed with a common reference, the optical axis deviation is better than 10″ (3σ), and entering the field of view of the guide mirror means entering the field of view of the solar observation payload. During the search process, the sun entering the field of view of the guide mirror is used as the sign of the sun entering the field of view), and the control input is switched to the measurement value of the solar observation guide mirror;

[0074] Taking the east-west sun pointing angle as the control input, the east-west sun pointing accuracy is kept within the specification range by adjusting the rotation speed of the solar array drive mechanism;

[0075] The north-south sun pointing angle is used as the control input, and the north-south sun pointing accuracy is maintained within the specification range by adjusting the rotation speed of the north-south drive mechanism.

[0076] Example 2

[0077] A two-dimensional pointing method for solar observation of a geostationary meteorological satellite provided by the present invention comprises:

[0078] Step S1: Design of the composition of the two-dimensional pointing system for geostationary meteorological satellite solar observation.

[0079] Step S2: Design of a two-dimensional pointing scheme for solar observation of a geostationary meteorological satellite.

[0080] Step S3: Calculate the sun's pointing angle in the east-west direction.

[0081] Step S4: Calculate the sun pointing angle in the north-south direction.

[0082] Step S5: Sun search strategy design.

[0083] Step S6: Design of closed-loop drive control law in the east-west direction.

[0084] Step S7: Design of closed-loop driving control law in the north-south direction.

[0085] Specifically, the step S1 includes: the two-dimensional pointing system for solar observation of a geostationary meteorological satellite is composed of a satellite computer, a solar array drive mechanism, a north-south drive mechanism, a solar observation guide mirror and other individual components, as shown in the attached figure. Figure 2 The onboard computer serves as the controller, the solar array drive mechanism serves as the east-west actuator, the north-south drive mechanism serves as the north-south actuator, and the solar observation guidance mirror serves as the sensor. Feedback closed-loop control is used to control the solar array drive mechanism and the north-south drive mechanism, ensuring that the solar observation payload is aligned with the sun in real time.

[0086] Specifically, the step S2 includes: the two-dimensional pointing control process of the geostationary meteorological satellite solar observation includes sub-processes such as initial solar capture, solar search, and solar tracking. The initial solar capture uses the east-west and north-south solar pointing angles calculated from the satellite attitude, orbit information, solar array drive mechanism, and north-south dimensional drive mechanism angle information as input for capture control. After the east-west and north-south solar pointing angles are near 0°, it is observed whether they enter the field of view of the solar observation guide mirror. If they enter the field of view of the solar observation guide mirror, the solar tracking process is directly entered; if they do not enter the solar observation guide mirror, a solar search is performed. In the solar search process, when the sun appears in the field of view of the solar observation guide mirror, the solar tracking process is entered, as shown in the attached figure. Figure 3 shown.

[0087] Specifically, step S3 includes:

[0088] S31. Calculate the solar vector in the J2000.0 inertial coordinate system And according to the satellite attitude and orbit, the vector is converted to the satellite celestial coordinate system to obtain the sun vector in the celestial coordinate system This calculation method is a common calculation method in the aerospace field and will not be described in detail in the present invention. The solar vector is a vector pointing from the satellite's center of mass to the sun's center of mass.

[0089] S32, according to the solar vector in the stellar coordinate system Solar array drive mechanism angle A ew and the north-south driving mechanism angle A ns Calculate the sun vector in the solar observation payload coordinate system

[0090]

[0091] The solar observation payload coordinate system is defined as: origin O s Defined as the center of the solar observation payload detector, Os X s The axis is parallel to the north-south drive mechanism, O s Z s Axis and O s X s The axis is vertical and points in the opposite direction of the principal optical axis of the solar observation payload, O s Y s The axis follows the right-hand rule, as shown in the attached Figure 4 When the solar array drive mechanism and the north-south drive mechanism are both at 0°, the solar observation load coordinate system O s X s Y s Z s With the stellar coordinate system O b X b Y b Z b parallel.

[0092] S33, according to the solar vector in the solar observation payload coordinate system Calculate the sun's pointing angle θ in the east-west direction s The east-west solar pointing angle is the solar vector in the solar observation load coordinate system X s O s Z s Projection within the plane and -Z s The angle of the axis, as shown in the Figure 4 Middle θ s shown.

[0093]

[0094] Where r ssx Sun vector Component in the X direction; is a vector In X s O s Z s Projection of a surface r ssz is a vector Component in the Z direction; Z is the solar observation load coordinate system s axis,

[0095] Preferably, the step S4 comprises: according to the solar vector in the solar observation payload coordinate system Calculate the sun's pointing angle in the north-south direction The north-south solar pointing angle is the solar vector in the solar observation load coordinate system Y s O s Z s Projection within the plane and -Z sThe angle of the axis, as shown in the Figure 4 middle shown.

[0096]

[0097] Where r ssy Sun vector Component in the Y direction; is a vector In Y s O s Z s Projection of a surface

[0098] Specifically, step S5 includes: using the east-west and north-south sun pointing angle data obtained in steps S2 and S3 as input, performing a two-dimensional search using a right-angle involute method, and searching for a stationary point interval position that is the effective field of view range of the solar observation guide mirror (0.2°), as shown in the attached figure. Figure 6 If the sun is not found within ±1°, search towards the center, as shown in the following figure. Figure 7 shown.

[0099] Specifically, step S6 includes: initial solar capture, solar search, and solar tracking modes use the same east-west closed-loop drive control law, with only different control parameters. The solar capture and solar search modes use the east-west solar pointing angle data obtained in step S2 as input, and the solar tracking mode uses the east-west solar pointing angle measured by the solar observation guide mirror as input. The solar array drive mechanism serves as an actuator to form a feedback control loop, switching the solar cell array speed gear according to the east-west solar pointing angle threshold to adjust the east-west solar pointing angle, thereby achieving closed-loop solar array solar pointing, as shown in the attached figure. Figure 8 In this step, R0, R1, and R2 are the east-west sun pointing angle control thresholds, ω0, ω1, and ω2 are the solar array drive speed gears, and θ0 is the east-west target position. In the solar capture and solar tracking modes, θ0 = 0; in the solar search mode, θ0 is the east-west search target position, that is, Figure 6 , Attachment Figure 7 The middle positions 0 to 17 correspond to the east-west target angles.

[0100] Specifically, step S7 includes: initial solar capture, solar search, and solar tracking modes use the same north-south closed-loop drive control law, with only different control parameters. The solar capture and solar search modes use the north-south solar pointing angle data obtained in step S2 as input, and the solar tracking mode uses the north-south solar pointing angle measured by the solar observation guide mirror as input. The north-south driving mechanism serves as an actuator to form a feedback control loop, and the solar array speed gear is switched according to the north-south solar pointing angle threshold to adjust the north-south solar pointing angle, thereby achieving closed-loop solar array pointing to the sun, as shown in the attached figure. Figure 8 In this step, R0, R1, and R2 are the north-south sun pointing angle control thresholds, ω0, ω1, and ω2 are the solar array drive speed gears, and θ0 is the north-south target position. In the sun capture and sun tracking modes, θ0 = 0; in the sun search mode, θ0 is the north-south search target position, that is, Figure 6 , Attachment Figure 7 The north-south target angles corresponding to positions 0 to 17.

[0101] The present invention also provides a two-dimensional pointing system for solar observation of a geostationary meteorological satellite. The two-dimensional pointing system for solar observation of a geostationary meteorological satellite can be realized by executing the process steps of the two-dimensional pointing method for solar observation of a geostationary meteorological satellite. That is, those skilled in the art can understand the two-dimensional pointing method for solar observation of a geostationary meteorological satellite as an optimal implementation of the two-dimensional pointing system for solar observation of a geostationary meteorological satellite.

[0102] Those skilled in the art will appreciate that, in addition to implementing the system, device, and various modules provided by the present invention in purely computer-readable program code, it is entirely possible to implement the same program in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, embedded microcontrollers, and the like by logically programming the method steps. Therefore, the system, device, and various modules provided by the present invention can be considered a hardware component, and the modules included therein for implementing various programs can also be considered structures within the hardware component; the modules for implementing various functions can also be considered both software programs for implementing the method and structures within the hardware component.

[0103] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A two-dimensional pointing method for solar observation of a geostationary meteorological satellite, characterized in that: include: Step S1: constructing a two-dimensional pointing system for solar observation of a geostationary meteorological satellite; Step S2: using the constructed geostationary meteorological satellite solar observation two-dimensional pointing system to perform solar capture, solar search, and solar tracking; Step S3: During the sun capture, sun search and sun tracking processes, the closed-loop sun pointing of the solar array in the east-west and north-south directions is realized based on the closed-loop driving control rules in the east-west and north-south directions.

2. The two-dimensional pointing method for solar observation of a geostationary meteorological satellite according to claim 1, characterized in that: The two-dimensional pointing system for solar observation of a geostationary meteorological satellite comprises: an onboard computer, a solar array drive mechanism, a north-south drive mechanism, and a solar observation guide mirror; The onboard computer serves as a controller to control the solar array drive mechanism and the north-south drive mechanism; The solar array drive mechanism serves as an east-west actuator; The north-south driving mechanism serves as an actuator in the north-south direction; The solar observation guide mirror serves as a sensor and is used to control the solar array drive mechanism and the north-south drive mechanism in a feedback closed-loop control manner.

3. The two-dimensional pointing method for solar observation of a geostationary meteorological satellite according to claim 1, characterized in that: The step S2 includes: using the east-west solar pointing angle and the north-south solar pointing angle calculated from the satellite attitude, orbit information, solar array drive mechanism, and north-south driving mechanism rotation angle information as inputs for capture control, and after the east-west and north-south solar pointing angles are near 0°, observing whether they enter the field of view of the solar observation guide mirror; if they enter the field of view of the solar observation guide mirror, directly entering the solar tracking process; if they do not enter the solar observation guide mirror, performing a solar search; during the solar search process, when the sun appears in the field of view of the solar observation guide mirror, entering the solar tracking process.

4. The two-dimensional pointing method for solar observation of a geostationary meteorological satellite according to claim 3, characterized in that: The east-west sun pointing angle includes: Step S2.1: Calculate the sun vector in the J2000.0 inertial coordinate system And according to the satellite attitude and orbit, the vector is converted to the satellite star coordinate system to obtain the sun vector in the star coordinate system The sun vector is a vector pointing from the satellite's mass center to the sun's mass center; Step S2.2: Based on the sun vector in the stellar coordinate system Solar array drive mechanism angle A ew and the north-south driving mechanism angle A ns Calculate the sun vector in the solar observation payload coordinate system Step S2.3: Based on the solar vector in the solar observation payload coordinate system Calculate the sun's pointing angle θ in the east-west direction s ; Where r ssx Sun vector Component in the X direction; is a vector In X s O s Z s Projection of a surface r ssz is a vector Component in the Z direction; Z is the solar observation load coordinate system s axis, 5. The two-dimensional pointing method for solar observation of a geostationary meteorological satellite according to claim 3, characterized in that: The north-south direction sun pointing angle includes: Calculate the sun's pointing angle in the north-south direction Where r ssy Sun vector Component in the Y direction; is a vector In Y s O s Z s Projection of a surface 6. The two-dimensional pointing method for solar observation of a geostationary meteorological satellite according to claim 3, characterized in that: The solar search includes: taking the sun pointing angle in the east-west direction and the sun pointing angle in the north-south direction as input, using a right-angle involute method to perform a two-dimensional search, and the interval position of the search station point is the effective field of view range of the solar observation guide mirror. If the sun is still not found within the search of ±1°, the search is narrowed toward the center.

7. The two-dimensional pointing method for solar observation of a geostationary meteorological satellite according to claim 1, characterized in that: The step S3 comprises: The solar capture and solar search modes use the calculated east-west solar pointing angle data as input, and the solar tracking mode uses the east-west solar pointing angle measured by the solar observation guide mirror as input. The solar array drive mechanism acts as an actuator to form a feedback control loop, switching the solar cell array speed gear according to the east-west solar pointing angle threshold to adjust the east-west solar pointing angle, thereby realizing closed-loop solar array pointing.

8. The two-dimensional pointing method for solar observation of a geostationary meteorological satellite according to claim 1, characterized in that: The step S3 comprises: The solar capture and solar search modes use the calculated north-south solar pointing angle data as input, and the solar tracking mode uses the north-south solar pointing angle measured by the solar observation guide mirror as input. The north-south dimensional drive mechanism serves as the actuator to form a feedback control loop. The solar cell array speed gear is switched according to the north-south solar pointing angle threshold to adjust the north-south solar pointing angle, thereby realizing closed-loop solar array pointing.

9. A two-dimensional pointing system for solar observation of a geostationary meteorological satellite, characterized in that: include: Module M1: Construction of a two-dimensional pointing system for solar observation of geostationary meteorological satellites; Module M2: Using the constructed geostationary meteorological satellite solar observation two-dimensional pointing system to perform solar capture, solar search and solar tracking; Module M3: During the solar capture, solar search, and solar tracking processes, the closed-loop solar array pointing in the east-west and north-south directions is realized based on the closed-loop drive control rules in the east-west and north-south directions.

10. The two-dimensional pointing system for solar observation of a geostationary meteorological satellite according to claim 9, characterized in that: The two-dimensional pointing system for solar observation of a geostationary meteorological satellite comprises: an onboard computer, a solar array drive mechanism, a north-south drive mechanism, and a solar observation guide mirror; The onboard computer serves as a controller to control the solar array drive mechanism and the north-south drive mechanism; The solar array drive mechanism serves as an east-west actuator; The north-south driving mechanism serves as an actuator in the north-south direction; The solar observation guide mirror is used as a sensor to control the solar array drive mechanism and the north-south drive mechanism in a feedback closed-loop control manner; The module M2 includes: using the east-west solar pointing angle and the north-south solar pointing angle calculated from the satellite attitude, orbit information, solar array drive mechanism, and north-south drive mechanism rotation angle information as inputs for capture control; after the east-west and north-south solar pointing angles are near 0°, observing whether they enter the field of view of the solar observation guide mirror; if they enter the field of view of the solar observation guide mirror, directly entering the solar tracking process; if they do not enter the field of view of the solar observation guide mirror, performing a solar search; during the solar search process, when the sun appears in the field of view of the solar observation guide mirror, entering the solar tracking process; The module M3 includes: The solar capture and solar search modes use the calculated east-west solar pointing angle data as input, while the solar tracking mode uses the east-west solar pointing angle measured by the solar observation guide mirror as input. The solar array drive mechanism acts as an actuator to form a feedback control loop. The solar array speed gear is switched according to the east-west solar pointing angle threshold to adjust the east-west solar pointing angle, thus achieving closed-loop solar array solar pointing. The module M3 includes: The solar capture and solar search modes use the calculated north-south solar pointing angle data as input, and the solar tracking mode uses the north-south solar pointing angle measured by the solar observation guide mirror as input. The north-south dimensional drive mechanism serves as the actuator to form a feedback control loop. The solar cell array speed gear is switched according to the north-south solar pointing angle threshold to adjust the north-south solar pointing angle, thereby realizing closed-loop solar array pointing.

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