Satellite on-orbit control method and related device

Abstract

Embodiments of the present application provide a method for on-orbit control of a satellite and related equipment, which can avoid excessive energy consumption of the satellite. The method comprises: determining whether there is a first task to be executed at a current time during autonomous operation of a target satellite; when the first task exists at the current time, determining a target type corresponding to the first task; and when the target satellite executes the first task, controlling operation of the target satellite based on a low-power consumption operation strategy corresponding to the target type.

Description

Technical Field

[0001] This invention relates to the field of satellite design, and more particularly to an on-orbit control method for satellites and related equipment. Background Technology

[0002] An artificial satellite is an unmanned spacecraft that orbits the Earth in space. Artificial satellites generally follow the laws of celestial mechanics when orbiting the Earth.

[0003] Currently, when artificial satellites are in orbit, they generally operate at full power because they frequently perform corresponding tasks. While operating at full power can meet the needs of mission execution, it results in excessive energy consumption for the satellite. Summary of the Invention

[0004] This invention provides an on-orbit control method and related equipment for satellites, which can avoid excessive energy consumption of satellites.

[0005] The first aspect of this invention provides an on-orbit control method for a satellite, applied to a target satellite, the method comprising:

[0006] During the autonomous operation of the target satellite, it is determined whether there is a first task to be executed at the current moment;

[0007] When the first task exists at the current moment, determine the target type corresponding to the first task;

[0008] When the target satellite performs the first task, the operation of the target satellite is controlled based on the low-power operation strategy corresponding to the target type.

[0009] In one possible design, controlling the operation of the target satellite based on the low-power operation strategy corresponding to the target type includes:

[0010] When the target type is a telemetry and control mission type, determine whether the first orbit extrapolation duration of the target satellite at the current moment is greater than a first preset threshold.

[0011] When the extrapolation time of the first orbit is less than the first preset threshold, the telemetry and control transponder corresponding to the target satellite is turned on, and the telemetry and control transponder is turned off when the first task is detected to have been completed.

[0012] When the extrapolation duration of the first orbit exceeds the first preset threshold, the global navigation satellite module corresponding to the target satellite is powered on, and the position and on-board time of the target satellite are updated based on the global navigation satellite module.

[0013] When the position of the target satellite and the onboard time update are detected, the telemetry, tracking, and command transponder is turned on, and when the first task is detected to have been completed, the telemetry, tracking, and command transponder is turned off.

[0014] In one possible design, controlling the operation of the target satellite based on the low-power operation strategy corresponding to the target type includes:

[0015] When the target type is a data transmission mission to Earth, determine whether the second orbit extrapolation duration of the target satellite at the current moment is less than a second preset threshold.

[0016] When the second orbit extrapolation time is less than the second preset threshold, the flywheel corresponding to the target satellite is activated, and the flywheel is controlled to adjust the attitude of the target satellite so that the attitude of the target satellite is a staring attitude toward the Earth.

[0017] Based on the adjusted attitude of the target satellite, transmit the data corresponding to the first task;

[0018] When the second orbit extrapolation duration exceeds the second preset threshold, the global navigation satellite module corresponding to the target satellite is powered on, and the position and on-board time of the target satellite are updated based on the global navigation satellite module.

[0019] When the position of the target satellite and the onboard time update are detected, the flywheel corresponding to the target satellite is activated, and the flywheel is controlled to adjust the attitude of the target satellite so that the attitude of the target satellite is a staring attitude towards the Earth, and the data corresponding to the first task is transmitted based on the adjusted attitude of the target satellite.

[0020] In one possible design, controlling the operation of the target satellite based on the low-power operation strategy corresponding to the target type includes:

[0021] When the target type is a remote sensing imaging mission, the position of the target satellite and its onboard information are updated based on the global navigation satellite module corresponding to the target satellite.

[0022] The attitude of the target satellite is adjusted to the target attitude corresponding to the remote sensing imaging mission based on the star sensor and / or the flywheel corresponding to the target satellite.

[0023] The remote sensing imaging task is performed based on the target attitude.

[0024] In one possible design, after controlling the target satellite's operation based on the low-power operation strategy, the method further includes:

[0025] Obtain the execution time of the second task, which is the task to be performed after the target satellite has performed the first task;

[0026] When the time interval between the execution time and the current time is less than a third preset threshold, the attitude of the target satellite is adjusted according to the task type of the second task.

[0027] In one possible design, the method further includes;

[0028] When the time interval between the execution time and the current time is greater than the third preset threshold, the execution task device corresponding to the target satellite is determined;

[0029] The device performing the task is turned off.

[0030] In one possible design, shutting down the task-performing device includes:

[0031] Power off the global navigation satellite module corresponding to the target satellite;

[0032] Control the shutdown of the telemetry, tracking, and command (TT&C) transponder corresponding to the target satellite;

[0033] The star sensor, terameter, and magnetometer corresponding to the target satellite are powered off.

[0034] The flywheel corresponding to the target satellite is shut down.

[0035] In one possible design, the method further includes:

[0036] When the global navigation satellite module corresponding to the target satellite is powered off, the power-off time of the global navigation satellite module corresponding to the target satellite is accumulated;

[0037] If the shutdown duration exceeds the threshold, the global navigation satellite module corresponding to the target satellite is activated, and the position and onboard time of the target satellite are updated.

[0038] When the star sensor, the solar sensor, and the magnetometer are powered off, the current attitude of the target satellite is determined by gyroscope integration and the solar cell matrix corresponding to the target satellite.

[0039] When the deviation between the current attitude and the target satellite's orbit is greater than a fourth preset threshold, the solar sensor and the magnetometer are activated, and the current attitude is adjusted based on the solar sensor and the magnetometer.

[0040] When the flywheel is powered off, the attitude of the target satellite is controlled by the magnetic torque device corresponding to the target satellite.

[0041] A second aspect of the present invention provides an on-orbit control device for a satellite, the device comprising:

[0042] The judgment module is used to determine whether there is a first task to be executed at the current moment during the autonomous operation of the target satellite;

[0043] The determination module is used to determine the target type corresponding to the first task when the first task exists at the current time;

[0044] The control module is used to control the operation of the target satellite based on the low-power operation strategy corresponding to the target type when the target satellite performs the first task.

[0045] In one possible design, the control module is specifically used for:

[0046] When the target type is a telemetry and control mission type, determine whether the first orbit extrapolation duration of the target satellite at the current moment is greater than a first preset threshold.

[0047] When the extrapolation time of the first orbit is less than the first preset threshold, the telemetry and control transponder corresponding to the target satellite is turned on, and the telemetry and control transponder is turned off when the first task is detected to have been completed.

[0048] When the extrapolation duration of the first orbit exceeds the first preset threshold, the global navigation satellite module corresponding to the target satellite is powered on, and the position and on-board time of the target satellite are updated based on the global navigation satellite module.

[0049] When the position of the target satellite and the onboard time update are detected, the telemetry, tracking, and command transponder is turned on, and when the first task is detected to have been completed, the telemetry, tracking, and command transponder is turned off.

[0050] In one possible design, the control module is further specifically used for:

[0051] When the target type is a data transmission mission to Earth, determine whether the second orbit extrapolation duration of the target satellite at the current moment is less than a second preset threshold.

[0052] When the second orbit extrapolation time is less than the second preset threshold, the flywheel corresponding to the target satellite is activated, and the flywheel is controlled to adjust the attitude of the target satellite so that the attitude of the target satellite is a staring attitude toward the Earth.

[0053] Based on the adjusted attitude of the target satellite, transmit the data corresponding to the first task;

[0054] When the second orbit extrapolation duration exceeds the second preset threshold, the global navigation satellite module corresponding to the target satellite is powered on, and the position and on-board time of the target satellite are updated based on the global navigation satellite module.

[0055] When the position of the target satellite and the onboard time update are detected, the flywheel corresponding to the target satellite is activated, and the flywheel is controlled to adjust the attitude of the target satellite so that the attitude of the target satellite is a staring attitude towards the Earth, and the data corresponding to the first task is transmitted based on the adjusted attitude of the target satellite.

[0056] In one possible design, the control module is further specifically used for:

[0057] When the target type is a remote sensing imaging mission, the position of the target satellite and its onboard information are updated based on the global navigation satellite module corresponding to the target satellite.

[0058] The attitude of the target satellite is adjusted to the target attitude corresponding to the remote sensing imaging mission based on the star sensor and / or the flywheel corresponding to the target satellite.

[0059] The remote sensing imaging task is performed based on the target attitude.

[0060] In one possible design, the control module is further used for:

[0061] Obtain the execution time of the second task, which is the task to be performed after the target satellite has performed the first task;

[0062] When the time interval between the execution time and the current time is less than a third preset threshold, the attitude of the target satellite is adjusted according to the task type of the second task.

[0063] In one possible design, the control module is further used for:

[0064] When the time interval between the execution time and the current time is greater than the third preset threshold, the execution task device corresponding to the target satellite is determined;

[0065] The device performing the task is turned off.

[0066] In one possible design, the control module shuts down the task-performing device by:

[0067] Power off the global navigation satellite module corresponding to the target satellite;

[0068] Control the shutdown of the telemetry, tracking, and command (TT&C) transponder corresponding to the target satellite;

[0069] The star sensor, terameter, and magnetometer corresponding to the target satellite are powered off.

[0070] The flywheel corresponding to the target satellite is shut down.

[0071] In one possible design, the control module is further used for:

[0072] When the global navigation satellite module corresponding to the target satellite is powered off, the power-off time of the global navigation satellite module corresponding to the target satellite is accumulated;

[0073] If the shutdown duration exceeds the threshold, the global navigation satellite module corresponding to the target satellite is activated, and the position and onboard time of the target satellite are updated.

[0074] When the star sensor, the solar sensor, and the magnetometer are powered off, the current attitude of the target satellite is determined by gyroscope integration and the solar cell matrix corresponding to the target satellite.

[0075] When the deviation between the current attitude and the target satellite's orbit is greater than a fourth preset threshold, the solar sensor and the magnetometer are activated, and the current attitude is adjusted based on the solar sensor and the magnetometer.

[0076] When the flywheel is powered off, the attitude of the target satellite is controlled by the magnetic torque device corresponding to the target satellite.

[0077] A third aspect of the present invention provides an electronic device, including a memory and a processor, wherein the processor is configured to execute a computer management program stored in the memory to implement the steps of the on-orbit control method for a satellite as described in the first aspect above.

[0078] A fourth aspect of the present invention provides a computer-readable storage medium having a computer management program stored thereon, which, when executed by a processor, implements the steps of the on-orbit control method for a satellite as described in the first aspect above.

[0079] In summary, it can be seen that in the embodiments provided by the present invention, when there is a first task to be executed at the current moment, the satellite operation is controlled according to the low-power operation strategy corresponding to the task type of the first task. This avoids the waste of energy caused by turning on all the satellite's equipment when the satellite has a task to perform. Attached Figure Description

[0080] Figure 1 A flowchart illustrating the on-orbit control method for a satellite provided in an embodiment of the present invention;

[0081] Figure 2A virtual structural diagram of the on-orbit control device for a satellite provided in an embodiment of the present invention;

[0082] Figure 3 A schematic diagram of the hardware structure of the on-orbit control device for a satellite provided in an embodiment of the present invention;

[0083] Figure 4 A schematic diagram of an embodiment of the electronic device provided in this invention;

[0084] Figure 5 A schematic diagram illustrating an embodiment of a computer-readable storage medium provided in this invention. Detailed Implementation

[0085] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0086] In the following description, specific embodiments of the invention will be illustrated with reference to steps and symbols performed by one or more computers, unless otherwise stated. Therefore, these steps and operations will be referred to several times as being performed by a computer, and computer execution as referred to herein includes operations by a computer processing unit representing electronic signals of data in a structured format. This operation transforms the data or maintains it at a location in the computer's memory system, which can be reconfigured or otherwise alter the operation of the computer in a manner well known to those skilled in the art. The data structure maintained by the data is the physical location of the memory, which has specific characteristics defined by the data format. However, the principles of the invention described above are not intended to be limiting, and those skilled in the art will understand that many of the steps and operations described below can also be implemented in hardware.

[0087] The principles of this invention are applied using many other general-purpose or purpose-specific computing, communication environments, or configurations. Examples of well-known computing systems, environments, and configurations suitable for use with this invention include (but are not limited to) handheld phones, personal computers, servers, multiprocessor systems, microcomputer-based systems, mainframe computers, and distributed computing environments, including any of the aforementioned systems or devices.

[0088] The terms "first," "second," and "third," etc., used in this invention are used to distinguish different objects, not to describe a specific order. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion.

[0089] The satellite platform consists of a power supply subsystem, a telemetry and control subsystem, an attitude and orbit control subsystem, a thermal control subsystem, a structural and thermal control subsystem, and a data management subsystem.

[0090] The current attitude and orbit control subsystem uses attitude sensors including analog sun sensors, digital sun sensors, star sensors, magnetometers, and gyroscopes. To ensure mission reliability, multiple attitude sensors are typically used in a heterogeneous backup configuration, with compatibility checks performed on-board to guarantee attitude sensing results. Actuators mainly consist of high-precision components such as flywheels, magnetic torquers, and propulsion systems. However, considering the propellant consumption required for propulsion systems, flywheels and magnetic torquers are generally used as actuators for long-term on-orbit missions. On-board time reference and position sensitivity are ensured by the Global Navigation Satellite System (GNSS), and the onboard computer possesses excellent orbit extrapolation and timekeeping capabilities.

[0091] The current configuration primarily considers backup use and mission accuracy, with room for optimization when used in conjunction with specific missions. For the telemetry, tracking, and command (TT&C) subsystem, X-band, S-band, and VHF / UHF band TT&C are commonly used. For simplified long-term ground-based TT&C management, it typically operates in long-term on-orbit standby mode with dual-machine hot standby and a power-on mode when passing through the target area. However, during long-term missions, the number of ground-based TT&C support sites is limited, resulting in some idle capacity. Fully utilizing the satellite mission characteristics and onboard configuration for low-power design will make better use of the onboard configuration, reduce the power supply subsystem configuration requirements, and decrease satellite mass and launch costs, which is of great significance.

[0092] For general attitude-sensitive components, the configuration includes: analog sun sensors, digital sun sensors, star sensors, and magnetometers. The satellite employs a combined battery pack and solar array power supply scheme, with one or more solar panels or bulk solar arrays onboard, which can be used as sensing devices depending on illumination conditions. For conventional attitude control, a flywheel + magnetic torque control scheme is used. Based on the mission, the platform support requirements for different missions are categorized as follows:

[0093] 1. High-precision time synchronization guarantee: GNSS is required for second pulse time synchronization, and there are requirements for satellite-to-ground time difference. GNSS units need to perform time synchronization in seconds, such as in remote sensing imaging missions and satellite-to-ground communication missions.

[0094] 2. High-precision attitude control guarantee: Flywheel is required for attitude control to ensure control accuracy, and star sensor ensures attitude sensitivity accuracy, such as during remote imaging and inter-satellite laser communication services.

[0095] 3. Telemetry and remote control requirements: Telemetry and control support is required. The telemetry and control transponder must be powered on to ensure remote control reception capability, and the transmitter must be powered on to ensure telemetry downlink capability.

[0096] 4. Staring at a target point: The target point needs to be pointed at by the satellite's given axis, such as in data transmission missions to the ground (data transmission antenna is not a wide-beam phased array antenna), staring imaging missions, etc.

[0097] During periods without mission requirements, the satellite employs a low-angular-velocity, sun-oriented, self-rotating attitude to ensure GNSS availability and rate damping duration requirements after startup, or a stable, sun-oriented, three-axis stable attitude. When the onboard GNSS is shut down for extended periods, the satellite's operational computer performs orbit extrapolation. Gyroscopes are used for attitude sensitivity, and attitude verification is performed based on solar array current and satellite attitude to ensure accuracy. When attitude deviations are excessive, the sun sensor combined with a magnetometer is activated for dual-vector attitude determination. Simultaneously, an interval T is set according to the GNSS startup to orbit determination and stable operation duration requirements. When the satellite is in this state for a duration exceeding T, GNSS is activated for onboard time updates to prevent excessive time differences between the satellite and ground stations. During extended periods of shutdown, the onboard telemetry and control system is activated by the operational computer upon passing a telemetry and control station, and the transmitter is turned on for downlink telemetry data. Based on mission requirements, the operational computer performs onboard mission planning and controls the status of onboard products upon triggering various boundary conditions. Before the mission begins, a magnetic torque converter and flywheel perform rapid rate damping and attitude adjustments to ensure mission attitude. For missions with high attitude control requirements, the satellite sensor should be powered on in advance to ensure its availability. According to the mission plan, a single copy of the telemetry and control transponder should be turned on before passing the telemetry and control station, and turned off during the non-stationing period.

[0098] The following section will provide a detailed explanation of the satellite's on-orbit control method, focusing on the on-orbit control device. This on-orbit control device can be a server or a service unit within a server; no specific limitation is made.

[0099] Please see Figure 1 , Figure 1 A flowchart illustrating the on-orbit control method for a satellite provided in an embodiment of the present invention includes:

[0100] 101. During the autonomous operation of the target satellite, determine whether there is a first task to be executed at the current moment. If so, proceed to step 102.

[0101] In this embodiment, the target satellite can be, for example, a remote sensing satellite. During the autonomous operation of the target satellite, it is determined whether there is a first task to be executed at the current moment. If there is a first task at the current moment, then step 102 is executed.

[0102] It should be noted that the target satellite's mission can be constrained by the following constraints:

[0103] 1. Task-triggered remote sensing, long-term on-orbit hibernation, not sensitive to attitude;

[0104] 2. With ground station A as the target data transmission and telemetry station, the telemetry and control requirements are planned at 1 time / day;

[0105] 3. The data transmission requirement is the first data transmission after the mission, and the antenna is not a wide-beam phased array;

[0106] 4. It has remote sensing imaging capabilities.

[0107] 102. Determine the target type corresponding to the first task.

[0108] In this embodiment, the satellite's on-orbit control device can determine the target type corresponding to the first mission. The target type includes, but is not limited to, telemetry and control missions, Earth data transmission missions, and remote sensing imaging missions.

[0109] 103. When the target satellite is performing its first mission, control the operation of the target satellite based on the low-power operation strategy corresponding to the target type.

[0110] In this embodiment, the satellite's on-orbit control device can control the target satellite's operation based on the low-power operation strategy corresponding to the target type of the first mission when the target satellite is performing the first mission. For ease of understanding, the following will explain in detail how to control the target satellite's low-power operation, taking the target type as telemetry and control mission type, ground data transmission mission type, and remote sensing imaging mission type respectively:

[0111] I. When the target type is a telemetry, tracking, and command (TT&C) mission, the satellite's on-orbit control system controls the target satellite's operation based on the low-power operation strategy corresponding to the target type, including:

[0112] When the target type is a telemetry and control mission, determine whether the first orbit extrapolation duration of the target satellite at the current moment is greater than the first preset threshold.

[0113] When the extrapolation time of the first orbit is less than the first preset threshold, the telemetry and control transponder corresponding to the target satellite is turned on, and the telemetry and control transponder is turned off when the first mission is detected to be completed.

[0114] When the extrapolation duration of the first orbit exceeds the first preset threshold, the global navigation satellite module corresponding to the target satellite is powered on, and the position and on-board time of the target satellite are updated based on the global navigation satellite module.

[0115] When the position of the target satellite is detected and the onboard time is updated, the telemetry, tracking, and command transponder is turned on, and when the first mission is detected to be completed, the telemetry, tracking, and command transponder is turned off.

[0116] In this embodiment, when the satellite's on-orbit control device determines that the target type is a telemetry and control mission, it can determine whether the first orbit extrapolation time of the target satellite at the current moment is greater than a first preset threshold (the first preset threshold can be, for example, 24 hours, and can also be adjusted according to the actual situation, without limitation). When it is determined that the first orbit extrapolation time is less than the first preset threshold, the telemetry and control transponder is turned on, and then the telemetry and control mission is executed based on the telemetry and control transponder. The device also monitors in real time whether the telemetry and control mission has been completed. When the telemetry and control mission is completed, the telemetry and control transponder is turned off.

[0117] When the extrapolation duration of the first orbit is determined to be greater than the first preset threshold, the GNNS is activated, and the position and on-board time of the target satellite are updated based on the GNNS. After the update is completed, the telemetry and control transponder is activated, and the telemetry and control mission is performed based on the telemetry and control transponder. When the telemetry and control mission is completed, the telemetry and control transponder is turned off to avoid turning on the telemetry and control transponder when there is no telemetry and control mission, thus avoiding increased energy consumption.

[0118] It should be noted that the activation and deactivation of the telemetry and control transponder can also be controlled according to the position of the target satellite relative to the ground station. For example, the telemetry and control transponder can be activated before the target satellite enters the station to perform telemetry and control tasks and to transmit telemetry data. The telemetry and control transponder can be deactivated when the target satellite leaves the station. Here, "entering the station" and "leaving the station" refer to the telemetry and control station's area where it can receive satellite telemetry data.

[0119] II. When the target type is a data transmission mission to Earth, the satellite's on-orbit control device controls the operation of the target satellite based on the low-power operation strategy corresponding to the target type, including:

[0120] When the target type is a data transmission mission to Earth, determine whether the second orbit extrapolation duration of the target satellite at the current moment is less than a second preset threshold.

[0121] When the second orbit extrapolation time is less than the second preset threshold, the flywheel corresponding to the target satellite is activated, and the flywheel is controlled to adjust the attitude of the target satellite so that the attitude of the target satellite is a staring attitude toward the Earth.

[0122] Based on the adjusted attitude of the target satellite, transmit the data corresponding to the first task;

[0123] When the second orbit extrapolation duration exceeds the second preset threshold, the global navigation satellite module corresponding to the target satellite is powered on, and the position and on-board time of the target satellite are updated based on the global navigation satellite module.

[0124] When the position of the target satellite and the onboard time update are detected, the flywheel corresponding to the target satellite is activated, and the flywheel is controlled to adjust the attitude of the target satellite so that the attitude of the target satellite is a staring attitude towards the Earth, and the data corresponding to the first task is transmitted based on the adjusted attitude of the target satellite.

[0125] In this embodiment, when the target type is a data transmission mission to Earth, that is, the first mission is for the target satellite to transmit data to the ground, the satellite's on-orbit control device can also determine whether the second orbit extrapolation time of the target satellite at the current moment is greater than a second preset threshold. If the second orbit extrapolation time is less than the second preset threshold, the flywheel corresponding to the target satellite is activated, and the flywheel is controlled to adjust the attitude of the target satellite so that the target satellite's attitude is "staring at Earth," meaning that the satellite's designated axis always points to the designated target on the ground. The data corresponding to the first mission is then transmitted based on the target satellite after the attitude adjustment.

[0126] If the extrapolation duration of the second orbit exceeds the second preset threshold, it indicates that the target satellite's GNNS has been powered off for a certain period of time. At this point, the GNNS can be powered on to update the satellite's position and onboard time. After the update, the Earth data transmission task can be performed. The steps for the target satellite to perform the Earth data transmission task have been explained in detail above, and will not be repeated here. In addition, attitude refers to the spatial pointing of the target satellite.

[0127] III. When the target type is a remote sensing imaging mission, the satellite's on-orbit control device controls the operation of the target satellite based on the low-power operation strategy corresponding to the target type, including:

[0128] When the target type is a remote sensing imaging mission, the position of the target satellite and its onboard information are updated based on the global navigation satellite module corresponding to the target satellite.

[0129] The attitude of the target satellite is adjusted to the target attitude corresponding to the remote sensing imaging mission based on the star sensor and / or the flywheel corresponding to the target satellite.

[0130] The remote sensing imaging task is performed based on the target attitude.

[0131] In this embodiment, when the first task is a remote sensing imaging task, the GNNS is directly controlled to update the position and on-board time of the target satellite, and the attitude of the target satellite is adjusted to the target attitude corresponding to the remote sensing imaging task through the sensor and / or flywheel, and the remote sensing imaging task is executed based on the target attitude.

[0132] In one embodiment, after the satellite's on-orbit control device controls the target satellite's operation based on a low-power operation strategy, it also performs the following operations:

[0133] Obtain the execution time of the second task, which is the task to be performed after the target satellite has performed the first task;

[0134] When the time interval between the execution time and the current time is less than a third preset threshold, the attitude of the target satellite is adjusted according to the task type of the second task.

[0135] In this embodiment, after completing the first task, the satellite's on-orbit control device can also obtain the execution time of the second task to be executed after the first task, and determine whether the time interval between the execution time and the current time is greater than a second preset threshold (the second preset threshold can be, for example, 15 minutes, but can also be adjusted according to the actual situation, and is not specifically limited). If the time interval is less than the second preset threshold, it means that the execution time of the second task is about to arrive, so there is no need to put the target satellite's task execution equipment into hibernation, and the attitude of the target satellite can be directly adjusted according to the task type of the second task, waiting for the second task to arrive to execute the second task. The above has already described in detail the adjustment of the target satellite's attitude according to the task type, and will not be repeated here.

[0136] When the time interval exceeds the third preset threshold, it indicates that the execution time of the second task is far from being reached. Maintaining the operation of all task execution equipment on the target satellite at this time would result in significant energy consumption. Therefore, the task execution equipment on the target satellite can be shut down to control the target satellite's orbit extrapolation with minimal power consumption. This task execution equipment includes, but is not limited to, GNNS modules, telemetry and command transponders, star sensors, terrestrial sensors, magnetometers, and flywheels.

[0137] It should be noted that when the global navigation satellite module corresponding to the target satellite is powered off, the power-off time of the global navigation satellite module corresponding to the target satellite is accumulated; when the power-off time exceeds a threshold, the global navigation satellite module corresponding to the target satellite is turned on, and the position and on-board time of the target satellite are updated; when the star sensor, terahertz sensor, and magnetometer are powered off, the current attitude of the target satellite is determined by gyro integration and the solar cell matrix corresponding to the target satellite; when the deviation between the current attitude and the target satellite's orbit is greater than a fourth preset threshold, the terahertz sensor and magnetometer are turned on, and the current attitude is adjusted based on the terahertz sensor and the magnetometer; when the flywheel is powered off, the attitude of the target satellite is controlled by the magnetic torque device corresponding to the target satellite.

[0138] In other words, the long-term autonomous operation process of a satellite after it enters orbit is as follows:

[0139] 1. The satellite uses orbit extrapolation to determine the next mission.

[0140] 2. If the next mission duration is longer than X minutes (determined according to mission time adjustment requirements, adjustable in orbit), the satellite will switch to a sun-oriented spin-stabilized attitude.

[0141] 1) Onboard GNSS power off, telemetry and control transponder, and payload power off;

[0142] 2) The satellite computer records the shutdown time and extrapolates the orbit based on the time before GNSS shutdown;

[0143] 3) Only the gyroscope is left in the attitude sensing device, and all other sensors are turned off. The satellite uses the gyroscope in combination with the magnetic field to sense its attitude.

[0144] 4) Use a magnetic torque converter as the attitude control actuator to ensure that the spin angular velocity is below the limit value (this threshold is limited according to the capability of the on-board actuator and is adjustable in orbit), and the satellite attitude is oriented towards the sun;

[0145] 5) When the GNSS (Global Navigation Satellite System) is shut down for more than one day, the GNSS will be activated to update the satellite position and onboard time (this time is jointly limited by the orbit extrapolation accuracy of the satellite computer, the GNSS position accuracy, and the magnetic field calculation accuracy, and is adjustable in orbit).

[0146] In summary, it can be seen that in the embodiments provided by the present invention, when there is a first task to be executed at the current moment, the satellite operation is controlled according to the low-power operation strategy corresponding to the task type of the first task. This avoids the waste of energy caused by turning on all the satellite's equipment when the satellite has a task to perform.

[0147] The embodiments of the present invention have been described above from the perspective of the on-orbit control method of the satellite. The embodiments of the present invention will now be described below from the perspective of the on-orbit control device of the satellite.

[0148] Please see Figure 2 , Figure 2 This is a virtual structural diagram of an on-orbit control device for a satellite provided in an embodiment of the present invention. The on-orbit control device 200 for the satellite includes:

[0149] The judgment module 201 is used to determine whether there is a first task to be executed at the current moment during the autonomous operation of the target satellite;

[0150] The determining module 202 is used to determine the target type corresponding to the first task when the first task exists at the current time;

[0151] The control module 203 is used to control the operation of the target satellite based on the low-power operation strategy corresponding to the target type when the target satellite performs the first task.

[0152] In one possible design, the control module 203 is specifically used for:

[0153] When the target type is a telemetry and control mission type, determine whether the first orbit extrapolation duration of the target satellite at the current moment is greater than a first preset threshold.

[0154] When the extrapolation time of the first orbit is less than the first preset threshold, the telemetry and control transponder corresponding to the target satellite is turned on, and the telemetry and control transponder is turned off when the first task is detected to have been completed.

[0155] When the extrapolation duration of the first orbit exceeds the first preset threshold, the global navigation satellite module corresponding to the target satellite is powered on, and the position and on-board time of the target satellite are updated based on the global navigation satellite module.

[0156] When the position of the target satellite and the onboard time update are detected, the telemetry, tracking, and command transponder is turned on, and when the first task is detected to have been completed, the telemetry, tracking, and command transponder is turned off.

[0157] In one possible design, the control module 203 is further specifically used for:

[0158] When the target type is a data transmission mission to Earth, determine whether the second orbit extrapolation duration of the target satellite at the current moment is less than a second preset threshold.

[0159] When the second orbit extrapolation time is less than the second preset threshold, the flywheel corresponding to the target satellite is activated, and the flywheel is controlled to adjust the attitude of the target satellite so that the attitude of the target satellite is a staring attitude toward the Earth.

[0160] Based on the adjusted attitude of the target satellite, transmit the data corresponding to the first task;

[0161] When the second orbit extrapolation duration exceeds the second preset threshold, the global navigation satellite module corresponding to the target satellite is powered on, and the position and on-board time of the target satellite are updated based on the global navigation satellite module.

[0162] When the position of the target satellite and the onboard time update are detected, the flywheel corresponding to the target satellite is activated, and the flywheel is controlled to adjust the attitude of the target satellite so that the attitude of the target satellite is a staring attitude towards the Earth, and the data corresponding to the first task is transmitted based on the adjusted attitude of the target satellite.

[0163] In one possible design, the control module 203 is further specifically used for:

[0164] When the target type is a remote sensing imaging mission, the position of the target satellite and its onboard information are updated based on the global navigation satellite module corresponding to the target satellite.

[0165] The attitude of the target satellite is adjusted to the target attitude corresponding to the remote sensing imaging mission based on the star sensor and / or the flywheel corresponding to the target satellite.

[0166] The remote sensing imaging task is performed based on the target attitude.

[0167] In one possible design, the control module 203 is further used for:

[0168] Obtain the execution time of the second task, which is the task to be performed after the target satellite has performed the first task;

[0169] When the time interval between the execution time and the current time is less than a third preset threshold, the attitude of the target satellite is adjusted according to the task type of the second task.

[0170] In one possible design, the control module 203 is further used for:

[0171] When the time interval between the execution time and the current time is greater than the third preset threshold, the execution task device corresponding to the target satellite is determined;

[0172] The device performing the task is turned off.

[0173] In one possible design, the control module 203 shuts down the task-performing device by:

[0174] Power off the global navigation satellite module corresponding to the target satellite;

[0175] Control the shutdown of the telemetry, tracking, and command (TT&C) transponder corresponding to the target satellite;

[0176] The star sensor, terameter, and magnetometer corresponding to the target satellite are powered off.

[0177] The flywheel corresponding to the target satellite is shut down.

[0178] In one possible design, the control module 203 is further used for:

[0179] When the global navigation satellite module corresponding to the target satellite is powered off, the power-off time of the global navigation satellite module corresponding to the target satellite is accumulated;

[0180] If the shutdown duration exceeds the threshold, the global navigation satellite module corresponding to the target satellite is activated, and the position and onboard time of the target satellite are updated.

[0181] When the star sensor, the solar sensor, and the magnetometer are powered off, the current attitude of the target satellite is determined by gyroscope integration and the solar cell matrix corresponding to the target satellite.

[0182] When the deviation between the current attitude and the target satellite's orbit is greater than a fourth preset threshold, the solar sensor and the magnetometer are activated, and the current attitude is adjusted based on the solar sensor and the magnetometer.

[0183] When the flywheel is powered off, the attitude of the target satellite is controlled by the magnetic torque device corresponding to the target satellite.

[0184] above Figure 3 The on-orbit control device of the satellite in this embodiment of the invention has been described from the perspective of modular functional entities. The following is a detailed description of the on-orbit control device of the satellite in this embodiment of the invention from the perspective of hardware processing. Please refer to [link / reference needed]. Figure 3 A schematic diagram of an embodiment of the on-orbit control device 300 for a satellite according to the present invention is shown. The on-orbit control device 300 for the satellite includes:

[0185] Input device 301, output device 302, processor 303, and memory 304 (where the number of processors 303 can be one or more). Figure 3 (Taking a processor 303 as an example). In some embodiments of the present invention, the input device 301, the output device 302, the processor 303, and the memory 304 may be connected via a communication bus or other means, wherein... Figure 3 Take the China-Israel communication bus connection as an example.

[0186] Specifically, by calling the operation instructions stored in memory 304, processor 303 executes the following steps:

[0187] During the autonomous operation of the target satellite, it is determined whether there is a first task to be executed at the current moment;

[0188] When the first task exists at the current moment, determine the target type corresponding to the first task;

[0189] When the target satellite performs the first task, the operation of the target satellite is controlled based on the low-power operation strategy corresponding to the target type.

[0190] By calling the operation instructions stored in memory 304, processor 303 is also used to execute... Figure 1 Any of the methods in the corresponding embodiments.

[0191] Please see Figure 4 , Figure 4A schematic diagram of an embodiment of the electronic device provided in this invention.

[0192] like Figure 4 As shown, this embodiment of the invention provides an electronic device, including a memory 410, a processor 420, and a computer program 411 stored in the memory 410 and executable on the processor 420. When the processor 420 executes the computer program 411, it performs the following steps:

[0193] During the autonomous operation of the target satellite, it is determined whether there is a first task to be executed at the current moment;

[0194] When the first task exists at the current moment, determine the target type corresponding to the first task;

[0195] When the target satellite performs the first task, the operation of the target satellite is controlled based on the low-power operation strategy corresponding to the target type.

[0196] In practical implementation, when the processor 420 executes the computer program 411, it can achieve... Figure 1 Any of the corresponding implementation methods in the embodiments.

[0197] Since the electronic device described in this embodiment is the device used to implement an on-orbit control device for a satellite in this embodiment of the invention, those skilled in the art can understand the specific implementation method and various variations of the electronic device in this embodiment based on the method described in this embodiment of the invention. Therefore, how the electronic device implements the method in this embodiment of the invention will not be described in detail here. Any device used by those skilled in the art to implement the method in this embodiment of the invention is within the scope of protection of this invention.

[0198] Please see Figure 5 , Figure 5 This is a schematic diagram of an embodiment of a computer-readable storage medium provided in this invention.

[0199] like Figure 5 As shown, this embodiment of the invention also provides a computer-readable storage medium 500, on which a computer program 511 is stored. When the computer program 511 is executed by a processor, it performs the following steps:

[0200] During the autonomous operation of the target satellite, it is determined whether there is a first task to be executed at the current moment;

[0201] When the first task exists at the current moment, determine the target type corresponding to the first task;

[0202] When the target satellite performs the first task, the operation of the target satellite is controlled based on the low-power operation strategy corresponding to the target type.

[0203] In the specific implementation process, the computer program 511 is executed by the processor to achieve... Figure 1 Any of the corresponding implementation methods in the embodiments.

[0204] It should be noted that the descriptions of each embodiment in the above embodiments have different focuses. For parts that are not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0205] Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention can take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0206] This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded computer, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0207] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0208] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0209] This invention also provides a computer program product comprising computer software instructions that, when executed on a processing device, cause the processing device to perform actions such as... Figure 1 The process in the corresponding embodiment.

[0210] The computer program product includes one or more computer instructions. When the computer program instructions are loaded and executed on a computer, all or part of the processes or functions described in the embodiments of the present invention are generated. The computer may be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer instructions may be stored in a computer-readable storage medium or transmitted from one computer-readable storage medium to another. For example, the computer instructions may be transmitted from one website, computer, server, or data center to another website, computer, server, or data center via wired (e.g., coaxial cable, fiber optic, digital subscriber line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) means. The computer-readable storage medium may be any available medium that a computer can store or a data storage device such as a server or data center that integrates one or more available media. The available medium may be a magnetic medium (e.g., floppy disk, hard disk, magnetic tape), an optical medium (e.g., DVD), or a semiconductor medium (e.g., solid-state disk (SSD)).

[0211] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working processes of the systems, devices, and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0212] In the embodiments provided by this invention, it should be understood that the disclosed systems, apparatuses, and methods can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be an indirect coupling or communication connection between devices or units through some interfaces, and may be electrical, mechanical, or other forms.

[0213] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0214] Furthermore, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0215] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0216] The above-described embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method of on-orbit control of a satellite, characterized by, The method applied to a target satellite comprises: judging whether there is a first task to be executed at a current time during autonomous operation of the target satellite; when the first task exists at the current time, determining a target type corresponding to the first task; when the target satellite executes the first task, controlling the target satellite to operate based on a low-power consumption operation strategy corresponding to the target type; the controlling the target satellite to operate based on the low-power consumption operation strategy corresponding to the target type comprises: when the target type is a measurement and control task type, judging whether a first orbit extrapolation duration of the target satellite at the current time is greater than a first preset threshold; when the first orbit extrapolation duration is less than the first preset threshold, starting a measurement and control transponder corresponding to the target satellite, and when it is monitored that the first task is executed, stopping the measurement and control transponder; when the first orbit extrapolation duration is greater than the first preset threshold, starting a global navigation satellite module corresponding to the target satellite, and updating a position and an on-board time of the target satellite based on the global navigation satellite module; when it is detected that the position and the on-board time of the target satellite are updated, starting the measurement and control transponder, and when it is monitored that the first task is executed, stopping the measurement and control transponder.

2. The method of claim 1, wherein, the controlling the target satellite to operate based on the low-power consumption operation strategy corresponding to the target type comprises: when the target type is a data transmission to earth task type, judging whether a second orbit extrapolation duration of the target satellite at the current time is less than a second preset threshold; when the second orbit extrapolation duration is less than the second preset threshold, starting a flywheel corresponding to the target satellite, and controlling the flywheel to adjust an attitude of the target satellite so that the attitude of the target satellite is earth staring; transmitting data corresponding to the first task based on the adjusted attitude of the target satellite; when the second orbit extrapolation duration is greater than the second preset threshold, starting a global navigation satellite module corresponding to the target satellite, and updating the position and the on-board time of the target satellite based on the global navigation satellite module; when it is detected that the position and the on-board time of the target satellite are updated, starting the flywheel corresponding to the target satellite, and controlling the flywheel to adjust the attitude of the target satellite so that the attitude of the target satellite is earth staring, and transmitting the data corresponding to the first task based on the adjusted attitude of the target satellite.

3. The method of claim 1, wherein, the controlling the target satellite to operate based on the low-power consumption operation strategy corresponding to the target type comprises: when the target type is a remote sensing imaging task type, updating the position and the on-board time of the target satellite based on a global navigation satellite module corresponding to the target satellite; adjusting the attitude of the target satellite to a target attitude corresponding to the remote sensing imaging task based on a star sensor corresponding to the target satellite and / or the flywheel corresponding to the target satellite; executing the remote sensing imaging task based on the target attitude.

4. The method according to any one of claims 1 to 3, characterized in that, after the controlling the target satellite to operate based on the low-power consumption operation strategy, the method further comprises: acquire an execution time of a second task, the second task being a task executed after the target satellite executes the first task; when a time interval between the execution time and a current time is less than a third preset threshold, adjust an attitude of the target satellite according to a task type of the second task.

5. The method of claim 4, wherein, The method further comprises; when the time interval between the execution time and the current time is greater than the third preset threshold, determine an execution task device corresponding to the target satellite; turn off the execution task device.

6. The method of claim 5, wherein, The turning off of the execution task device comprises: control a global navigation satellite module corresponding to the target satellite to shut down; control a TT&C (Telemetry, Tracking and Command) responder corresponding to the target satellite to shut down; control a star sensor, a sun sensor and a magnetometer corresponding to the target satellite to shut down; control a flywheel corresponding to the target satellite to shut down.

7. The method of claim 6, wherein, The method further comprises: when the global navigation satellite module corresponding to the target satellite is shut down, accumulate a shutdown duration of the global navigation satellite module; when the shutdown duration exceeds a threshold value, turn on the global navigation satellite module corresponding to the target satellite, and update a position and an on-board time of the target satellite; when the star sensor, the sun sensor and the magnetometer are shut down, determine a current attitude of the target satellite by gyro integration and a solar cell array corresponding to the target satellite; when a deviation between the current attitude and an orbit of the target satellite is greater than a fourth preset threshold, control the sun sensor and the magnetometer to be turned on, and adjust the current attitude based on the sun sensor and the magnetometer; when the flywheel is shut down, control an attitude of the target satellite by a magnetic moment device corresponding to the target satellite.

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