CN112810840A - On-orbit operation method and device for satellite combining response activation and standby latency - Google Patents
On-orbit operation method and device for satellite combining response activation and standby latency Download PDFInfo
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Abstract
The present application relates to a method, apparatus, computer device and storage medium for in-orbit operation of a satellite in response to activation in combination with standby latency. The method comprises the following steps: the multi-face solar cell array is arranged on the structural surface of the satellite, a minimum system is defined, the multi-face solar cell array enters a latent mode when no task is executed, the satellite posture enters an uncontrolled slow rotation state in the latent mode, and at least one face of the multi-face solar cell array is exposed to the sun, so that energy input is provided for normal work of the minimum system. In the latent mode, the attitude measurement and control system does not need to be started up for a long time, so that the influence of space irradiation on electronic components and abrasion on a momentum wheel bearing caused by high-speed rotation is reduced, and the service life of the attitude measurement and control device can be greatly prolonged; meanwhile, the possibility of the situation of insufficient energy of the satellite caused by instability of the satellite attitude due to the fault of the attitude control software is reduced. The satellite operation method provided by the invention can improve the satellite energy utilization efficiency and the satellite operation reliability.
Description
Technical Field
The present invention relates to the field of satellite in-orbit operation technologies, and in particular, to a method, an apparatus, a computer device, and a storage medium for satellite in-orbit operation that combines response activation and standby latency.
Background
The satellite is divided into a platform and a load, and the platform comprises a satellite-borne computer, a power supply, a satellite-ground measurement and control system, an attitude measurement and control system, a load and data transmission system and the like. In the design of the in-orbit operation mode of the satellite, the starting state and the satellite attitude pointing state of the equipment in different task modes are required to be designed according to the task requirements.
In the prior art, when a satellite runs in orbit, the attitude of the satellite is kept at a specific position so as to meet the energy acquisition requirement of a satellite solar cell array. The defects are as follows: firstly, the satellite turns on an attitude measurement and control subsystem at any time, and attitude measurement and control equipment such as a momentum wheel, a star sensor, a gyroscope and the like needs to consume electric energy, so that the load of satellite energy is increased; secondly, the attitude measurement and control equipment such as the momentum wheel, the star sensor, the gyroscope and the like is electrified for a long time, and certain influence is caused on the service life; in addition, the installation attitude of the energy system is designed in a state of being kept for a long time, once the satellite attitude control is abnormal such as rolling, the energy balance of the satellite is broken quickly, and the satellite cannot work normally.
Therefore, the prior art has the problems of large power consumption and poor reliability of equipment.
Disclosure of Invention
In view of the above, there is a need to provide an in-orbit operation method, an apparatus, a computer device and a storage medium for a satellite, which can reduce the energy consumption of the satellite device and improve the operational reliability of the satellite by combining the response activation and the standby latency.
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.
In one embodiment, the method further comprises the following steps: 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.
In one embodiment, the method further comprises the following steps: 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 the satellite freely rotates in space at a certain angular velocity.
In one embodiment, the method further comprises the following steps: 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.
In one embodiment, the method further comprises the following steps: after the satellite operates in a latent mode, 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.
In one embodiment, the method further comprises the following steps: 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.
In one embodiment, the method further comprises the following steps: 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.
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.
A computer device comprising a memory and a processor, the memory storing a computer program, the processor implementing the following steps when executing the computer program:
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.
A computer-readable storage medium, on which a computer program is stored which, when executed by a processor, carries out the steps of:
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.
According to the satellite on-orbit operation method, device, computer equipment and storage medium combining response activation and standby latency, the minimum system is defined by arranging the multi-face solar cell array on the structural surface of the satellite, when the satellite does not have a task, the satellite enters the latency mode, the satellite posture enters the uncontrolled slow rotation state in the latency mode, and at least one face of the multi-face solar cell array is exposed to the sun, so that energy input is provided for normal operation of the minimum system. In the latent mode, the attitude of the satellite does not need to be controlled, and the attitude measurement and control system for controlling the attitude of the satellite does not need to be started for a long time, so that the influence of space irradiation on electronic components and the abrasion of high-speed rotation on a momentum wheel bearing are reduced, and the service life of the attitude measurement and control equipment can be greatly prolonged; meanwhile, the possibility of the problem of insufficient energy of the satellite caused by instability of the satellite attitude due to the fault of the attitude control software is reduced. Therefore, the satellite operation method provided by the invention improves the satellite energy utilization efficiency and the satellite operation reliability.
Drawings
FIG. 1 is a flow diagram illustrating a method for responding to an activation of an in-orbit operation of a satellite in combination with a standby latency in one embodiment;
FIG. 2 is a schematic diagram of a satellite multi-faceted solar cell array in one embodiment;
FIG. 3 is a flow chart illustrating a method for responding to an activation of an in-orbit operation of a satellite in combination with a standby latency in another embodiment;
FIG. 4 is a block diagram of an embodiment of an in-orbit satellite operation device coupled with standby latency in response to activation;
FIG. 5 is a diagram illustrating an internal structure of a computer device according to an embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
The method for responding to the activation and combining the standby latency of the satellite in-orbit operation provided by the application can be applied to the application environment as shown below. Wherein the content of the first and second substances,
in one embodiment, as shown in fig. 1, there is provided a method of in-orbit operation of a satellite in response to activation in combination with standby latency, comprising the steps of:
102, receiving a latent operation switching instruction when the satellite in-orbit operation execution task is finished; the structural surface of the satellite is provided with a multi-surface solar cell array.
According to the satellite operation method provided by the invention, when the satellite does not execute a task, the satellite operates in the lowest power consumption state by using the standby latent minimum system, the area of the designed solar cell array is calculated according to the energy requirement and the energy conversion efficiency of the whole satellite, the solar cell array is reasonably distributed on the surfaces of more than three structures of the satellite to form the assembled solar cell array, and as shown in figure 2, the assembled solar cell array with more than three surfaces designed by the invention can ensure that at least one surface is exposed to the sun, and provides energy input for the normal operation of the satellite in the lowest power consumption state. And when the current task is finished, the satellite onboard computer sends an instruction for switching to a latent operation state.
The predefined minimum system comprises an on-board computer, a power supply and a satellite-ground measurement and control device, and in the latent mode, the device in the minimum system is kept in a power-on state, and other devices are in a power-off state. The whole star attitude is in an uncontrolled slow rotation state because the attitude measurement and control equipment is not started.
In the satellite in-orbit operation method combining response activation and standby latency, the minimum system is defined by arranging the multi-face solar cell array on the structural surface of the satellite, the satellite enters a latency mode when the satellite does not have a task, the satellite posture enters an uncontrolled slow rotation state in the latency mode, and at least one face of the multi-face solar cell array is exposed to the sun, so that energy input is provided for normal work of the minimum system. In the latent mode, the attitude of the satellite does not need to be controlled, and the attitude measurement and control system for controlling the attitude of the satellite does not need to be started for a long time, so that the influence of space irradiation on electronic components and the abrasion of high-speed rotation on a momentum wheel bearing are reduced, and the service life of the attitude measurement and control equipment can be greatly prolonged; meanwhile, the possibility of the problem of insufficient energy of the satellite caused by instability of the satellite attitude due to the fault of the attitude control software is reduced. Therefore, the satellite operation method provided by the invention improves the satellite energy utilization efficiency and the satellite operation reliability.
In one embodiment, the method further comprises the following steps: 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; 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.
The satellite-borne computer is used for processing local and uplink instructions, the power supply system is used for supplying power to equipment and storing electric energy, and the satellite-ground measurement and control equipment is used for intercepting ground task instructions.
In one embodiment, the method further comprises the following steps: 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; the satellite attitude enters an uncontrolled state in a latent mode, the satellite freely rotates in space at a certain angular speed, 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 a minimum system through the multi-surface solar cell array.
Because the designed multi-face solar cell array can ensure that at least one face is exposed no matter what posture the satellite is in, the satellite freely rotates in space at a certain angular speed, and the multi-face solar cell array can still provide working electric energy for the minimum system in a latent state.
In one embodiment, the method further comprises the following steps: after the satellite operates in a latent mode, receiving a task execution switching instruction; according to the task execution switching instruction, opening equipment out of a 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 manoeuvred to a task required bearing.
When the satellite receives a task instruction through the minimum system, the on-board computer automatically opens the attitude measurement and control equipment, the imaging load subsystem and the data transmission subsystem. The satellite ground attitude is quickly established, the satellite points to the position to be imaged, the imaging load completes the imaging task of the target area, and response activation under task driving is realized. The attitude measurement and control equipment comprises a momentum wheel, a star sensor, a gyroscope and the like.
In one embodiment, the method further comprises the following steps: according to the task execution switching instruction, opening equipment out of a minimum system equipment list in the satellite system so as to enable the satellite to operate in a task execution mode; devices outside the minimum system device list include: momentum wheel, star sensor, gyroscope, sun sensor, magnetometer, imaging load subsystem and data transmission subsystem.
Because attitude measurement and control equipment such as the momentum wheel, the star sensor, the gyroscope and the like in the satellite attitude measurement and control subsystem are not started for a long time, the influence of space irradiation on electronic components is reduced, the abrasion of a momentum wheel bearing caused by high-speed rotation is reduced due to the fact that the momentum wheel is not started for a long time, and the service life of the attitude measurement and control equipment can be greatly prolonged; in addition, the invention can avoid the problem of insufficient energy of the satellite caused by instability of the attitude of the satellite due to faults of attitude control software and the like, the satellite is in an uncontrolled state at ordinary times, the energy expenditure is very low, and the solar cell array can meet the energy requirement under slow rotation of the attitude. Meanwhile, the requirement of the satellite on ground measurement and control resources can be greatly reduced for the low requirement of attitude control.
In one embodiment, the method further comprises the following steps: according to the task execution switching instruction, an attitude measurement and control device, an imaging load subsystem and a data transmission subsystem in the satellite system are opened, so that the satellite establishes a satellite ground attitude and points to a position to be imaged through the attitude measurement and control device, an imaging task of a target area is completed through the imaging load subsystem, and imaging data are sent back to the ground through the data transmission subsystem.
It should be understood that, although the steps in the flowchart of fig. 1 are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and described, and may be performed in other orders, unless explicitly stated otherwise. Moreover, at least a portion of the steps in fig. 1 may include multiple sub-steps or multiple stages that are not necessarily performed at the same time, but may be performed at different times, and the order of performance of the sub-steps or stages is not necessarily sequential, but may be performed in turn or alternately with other steps or at least a portion of the sub-steps or stages of other steps.
In one embodiment, as shown in fig. 3, there is provided a method for in-orbit operation of a satellite in response to activation in combination with standby latency, comprising: the imaging satellite comprises a basic system, a minimum system, an imaging load subsystem and a data transmission subsystem, wherein the basic system of the imaging satellite is powered on, the attitude of the satellite enters a slow rotation state, the minimum system detects whether an imaging task instruction is received, if the task instruction is received, attitude measurement and control equipment is powered on, the attitude is determined and maneuvered to an imaging position, the imaging load subsystem and the data transmission subsystem are started, a target area in a task is imaged through the imaging load of the imaging satellite, after imaging is completed, the attitude measurement and control equipment, the imaging load and the data transmission subsystem are shut down, and the satellite enters the slow rotation state again.
In another embodiment, the task-driven response-based activation of the satellite in-orbit operation mode combined with the standby latency is mainly performed as follows.
1. The satellite-borne computer, the power supply controller and the satellite-ground measurement and control stand-alone machine in the satellite basic system are powered on, and other stand-alone machine equipment is powered off;
2. the satellite attitude is in an uncontrolled state and freely rotates in space according to a certain angular speed;
3. the satellite basic system consumes electric energy with 6W power consumption;
4. each solar cell array of the satellite obtains electric energy with 20W power, the equivalent generating power of the solar cell array is larger than the electric energy consumption of a basic system, and the satellite realizes energy balance;
5. at the time T, the satellite receives a task instruction for imaging a certain place of the subsatellite point;
6. the satellite on-board computer sends out a command for electrifying attitude measurement and control equipment such as a momentum wheel, a star sensor, a gyroscope and the like, the satellite attitude is subjected to damping control, and the satellite angular velocity is controlled to be 0;
7. satellite attitude determination software calculates the attitude of the satellite;
8. maneuvering the satellite attitude from a pitch angle of 60 degrees to an attitude of 0 degree;
9. the satellite-borne computer sends out imaging load and a transmitter instruction;
10. imaging the sub-satellite point region by the satellite imaging load, and keeping the attitude condition required by load imaging by the satellite attitude control system;
11. after the satellite imaging is finished, the satellite spaceborne computer sends attitude measurement and control equipment such as a momentum wheel, a star sensor, a gyroscope and the like, an imaging load and a data transmission shutdown instruction;
12. the satellite attitude enters an uncontrolled state and freely rotates in space at an angular velocity of 1 DEG/s.
Therefore, under the in-orbit operation mode of the satellite based on the task-driven response activation and standby latency combination, the satellite is in a state of uncontrolled attitude and standby latency at ordinary times, and the electric energy cost is saved. Under the driving of the imaging task, the gesture can be quickly established to realize response activation, and the imaging task is completed by maneuvering the gesture to the required position.
In one embodiment, as shown in fig. 4, there is provided an in-orbit satellite operation device combined with standby latency in response to activation, comprising: a latency instruction receiving module 402 and a latency running module 404, wherein:
a latent instruction receiving module 402, configured to receive a latent operation switching instruction when the in-orbit operation execution task of the satellite is finished; a multi-surface solar cell array is arranged on the structural surface of the satellite;
a latent operation module 404, configured to close devices outside the minimum system device list in the satellite system according to the latent operation switching instruction and a prestored minimum system device list, so that the satellite operates in a latent mode; 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.
The latent operation module 404 is further configured to receive a task execution switching instruction after the satellite operates in the latent mode; according to the task execution switching instruction, opening equipment out of a 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 manoeuvred to a task required bearing.
The latent operation module 404 is further configured to execute a switching instruction according to the task, open an attitude measurement and control device, an imaging load subsystem, and a data transmission subsystem in the satellite system, so that the satellite establishes a satellite ground attitude and points to a position to be imaged through the attitude measurement and control device, complete an imaging task for the target area through the imaging load subsystem, and send imaging data back to the ground through the data transmission subsystem.
For specific limitations of the satellite in-orbit operation device combined with the standby latency in response to activation, reference may be made to the above limitations of the satellite in-orbit operation method combined with the standby latency in response to activation, and details thereof are not repeated herein. The above-mentioned responding to the activation of the various modules in the satellite in-orbit operation device combined with the standby latency can be realized in whole or in part by software, hardware and a combination thereof. The modules can be embedded in a hardware form or independent from a processor in the computer device, and can also be stored in a memory in the computer device in a software form, so that the processor can call and execute operations corresponding to the modules.
In one embodiment, a computer device is provided, which may be a terminal, and its internal structure diagram may be as shown in fig. 5. The computer device includes a processor, a memory, a network interface, a display screen, and an input device connected by a system bus. Wherein the processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device comprises a nonvolatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of an operating system and computer programs in the non-volatile storage medium. The network interface of the computer device is used for communicating with an external terminal through a network connection. The computer program is executed by a processor to implement a method of in-orbit operation of a satellite in response to activation in combination with standby latency. The display screen of the computer equipment can be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer equipment can be a touch layer covered on the display screen, a key, a track ball or a touch pad arranged on the shell of the computer equipment, an external keyboard, a touch pad or a mouse and the like.
Those skilled in the art will appreciate that the architecture shown in fig. 5 is merely a block diagram of some of the structures associated with the disclosed aspects and is not intended to limit the computing devices to which the disclosed aspects apply, as particular computing devices may include more or less components than those shown, or may combine certain components, or have a different arrangement of components.
In an embodiment, a computer device is provided, comprising a memory storing a computer program and a processor implementing the steps of the above method embodiments when executing the computer program.
In an embodiment, a computer-readable storage medium is provided, on which a computer program is stored, which computer program, when being executed by a processor, carries out the steps of the above-mentioned method embodiments.
It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by hardware instructions of a computer program, which can be stored in a non-volatile computer-readable storage medium, and when executed, can include the processes of the embodiments of the methods described above. Any reference to memory, storage, database, or other medium used in the embodiments provided herein may include non-volatile and/or volatile memory, among others. Non-volatile memory can include read-only memory (ROM), Programmable ROM (PROM), Electrically Programmable ROM (EPROM), Electrically Erasable Programmable ROM (EEPROM), or flash memory. Volatile memory can include Random Access Memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms such as Static RAM (SRAM), Dynamic RAM (DRAM), Synchronous DRAM (SDRAM), Double Data Rate SDRAM (DDRSDRAM), Enhanced SDRAM (ESDRAM), Synchronous Link DRAM (SLDRAM), Rambus Direct RAM (RDRAM), direct bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).
The technical features of the above embodiments can be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the above embodiments are not described, but should be considered as the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent 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 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 the satellite freely rotates in space at a certain angular velocity.
4. 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, 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 combination with standby latency in response to activation, 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.
Priority Applications (1)
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