CN112810840B - On-orbit operation method and device for satellite combining response activation and standby latency - Google Patents

Abstract

The present application relates to a satellite on-orbit operation method, device, computer equipment and storage medium combined with response activation and standby latency. The method includes: defining a minimum system by arranging a multi-faceted solar cell array on the structural surface of the satellite, entering a latent mode when no task is performed, and in the latent mode, the attitude of the satellite enters an uncontrolled slow rotation state, and the multi-faceted solar cells At least one surface of the array is exposed to sunlight, providing energy input for the normal operation of the minimum system. In the latent mode, the attitude measurement and control system does not need to be turned on for a long time, which reduces the influence of space irradiation on electronic components and the wear of the momentum wheel bearing caused by high-speed rotation, which can greatly improve the working life of attitude measurement and control equipment; The possibility of insufficient satellite energy caused by the instability of the satellite attitude caused by the failure of the attitude control software is reduced. The satellite operation method proposed by the invention can improve the utilization efficiency of satellite energy and the reliability of satellite operation.

Description

Method and device for satellite on-orbit operation combined with response activation and standby latency

technical field

The present application relates to the technical field of satellite on-orbit operation, and in particular to a satellite on-orbit operation method, device, computer equipment and storage medium that combine response activation and standby latency.

Background technique

The satellite is divided into two parts: the platform and the payload. The platform also includes the on-board computer, power supply, satellite-ground measurement and control, attitude measurement and control, payload and data transmission. In the design of satellite on-orbit operation mode, it is necessary to design the power-on state of the device and the satellite attitude pointing state in different mission modes according to the needs of the mission.

In the prior art, when the satellite is running in orbit, the attitude of the satellite is maintained at a specific orientation, so as to meet the energy acquisition needs of the solar battery array of the satellite. The defects are: first, the attitude measurement and control subsystem of the satellite is turned on at any time, and attitude measurement and control equipment such as momentum wheels, star sensors, and gyroscopes need to consume electricity, which increases the burden of satellite energy; second, momentum wheels, star sensors, etc. The long-term power-on of attitude measurement and control equipment such as sensors and gyroscopes will have a certain impact on the working life; in addition, the energy system is designed to maintain the installation attitude for a long time. Once the satellite attitude control has an abnormality such as rollover, the satellite energy balance will soon be broken. , the satellite cannot continue to work properly.

Therefore, the prior art has the problems of large power consumption of the device and weak reliability.

SUMMARY OF THE INVENTION

Based on this, it is necessary to provide a satellite on-orbit operation method, device, computer equipment and storage medium that can reduce the energy consumption of satellite equipment and improve the reliability of satellite operation by combining response activation and standby latency.

A satellite on-orbit operation method combining response activation and standby latency, the method comprising:

When the satellite's on-orbit execution task is completed, a latent operation switching instruction is received; the structure surface of the satellite is provided with a multi-faceted solar cell array;

According to the latent operation switching instruction and the pre-stored minimum system equipment list, devices other than the minimum system equipment list in the satellite system are turned off, so that the satellite operates in the latent mode; wherein, in the latent mode The attitude of the lower satellite enters an uncontrolled state, and in the uncontrolled state, at least one surface of the multi-faceted solar cell array is exposed to sunlight.

In one of the embodiments, the method further includes: according to the latent operation switching instruction and the pre-stored minimum system equipment list, shutting down the equipments in the satellite system that are not in the minimum system equipment list, so that the satellite operates in the minimum system equipment list. The latent mode; the equipment in the minimum system equipment list includes: on-board computer, power supply controller, and satellite-to-ground measurement and control stand-alone.

In one of the embodiments, the method further includes: according to the latent operation switching instruction and the pre-stored minimum system equipment list, shutting down the equipments in the satellite system that are not in the minimum system equipment list, so that the satellite operates in the minimum system equipment list. The latent mode; wherein, in the latent mode, the attitude of the satellite enters an uncontrolled state, and the satellite rotates freely in space according to a certain angular velocity.

In one of the embodiments, the method further includes: according to the latent operation switching instruction and the pre-stored minimum system equipment list, shutting down the equipments in the satellite system that are not in the minimum system equipment list, so that the satellite operates in the minimum system equipment list. A latent mode; wherein, in the latent mode, the satellite attitude enters an uncontrolled state, and in the uncontrolled state, at least one surface of the multi-faceted solar cell array is exposed to the sun, and the multi-faceted solar cell array is the minimum system. Provides energy input.

In one of the embodiments, the method further includes: after the satellite operates in a latent mode, a task execution switching instruction is received;

According to the task execution switching instruction, devices other than the minimum system device list in the satellite system are turned on, so that the satellite operates in a task execution mode; wherein, in the task execution mode, the satellite attitude maneuvers to The orientation required by the task.

In one of the embodiments, the method further includes: according to the task execution switching instruction, turning on devices in the satellite system that are not in the minimum system device list, so that the satellite operates in a task execution mode; the minimum system Equipment outside the equipment list includes: momentum wheels, star sensors, gyroscopes, solar sensors, magnetometers, imaging payload subsystems, and data transmission subsystems.

In one embodiment, the method further includes: executing a switching instruction according to the task, and turning on the attitude measurement and control equipment, the imaging payload subsystem and the data transmission subsystem in the satellite system, so that the satellite passes the attitude measurement Establish the satellite's attitude towards the ground with the control device, point to the azimuth that needs to be imaged, complete the imaging task of the target area through the imaging payload subsystem, and send the imaging data back to the ground through the data transmission subsystem.

A satellite on-orbit operation device combined with response activation and standby latency, the device comprises:

The latent instruction receiving module is used for receiving the latent operation switching instruction when the satellite on-orbit execution task ends; the structure surface of the satellite is provided with a multi-faceted solar cell array;

a latent operation module, configured to turn off the devices in the satellite system other than the minimum system equipment list according to the latent operation switching instruction and the pre-stored minimum system equipment list, so that the satellite operates in the latent mode; wherein , in the latent mode, the satellite attitude enters an uncontrolled state, and in the uncontrolled state, at least one surface of the multi-faceted solar cell array is exposed to sunlight.

A computer device includes a memory and a processor, the memory stores a computer program, and the processor implements the following steps when executing the computer program:

When the satellite's on-orbit execution task is completed, a latent operation switching instruction is received; the structure surface of the satellite is provided with a multi-faceted solar cell array;

According to the latent operation switching instruction and the pre-stored minimum system equipment list, devices other than the minimum system equipment list in the satellite system are turned off, so that the satellite operates in the latent mode; wherein, in the latent mode The attitude of the lower satellite enters an uncontrolled state, and in the uncontrolled state, at least one surface of the multi-faceted solar cell array is exposed to sunlight.

A computer-readable storage medium on which a computer program is stored, and when the computer program is executed by a processor, the following steps are implemented:

When the satellite's on-orbit execution task is completed, a latent operation switching instruction is received; the structure surface of the satellite is provided with a multi-faceted solar cell array;

According to the latent operation switching instruction and the pre-stored minimum system equipment list, devices other than the minimum system equipment list in the satellite system are turned off, so that the satellite operates in the latent mode; wherein, in the latent mode The attitude of the lower satellite enters an uncontrolled state, and in the uncontrolled state, at least one surface of the multi-faceted solar cell array is exposed to sunlight.

The above-mentioned satellite on-orbit operation method, device, computer equipment and storage medium combined with response activation and standby lurking, define a minimum system by setting a multi-faceted solar cell array on the structural surface of the satellite, and enter the lurking mode when the satellite has no task execution. In the latent mode, the satellite attitude enters an uncontrolled slow rotation state, and at least one surface of the multi-faceted solar array is exposed to the sun, providing energy input for the normal operation of the minimum system. In the latent mode, there is no need to control the attitude of the satellite, and the attitude measurement and control system used to control the attitude of the satellite does not need to be turned on for a long time, which reduces the impact of space irradiation on electronic components and the wear and tear of the momentum wheel bearing caused by high-speed rotation. It can greatly improve the working life of the attitude measurement and control equipment; at the same time, it also reduces the possibility of insufficient satellite energy caused by the instability of the satellite attitude caused by the failure of the attitude control software. Therefore, the satellite operation method proposed by the present invention improves the utilization efficiency of satellite energy and the reliability of satellite operation.

Description of drawings

1 is a schematic flowchart of a satellite on-orbit operation method combining response activation and standby latency in one embodiment;

2 is a schematic diagram of a satellite multi-faceted solar cell array in one embodiment;

3 is a schematic flowchart of a satellite on-orbit operation method combining response activation and standby latency in another embodiment;

Fig. 4 is a structural block diagram of a satellite on-orbit operation device combined with response activation and standby latency in one embodiment;

FIG. 5 is a diagram of the internal structure of a computer device in one embodiment.

Detailed ways

In order to make the purpose, technical solutions and advantages of the present application more clearly understood, the present application will be described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application, but not to limit the present application.

The satellite on-orbit operation method combining response activation and standby latency provided in this application can be applied to the application environment shown below. in,

In one embodiment, as shown in FIG. 1 , a method for satellite on-orbit operation combining response activation and standby latency is provided, comprising the following steps:

Step 102 , when the satellite in-orbit operation and execution task is completed, a latent operation switching instruction is received; a multi-sided solar cell array is arranged on the structural surface of the satellite.

In the satellite operation method proposed by the invention, when the satellite is not performing tasks, it operates in the lowest power consumption state with the smallest system on standby and latent, and the designed area of the solar cell array is calculated according to the energy demand of the whole satellite and the energy conversion efficiency. Therefore, the solar cell array is reasonably distributed on more than three structural surfaces of the satellite to form a body-mounted solar cell array. As shown in Figure 2, the body-mounted solar cell array with more than three surfaces designed by the present invention can Ensure that at least one surface is exposed to the sun to provide energy input for the normal operation of the satellite in the lowest power consumption state. When the current task is completed, the satellite onboard computer issues an instruction to switch to the latent operation state.

Step 104, according to the latent operation switching instruction and the pre-stored minimum system equipment list, turn off the equipment other than the minimum system equipment list in the satellite system, so that the satellite operates in the latent mode; wherein, in the latent mode, the satellite attitude enters an uncontrolled state , in the uncontrolled state, at least one face of the multi-faceted solar cell array is exposed to sunlight.

The pre-defined minimum system includes the onboard computer, power supply, and satellite-ground measurement and control equipment. In the latent mode, the equipment in the minimum system remains powered on, and other equipment is turned off. Since the attitude measurement and control equipment is not turned on, the attitude of the whole star is in an uncontrolled slow rotation state.

In the above-mentioned satellite on-orbit operation method combining response activation and standby latency, the minimum system is defined by setting a multi-faceted solar cell array on the structural surface of the satellite. The controlled slow spin state, and at least one face of the multi-faceted solar array is exposed to sunlight, provides energy input for the normal operation of the minimum system. In the latent mode, there is no need to control the attitude of the satellite, and the attitude measurement and control system used to control the attitude of the satellite does not need to be turned on for a long time, which reduces the impact of space irradiation on electronic components and the wear and tear of the momentum wheel bearing caused by high-speed rotation. It can greatly improve the working life of the attitude measurement and control equipment; at the same time, it also reduces the possibility of insufficient satellite energy caused by the instability of the satellite attitude caused by the failure of the attitude control software. Therefore, the satellite operation method proposed by the present invention improves the utilization efficiency of satellite energy and the reliability of satellite operation.

In one embodiment, the method further includes: according to the latent operation switching instruction and the pre-stored minimum system equipment list, shutting down the equipment other than the minimum system equipment list in the satellite system, so that the satellite operates in the latent mode; in the minimum system equipment list The equipment includes: on-board computer, power controller, satellite-to-ground measurement and control stand-alone.

The on-board computer is used to process local and uplink commands, the power system is used to supply equipment and reserve power, and the satellite-to-ground measurement and control equipment is used to listen to ground mission commands.

In one of the embodiments, the method further includes: according to the latent operation switching instruction and the pre-stored minimum system equipment list, shutting down the equipment outside the minimum system equipment list in the satellite system, so that the satellite operates in the latent mode; wherein, in the latent mode The attitude of the satellite enters the uncontrolled state, and the satellite rotates freely in space according to a certain angular velocity. In the uncontrolled state, at least one surface of the multi-faceted solar array is exposed to the sun, and the multi-faceted solar array provides energy input for the minimum system.

Since the designed multi-faceted solar array can ensure that no matter what posture the satellite is in, at least one face will be exposed to the sun. Therefore, the satellite rotates freely in space at a certain angular velocity, and the multi-faceted solar array can still provide the smallest system in the latent state. working power.

In one embodiment, the method further includes: after the satellite operates in the latent mode, a task execution switching instruction is received; according to the task execution switching instruction, devices other than the minimum system equipment list in the satellite system are turned on, so that the satellite operates in the task execution mode. mode; wherein, in the mission execution mode, the satellite attitude maneuvers to the azimuth required by the mission.

When the satellite receives the mission command through the minimum system, the onboard computer automatically turns on the attitude measurement and control equipment, the imaging payload subsystem and the data transmission subsystem. Quickly establish the satellite's attitude towards the ground and point to the azimuth that needs to be imaged. The imaging payload completes the imaging task of the target area and realizes the "response activation" driven by the task. Attitude measurement and control equipment includes momentum wheel, star sensor, gyroscope, etc.

In one of the embodiments, the method further includes: according to the task execution switching instruction, turning on devices other than the minimum system device list in the satellite system, so that the satellite operates in the task execution mode; the devices outside the minimum system device list include: a momentum wheel , star sensor, gyroscope, solar sensor, magnetometer, imaging payload subsystem and data transmission subsystem.

Because the attitude measurement and control equipment such as momentum wheel, star sensor, gyroscope and other attitude measurement and control equipment in the satellite attitude measurement and control subsystem are not turned on for a long time, the influence of space irradiation on electronic components is reduced, and the momentum wheel is not turned on for a long time. The wear and tear of the momentum wheel bearing caused by the rotation can greatly improve the working life of the attitude measurement and control equipment; in addition, the present invention can avoid the problem of insufficient satellite energy caused by the instability of the satellite attitude caused by the fault of the attitude control software. It is in an uncontrolled state, the energy consumption is very low, and the solar array can meet the energy demand in a slow attitude. At the same time, the low requirements for attitude control will greatly reduce the satellite's demand for ground monitoring and control resources.

In one of the embodiments, it also includes: executing the switching instruction according to the task, and turning on the attitude measurement and control equipment, the imaging load subsystem and the data transmission subsystem in the satellite system, so that the satellite can establish the satellite-to-ground attitude through the attitude measurement and control equipment. , Point to the azimuth that needs to be imaged, complete the imaging task of the target area through the imaging payload subsystem, and send the imaging data back to the ground through the data transmission subsystem.

It should be understood that although the various steps in the flowchart of FIG. 1 are shown in sequence according to the arrows, these steps are not necessarily executed in the sequence shown by the arrows. Unless explicitly stated herein, the execution of these steps is not strictly limited to the order, and these steps may be performed in other orders. Moreover, at least a part of the steps in FIG. 1 may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily executed and completed at the same time, but may be executed at different times. The execution of these sub-steps or stages The sequence is also not necessarily sequential, but may be performed alternately or alternately with other steps or sub-steps of other steps or at least a portion of a phase.

In a specific embodiment, as shown in FIG. 3 , a method for satellite on-orbit operation combining response activation and standby latency is provided, including: the basic system of the imaging satellite, that is, the minimum system is powered on, and the satellite attitude enters a slow rotation state , the minimum system detects whether the imaging task command is received. If the task command is received, the attitude measurement and control equipment is powered on, the attitude is determined and the attitude is maneuvered to the imaging position, and the imaging payload subsystem and the data transmission subsystem are turned on. The imaging payload of the satellite images the target area in the mission. After the imaging is completed, the attitude measurement and control equipment, imaging payload and data transmission system are shut down, and the satellite enters the slow rotation state again.

In another specific embodiment, the main process of satellite operation in the satellite on-orbit operation mode combined with the combination of task-driven response activation and standby latency is as follows.

1. The on-board computer, power controller, and satellite-ground measurement and control unit in the satellite basic system are powered on, and other stand-alone equipment is shut down;

2. The satellite attitude is in an uncontrolled state, and it rotates freely in space according to a certain angular velocity;

3. The basic satellite system consumes power with 6W power consumption;

4. Each solar cell array of the satellite obtains electrical energy with a power of 20W, the equivalent power generation of the solar cell array is greater than the power consumption of the basic system, and the satellite achieves energy balance;

5. At time T, the satellite receives a mission command to image a location at the sub-satellite point;

6. The satellite onboard computer sends the power-on command for attitude measurement and control equipment such as momentum wheel, star sensor, gyroscope, etc., the satellite attitude is damped, and the satellite angular velocity is controlled to 0;

7. The satellite attitude determination software calculates the attitude of the satellite;

8. The satellite attitude maneuvers from a pitch angle of 60° to a pitch angle of 0°;

9. The satellite onboard computer issues the imaging payload and data transmission start-up command;

10. The satellite imaging payload images the sub-satellite point area, and the satellite attitude control system maintains the attitude conditions required for payload imaging;

11. After the satellite imaging is completed, the satellite onboard computer sends attitude measurement and control equipment such as momentum wheels, star sensors, and gyroscopes, as well as imaging payloads and data transmission shutdown commands;

12. The attitude of the satellite enters an uncontrolled state and rotates freely in space at an angular velocity of 1°/s.

It can be seen that in the satellite on-orbit operation mode based on the combination of task-driven response activation and standby latency, the satellite is usually in an uncontrolled "standby latency" state, saving power costs. Driven by the imaging task, the attitude can be quickly established to achieve "response activation", and the imaging task can be completed by maneuvering the attitude to the required orientation.

In one embodiment, as shown in FIG. 4, a satellite on-orbit operation device combined with responsive activation and standby latency is provided, including: a latency command receiving module 402 and a latency operation module 404, wherein:

The latent instruction receiving module 402 is used for receiving the latent operation switching instruction when the satellite on-orbit execution task ends; the structure surface of the satellite is provided with a multi-faceted solar cell array;

The latent operation module 404 is configured to close the devices other than the minimum system equipment list in the satellite system according to the latent operation switching instruction and the pre-stored minimum system equipment list, so that the satellite operates in the latent mode; wherein, in the latent mode, the attitude of the satellite is In the uncontrolled state, at least one side of the multi-faceted solar cell array is exposed to the sun.

The latent operation module 404 is further configured to receive the task execution switching instruction after the satellite operates in the latent mode; according to the task execution switching instruction, turn on the devices other than the minimum system equipment list in the satellite system, so that the satellite operates in the task execution mode; Among them, in the task execution mode, the satellite attitude maneuvers to the azimuth required by the task.

The latent operation module 404 is also used to execute the switching instruction according to the task, and open the attitude measurement and control equipment, the imaging load subsystem and the data transmission subsystem in the satellite system, so that the satellite can establish the satellite-to-ground attitude and pointing requirements through the attitude measurement and control equipment. The orientation of the imaging, the imaging task of the target area is completed through the imaging payload subsystem, and the imaging data is sent back to the ground through the data transmission subsystem.

For the specific definition of the satellite on-orbit operation device combining response activation and standby latency, please refer to the above definition of the satellite on-orbit operation method combining response activation and standby latency, which will not be repeated here. The various modules in the satellite on-orbit operation device combined with the above-mentioned response activation and standby latency can be implemented in whole or in part by software, hardware and combinations thereof. The above modules can be embedded in or independent of the processor in the computer device in the form of hardware, or stored in the memory in the computer device in the form of software, so that the processor can call and execute the operations corresponding to the above modules.

In one embodiment, a computer device is provided, and the computer device may be a terminal, and its internal structure diagram may be as shown in FIG. 5 . The computer equipment includes a processor, memory, a network interface, a display screen, and an input device connected by a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium, an internal memory. The nonvolatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the execution of the operating system and computer programs in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a method for satellite on-orbit operation combining responsive activation and standby latency is realized. The display screen of the computer equipment may be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer equipment may be a touch layer covered on the display screen, or a button, a trackball or a touchpad set on the shell of the computer equipment , or an external keyboard, trackpad, or mouse.

Those skilled in the art can understand that the structure shown in FIG. 5 is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer equipment to which the solution of the present application is applied. Include more or fewer components than shown in the figures, or combine certain components, or have a different arrangement of components.

In one embodiment, a computer device is provided, including a memory and a processor, where the memory stores a computer program, and the processor implements the steps in the above method embodiments when the processor executes the computer program.

In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored, and when the computer program is executed by a processor, implements the steps in the above method embodiments.

Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be implemented by instructing relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage In the medium, when the computer program is executed, it may include the processes of the above-mentioned method embodiments. Wherein, any reference to memory, storage, database or other medium used in the various embodiments provided in this application may include non-volatile and/or volatile memory. Nonvolatile memory may include read only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous chain Road (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

The technical features of the above embodiments can be combined arbitrarily. In order to make the description simple, all possible combinations of the technical features in the above embodiments are not described. However, as long as there is no contradiction in the combination of these technical features It is considered to be the range described in this specification.

The above-mentioned embodiments only represent several embodiments of the present application, and the descriptions thereof are specific and detailed, but should not be construed as a limitation on the scope of the invention patent. It should be pointed out that for those skilled in the art, without departing from the concept of the present application, several modifications and improvements can be made, which all belong to the protection scope of the present application. Therefore, the scope of protection of the patent of the present application shall be subject to the appended claims.

Claims (10)

1. A method of in-orbit operation of a satellite in response to activation in combination with standby latency, the method comprising:

when the satellite in-orbit operation execution task is finished, a latent operation switching instruction is received; a multi-surface solar cell array is arranged on the structural surface of the satellite;

according to the latent operation switching instruction and a pre-stored minimum system equipment list, closing equipment out of the minimum system equipment list in the satellite system so as to enable the satellite to operate in a latent mode; and the satellite attitude enters an uncontrolled state in the latent mode, and at least one surface of the multi-surface solar cell array is exposed to the sun in the uncontrolled state.

2. The method of claim 1, wherein turning off devices in the satellite system other than the minimum system device list according to the latency switching instruction and a pre-stored minimum system device list to operate the satellite in the latency mode comprises:

according to the latent operation switching instruction and a pre-stored minimum system equipment list, closing equipment out of the minimum system equipment list in the satellite system so as to enable the satellite to operate in a latent mode; the devices in the minimum system device list include: the satellite-borne computer, the power supply controller and the satellite-ground measurement and control single machine.

3. The method according to claim 1, wherein according to the latency switching instruction and a pre-stored minimum system device list, devices out of the minimum system device list in the satellite system are turned off to operate the satellite in a latency mode; wherein the satellite attitude entering an uncontrolled state in the latent mode comprises:

according to the latent operation switching instruction and a prestored minimum system equipment list, closing equipment outside the minimum system equipment list in the satellite system so as to enable the satellite to operate in a latent mode; and the satellite attitude enters an uncontrolled state in the latent mode, and the satellite freely rotates in space at a certain angular velocity.

4. The method according to claim 1, wherein according to the latency switch command and a pre-stored minimum system device list, turning off devices in the satellite system other than the minimum system device list to operate the satellite in a latency mode; wherein, satellite gesture enters into the uncontrolled state under the mode of said latency, there is one at least face of said multiaspect solar array exposed to the sun under said uncontrolled state, include:

according to the latent operation switching instruction and a pre-stored minimum system equipment list, closing equipment out of the minimum system equipment list in the satellite system so as to enable the satellite to operate in a latent mode; and the satellite attitude enters an uncontrolled state in the latent mode, at least one surface of the multi-surface solar cell array is exposed to the sun in the uncontrolled state, and energy input is provided for the minimum system through the multi-surface solar cell array.

5. The method of claim 1, wherein the satellite operates after a latent mode, comprising:

receiving a task execution switching instruction;

according to the task execution switching instruction, opening equipment out of the minimum system equipment list in the satellite system so as to enable the satellite to operate in a task execution mode; wherein in the task execution mode, the satellite attitude is maneuvered to a task required bearing.

6. The method of claim 5, wherein turning on devices in the satellite system that are outside the minimum system device list in accordance with the task execution switch instruction to cause the satellite to operate in a task execution mode comprises:

according to the task execution switching instruction, opening equipment out of the minimum system equipment list in the satellite system so as to enable the satellite to operate in a task execution mode; the devices outside the minimum system device list include: momentum wheel, star sensor, gyroscope, sun sensor, magnetometer, imaging load subsystem and data transmission subsystem.

7. The method of claim 6, wherein turning on devices in the satellite system that are outside the minimum system device list in accordance with the task execution switch instruction to cause the satellite to operate in a task execution mode comprises:

and according to the task execution switching instruction, opening an attitude measurement and control device, an imaging load subsystem and a data transmission subsystem in the satellite system so as to enable the satellite to establish a satellite ground attitude and point to the azimuth to be imaged through the attitude measurement and control device, completing an imaging task on a target area through the imaging load subsystem, and sending imaging data back to the ground through the data transmission subsystem.

8. An in-orbit satellite operation device in response to activation in combination with standby latency, the device comprising:

the latency instruction receiving module is used for receiving a latency operation switching instruction when the satellite in-orbit operation execution task is finished; a multi-surface solar cell array is arranged on the structural surface of the satellite;

a latent operation module, configured to close devices in the satellite system that are not in the minimum system device list according to the latent operation switching instruction and a pre-stored minimum system device list, so that the satellite operates in a latent mode; and the satellite attitude enters an uncontrolled state in the latent mode, and at least one surface of the multi-surface solar cell array is exposed to the sun in the uncontrolled state.

9. A computer device comprising a memory and a processor, the memory storing a computer program, wherein the processor implements the steps of the method of any one of claims 1 to 7 when executing the computer program.

10. A computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the steps of the method of any one of claims 1 to 7.

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