Satellite separation control method and device, computer device and storage medium

Abstract

This application relates to a method, apparatus, computer device, and storage medium for the separation control of a flexible satellite. The method includes: acquiring a state signal of the flexible satellite surface; determining the current state of the flexible satellite based on the state signal; wherein the current state includes a mounted state and a separated state; when the flexible satellite is in the separated state, generating a start control command; and controlling the flexible satellite to enter an operational state based on the start control command. This application enables automatic control of the flexible satellite's activation subsystem and its auxiliary devices after separation, enhancing the reliability of the control process.

Description

Technical Field

[0001] This application relates to the field of satellite control technology, and in particular to a method, apparatus, computer equipment, and storage medium for the separation and control of a flexible satellite. Background Technology

[0002] Today's small, multi-functional satellites enable nations, businesses, and even universities to utilize space. In other words, small satellites are transforming the traditional space industry. Particularly in the economic sphere, next-generation space technologies, exemplified by microsatellite technology, are driving the development of commercial spaceflight, leading to wider applications of space technology and improved global connectivity.

[0003] Spacecraft development has become increasingly diverse with technological advancements, including solar sails, thin-film solar panels, and communication satellites. These structures are fundamentally reliant on flexible, deployable structures. Among these, flexible satellite technology is the most novel. In space, a microsatellite can carry multiple compressible flexible satellites, which separate upon reaching a predetermined orbit. Currently, however, flexible satellites cannot automatically enter operational mode after separation from their parent satellite, resulting in poor reliability. Summary of the Invention

[0004] This application provides a method, apparatus, computer equipment, and storage medium for the separation and control of a flexible satellite, so as to at least solve the problem of automatic control of a flexible satellite after separation from its parent satellite in related technologies.

[0005] In a first aspect, embodiments of this application provide a separation control method for a flexible satellite, comprising:

[0006] Acquire state signals from the surface of a flexible satellite;

[0007] The current state of the flexible satellite is determined based on the state signal; wherein, the current state includes the onboard state and the detached state;

[0008] When the flexible satellite is in the separated state, a start control command is generated;

[0009] The flexible satellite is controlled to enter the working state based on the start-up control command.

[0010] In some embodiments, the start-up control commands include opening the solar panels and / or opening the communication channel.

[0011] In some embodiments, the state signal includes a pressure signal and / or a light intensity signal; determining the current state of the flexible satellite based on the state signal includes:

[0012] The current state of the flexible satellite is determined based on the pressure signal and / or the light intensity signal.

[0013] In some embodiments, determining the current state of the flexible satellite based on the pressure signal and / or the light intensity signal includes:

[0014] When the pressure signal is less than the pressure threshold and / or the light intensity signal is greater than the light intensity threshold, it is determined that the flexible satellite is in a separated state.

[0015] When the pressure signal is greater than the pressure threshold and / or the light intensity signal is less than the light intensity threshold, it is determined that the flexible satellite is in the onboard state.

[0016] In some embodiments, after controlling the flexible satellite to enter the working state based on the activation control command, the method further includes:

[0017] When the light intensity signal is less than the light intensity threshold, the solar panels are turned off.

[0018] In some embodiments, after controlling the flexible satellite to enter the working state based on the activation control command, the method further includes:

[0019] It receives and displays the operational control commands sent by the host satellite in real time.

[0020] In some embodiments, it also includes:

[0021] Obtain the operational time of the flexible satellite;

[0022] When the running time exceeds a time threshold, a start control command is generated;

[0023] The flexible satellite is controlled to enter the working state based on the start-up control command.

[0024] Secondly, embodiments of this application provide a separation control device for a flexible satellite, comprising:

[0025] The signal acquisition unit is used to acquire the state signals of the flexible satellite surface.

[0026] A current state determination unit is used to determine the current state of the flexible satellite based on the state signal; wherein the current state includes the onboard state and the separated state;

[0027] The first instruction generation unit is used to generate a start control instruction when the flexible satellite is in the separated state;

[0028] The first state control unit is used to control the flexible satellite to enter the working state based on the start control command.

[0029] Thirdly, embodiments of this application provide a computer device, including a memory, a processor, a sensor module, and a display module, as well as a computer program stored in the memory and executable on the processor. The sensor module and display module are disposed on the flexible satellite and connected to the processor. When the processor executes the computer program, it implements the separation control method for the flexible satellite as described in the first aspect above.

[0030] Fourthly, embodiments of this application provide a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the separation control method for flexible satellites as described in the first aspect above.

[0031] Compared to related technologies, the flexible satellite separation control method provided in this application obtains the state signal of the flexible satellite surface, determines the current state of the flexible satellite based on the state signal, and generates a start control command to control the flexible satellite to enter the working state when the flexible satellite is in the separation state. This realizes the automatic start of the working state when the two satellites separate, which facilitates the automatic control of the flexible satellite start subsystem and its auxiliary devices after separation, and enhances the reliability of the control process.

[0032] Details of one or more embodiments of this application are set forth in the following drawings and description to make other features, objects and advantages of this application more readily apparent. Attached Figure Description

[0033] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0034] Figure 1 This is a schematic diagram of the structure of a flexible satellite in one embodiment (the solar panels are in the off state).

[0035] Figure 2 This is a schematic diagram of the structure of a flexible satellite in one embodiment (with the solar panels in the open state).

[0036] Figure 3 This is a schematic diagram of the interface structure of a flexible satellite in one embodiment;

[0037] Figure 4 This is a flowchart illustrating the separation control method for a flexible satellite in one embodiment;

[0038] Figure 5 This is a flowchart illustrating a preferred embodiment of a flexible satellite separation control method.

[0039] Figure 6This is a structural block diagram of the separation control device for a flexible satellite in one embodiment;

[0040] Figure 7 This is a schematic diagram of the structure of a computer device in one embodiment.

[0041] Figure descriptions: 101-Flexible satellite body; 1021-Pressure sensor module; 1022-Photosensitive sensor module; 103-Solar panel; 104-Wireless communication module; 105 / 74-Display module; 301-Signal acquisition unit; 302-Current state judgment unit; 303-First instruction generation unit; 304-First state control unit; 70-Bus; 71-Processor; 72-Memory; 73-Sensor module; 75-Communication module. Detailed Implementation

[0042] To make the objectives, technical solutions, and advantages of this application clearer, the application is described and illustrated below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application. All other embodiments obtained by those skilled in the art based on the embodiments provided in this application without inventive effort are within the scope of protection of this application.

[0043] Obviously, the accompanying drawings described below are merely some examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios based on these drawings without any inventive effort. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this application, any changes to design, manufacturing, or production based on the technical content disclosed in this application are merely conventional technical means and should not be construed as insufficient disclosure of the content of this application.

[0044] In this application, the reference to "embodiment" means that a specific feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places in the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment that is mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described in this application may be combined with other embodiments without conflict.

[0045] Unless otherwise defined, the technical or scientific terms used in this application shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms “a,” “an,” “an,” “the,” and similar words used in this application do not indicate quantity limitation and may indicate singular or plural. The terms “comprising,” “including,” “having,” and any variations thereof used in this application are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or device that includes a series of steps or modules (units) is not limited to the listed steps or units, but may also include steps or units not listed, or may include other steps or units inherent to these processes, methods, products, or devices. The terms “connected,” “linked,” “coupled,” and similar words used in this application are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. “Multiple” used in this application refers to two or more. “And / or” describes the relationship between related objects, indicating that three relationships may exist; for example, “A and / or B” can represent: A alone, A and B simultaneously, and B alone. The character " / " generally indicates that the preceding and following objects are in an "or" relationship. The terms "first," "second," and "third" used in this application are merely to distinguish similar objects and do not represent a specific ordering of the objects.

[0046] With the advancement of technology, spacecraft development has become increasingly diverse. As people's needs become more diversified, microsatellites, with their characteristics of light weight, small size, low cost, short development cycle, low risk, and good performance, have attracted widespread attention and are continuously developing in payload, control, propulsion, and telemetry. Among them, flexible satellites are spacecraft with a typical structural feature of a central rigid body plus lightweight flexible accessories, exhibiting rigid-flexible coupling. Flexible satellites have a compressible, flexible, and deployable structure, enabling the deployment of large-aperture antennas in space and their compact size on the ground for mounting on rockets, thus broadening their practical applications.

[0047] Figure 1-2 This is a schematic diagram of the structure of the flexible satellite provided in this embodiment, as shown below. Figure 1-2 As shown, this embodiment provides a flexible satellite, including: a flexible satellite body 101, a main control module, a sensor module, and a solar panel 103. Wherein:

[0048] The sensor module is attached to the surface of the flexible satellite body 101 and connected to the main control module, and is used to detect the state signals of the flexible satellite surface and send them to the main control module. Optionally, the state signals include pressure signals and / or light intensity signals; the sensor module includes: a pressure sensor module 1021 and / or a photosensor module 1022. The pressure sensor module 1021 is used to detect the pressure signals on the surface of the flexible satellite body 101 and send them to the main control module; the photosensor module is used to detect the light intensity signals on the surface of the flexible satellite body 101 and send them to the main control module.

[0049] For example, the pressure sensor can be a flexible pressure sensor with high sensitivity, high resolution, and fast response characteristics, such as the DF9-40 series flexible thin-film pressure sensor or the FSR series flexible pressure sensor (e.g., the D2027 flexible thin-film pressure sensor), which can be easily attached to the surface of irregular objects. The photosensitive sensor is a photoresistor, such as a 5516 photoresistor. Of course, the pressure sensor and the photosensitive sensor can also be other existing sensors, and appropriate models can be selected according to actual needs. Here, the present invention does not impose specific limitations.

[0050] Specifically, in some other embodiments, a current-limiting resistor is connected in series between the sensor module and the main control module to limit the current flowing through the sensor module. Preferably, the resistance range of the current-limiting resistor is 10Ω-100Ω.

[0051] The solar panel 103 is disposed circumferentially on the flexible satellite body 101 and electrically connected to the main control module, and is used to supply power to the flexible satellite when in operation. Preferably, the solar panel 103 is a flexible solar panel, which has advantages such as being lightweight, flexible, small in size, and having high power generation efficiency. Typically, the solar panel 103 is arranged on both sides of the flexible satellite along its orbital flight direction. When the drive mechanism of the solar panel receives the start control command including opening the solar panel 103, the drive mechanism can automatically control the solar panel 103 of the flexible satellite from the closed state (e.g., ...). Figure 1 (As shown) extended to the open state (and Figure 2 As shown in the image, this technology collects solar energy, enabling the satellite to have an independent energy supply capability.

[0052] In one embodiment, the flexible satellite further includes a servo motor disposed inside the satellite body, the servo motor being electrically connected to the main control module and its output shaft being connected to the solar panel 103. The servo motor can be used to receive start-up control commands sent by the main control module and to control the deployment and deactivation of the solar panel 103.

[0053] The main control module is located inside the flexible satellite body 101 and is used to receive the status signals and control the solar panels 103 to enter the working state according to the status signals. Optionally, the main control module can use an ATMEGA2560 control chip, which processes various received command data and completes the corresponding control requirements.

[0054] In one embodiment, the flexible satellite further includes a wireless communication module 104, which is connected to the main control module and used to establish a communication connection with the parent satellite. Specifically, the wireless communication module 104 receives work control commands sent by the parent satellite and sends them to the main control module for corresponding processing, and can feed back processing results and working status to the parent satellite. Optionally, the wireless communication module 104 can be a flexible antenna, an XBEE module, or other wireless communication modules 104, and the appropriate model can be selected according to the actual situation. Here, the present invention does not impose specific limitations. Preferably, the flexible satellite further includes a display module 105 disposed on the surface of the flexible satellite body 101. The display module 105 is connected to the main control module and is used to display the work control commands sent by the parent satellite in real time. Of course, the display module 105 can display real-time working status, command content, and command processing progress. In a preferred embodiment, the display module 105 can be an OLED screen, which can be connected to the control module through an LCD interface.

[0055] For example, Figure 3 This is a schematic diagram of the hardware interface structure of a flexible satellite, such as... Figure 3 As shown, the flexible satellite includes a main control module (MCU), a pressure sensor module 1021, a photosensor module 1022, a wireless communication module 104, a display module 105, a servo motor, and a current-limiting resistor. The pressure sensor module 1021 is a D2027 flexible thin-film pressure sensor, the photosensor module 1022 is a photoresistor, the wireless communication module 104 is an XBEE communication module, and the display module 105 is an OLED. The wireless communication module 104, the display module 105, and the servo motor are all connected to the main control module (MCU). The current-limiting resistor includes a first current-limiting resistor and a second current-limiting resistor. The first current-limiting resistor is connected in series between the main control module (MCU) and the photosensor module; the second current-limiting resistor is connected in series between the main control module (MCU) and the pressure sensor module. Optionally, the pressure sensor module and the photosensitive sensor module 1022 are configured as one or more, and each photosensitive sensor module 1022 is connected in series with the main control module MCU with a first current-limiting resistor; each pressure sensor module 1021 is connected in series with the main control module MCU with a second current-limiting resistor.

[0056] This embodiment also provides a separation control system for a flexible satellite, including: a parent satellite and at least one flexible satellite as described above; wherein the parent satellite and the flexible satellite are in a mounted state or a separated state. The flexible satellite is used to control the solar panel 103 to enter the working state when separated from the parent satellite; the parent satellite is used to carry the flexible satellite and send working control commands to it after the solar panel 103 enters the working state.

[0057] In this implementation, a parent satellite typically carries one or more flexible satellites. When the parent satellite reaches its predetermined orbit, the flexible satellites separate from it via ejection. After separation, the flexible satellite enters its operational orbit, and the satellite maintenance aircraft activates its subsystems, enabling the flexible satellite to enter operational status after separation and be controlled by the parent satellite.

[0058] This embodiment also provides a method for separating and controlling a flexible satellite. Figure 4 This is a flowchart of a flexible satellite separation control method according to an embodiment of this application, such as... Figure 4 As shown, the process includes the following steps:

[0059] Step S201: Obtain the state signal of the flexible satellite surface.

[0060] In this embodiment, a microsatellite (parent satellite) can carry multiple compressible flexible satellites. Before the flexible satellites separate from the parent satellite and are ejected, they remain in a compressed state. When the microsatellite reaches its fixed orbit, it separates from one or more flexible satellites. At this time, the surface state of the flexible satellite changes, generating a changing state signal.

[0061] The status signal corresponds to the current state of the flexible satellite, and may be, for example, an image signal, a time signal, a light intensity signal, or a pressure signal, etc. This application does not make any specific limitation.

[0062] Step S202: Determine the current state of the flexible satellite based on the state signal; wherein the current state includes the mounted state and the separated state.

[0063] In one embodiment, the state signal includes a pressure signal and / or a light intensity signal; then determining the current state of the flexible satellite based on the state signal includes: determining the current state of the flexible satellite based on the pressure signal and / or the light intensity signal.

[0064] Specifically, the flexible satellite has sensor modules attached to its surface, which are pressure sensors and / or photosensors. Before separation, the flexible satellite is in a compressed state; upon ejection, the pressure changes abruptly. The voltage applied to the pressure sensor on the flexible satellite's surface changes with its resistance: the greater the pressure on the flexible satellite's surface, the smaller the resistance of the pressure sensor, and thus the smaller the voltage it bears. Therefore, the pressure sensor can be used to monitor the pressure signal on the flexible satellite's surface and transmit it to the main control module. Simultaneously, before separation, the flexible satellite is in the ejection box where the light is dim; upon ejection into space, the light intensity changes abruptly. The voltage applied to the photosensor on the flexible satellite's surface changes with its resistance: the greater the light intensity on the flexible satellite's surface, the smaller the resistance of the photosensor. Therefore, the photosensor can be used to detect the light intensity signal on the flexible satellite's surface and transmit it to the main control module.

[0065] When at least one of the pressure signal and light intensity signal undergoes a sudden change, it can be determined that the flexible satellite is in a mounted or separated state. Specifically, when the pressure signal is less than a pressure threshold and / or the light intensity signal is greater than a light intensity threshold, the flexible satellite is determined to be in a separated state; when the pressure signal is greater than a pressure threshold and / or the light intensity signal is less than a light intensity threshold, the flexible satellite is determined to be in a mounted state.

[0066] Step S203: When the flexible satellite is in a separated state, a start control command is generated.

[0067] Step S204: Control the flexible satellite to enter the working state based on the start-up control command.

[0068] In this embodiment, after the flexible satellite separates from the parent satellite, the flexible satellite's satellite maintenance unit needs to activate the satellite maintenance system according to the activation control command, so that the flexible satellite enters the working state after separation, in order to realize the operation management, automatic control, information transmission, etc. of the flexible satellite.

[0069] The satellite service system typically includes a satellite service host and multiple satellite service subsystems. The satellite service host manages the satellite service subsystems, which may include, for example, a position and attitude control subsystem, a communication subsystem, a temperature control subsystem, a power supply subsystem, a storage subsystem, and a payload subsystem (for remote sensing satellites, the payload subsystem may be a camera subsystem). Correspondingly, the start-up control commands include activating the solar panel 103, activating the communication channel, activating positioning, activating the scanner or camera, and remote desktop connection, etc.

[0070] The embodiments of this application will be described and illustrated below through preferred embodiments.

[0071] In one embodiment, after controlling the flexible satellite to enter the working state based on the start control command, the method further includes: turning off the solar panel 103 when the light intensity signal is less than the light intensity threshold.

[0072] In this embodiment, the efficiency of the solar panel 103 is closely related to the intensity of the light intensity signal. Generally, the stronger the light intensity signal, the greater the efficiency of the solar panel 103. When the light intensity signal is less than the light intensity threshold (e.g., when the satellite is in darkness), the solar panel 103 is inefficient and can be turned off.

[0073] In one embodiment, after controlling the flexible satellite to enter the working state based on the activation control command, the method further includes:

[0074] Step S205: Receive the work control commands sent by the mother satellite and display them in real time.

[0075] In this embodiment, the separation control device further includes a display module 105, which is disposed on the flexible satellite and connected to the main control module. It is used to display the work control commands sent by the parent satellite in real time. For example, the display module 105 can display the content of the work control commands, the sending status, the processing status, and the network connection status, etc., so as to facilitate real-time monitoring of the processing status of the work control commands.

[0076] In one preferred embodiment, it further includes:

[0077] Step S206: Obtain the flexible satellite's operating time;

[0078] Step S207: When the running time is greater than the time threshold, a start control command is generated;

[0079] Step S208: Control the flexible satellite to enter the working state based on the start control command.

[0080] In this embodiment, in order to gradually start the payload, ensure the normal operation of the satellite and enhance the operational reliability of the flexible satellite, the operation of the flexible satellite can be monitored by timing control: for example, the start time and mills functions can be programmed to automatically jump to the solar panel 103 judgment link when a fixed time is reached, as a supplement to the current state judgment link of the flexible satellite mentioned above.

[0081] See Figure 5As shown, in one embodiment, after the satellite is started, a delay procedure is initiated. The flexible satellite's operating time is acquired. When the operating time exceeds a time threshold, a start-up control command is generated. The control module then controls the flexible satellite to enter the working state and deploys the solar panels 103. Simultaneously, the current state of the flexible satellite is determined by acquiring state signals from its surface. Specifically, the current state can be determined based on the pressure signal and / or the light intensity signal. When the pressure signal is less than a pressure threshold and / or the light intensity signal is greater than a light intensity threshold, the flexible satellite is determined to be in a separated state. At this time, the control module controls the flexible satellite to enter the working state and deploys the solar panels 103. The satellite can then receive and display the working control commands sent by the parent satellite in real time. When the light intensity signal is less than a light intensity threshold, the flexible satellite is determined to be in a mounted state, and the solar panels 103 are deactivated.

[0082] It should be noted that the steps shown in the above process or in the flowchart of the accompanying figures can be executed in a computer system such as a set of computer-executable instructions, and although a logical order is shown in the flowchart, in some cases the steps shown or described may be executed in a different order than that shown here.

[0083] This embodiment also provides a separation control device for a flexible satellite, which is used to implement the above embodiments and preferred embodiments, and will not be repeated as described above. As used below, the terms "module," "unit," "subunit," etc., can refer to a combination of software and / or hardware that performs a predetermined function. Although the device described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0084] Figure 6 This is a structural block diagram of a separation control device for a flexible satellite according to an embodiment of this application, such as... Figure 6 As shown, the device includes:

[0085] The signal acquisition unit 301 is used to acquire the state signals of the flexible satellite surface;

[0086] The current state determination unit 302 is used to determine the current state of the flexible satellite based on the state signal; wherein, the current state includes the onboard state and the separated state;

[0087] The first instruction generation unit 303 is used to generate a start control instruction when the flexible satellite is in the separated state;

[0088] The first state control unit 304 is used to control the flexible satellite to enter the working state based on the start control command.

[0089] In some embodiments, the start-up control commands include turning on the solar panel 103 and / or turning on the communication channel.

[0090] In some embodiments, the state signal includes a pressure signal and / or a light intensity signal; then the current state determination unit 302 includes a signal determination module.

[0091] The signal determination module is used to determine the current state of the flexible satellite based on the pressure signal and / or the light intensity signal.

[0092] The signal determination module includes: a first state determination module and a second state determination module.

[0093] The first state determination module is used to determine that the flexible satellite is in a separated state when the pressure signal is less than the pressure threshold and / or the light intensity signal is greater than the light intensity threshold.

[0094] The second state determination module is used to determine that the flexible satellite is in the onboard state when the pressure signal is greater than the pressure threshold and / or the light intensity signal is less than the light intensity threshold.

[0095] The separation control device for flexible satellites also includes a second state control unit.

[0096] The second state control unit is used to turn off the solar panel 103 when the light intensity signal is less than the light intensity threshold.

[0097] The separation control device for flexible satellites also includes a display unit.

[0098] The display unit is used to receive and display the work control commands sent by the mother satellite in real time.

[0099] The separation control device for flexible satellites also includes:

[0100] The runtime acquisition unit is used to acquire the runtime of the flexible satellite;

[0101] The second instruction generation unit is used to generate a start control instruction when the running time is greater than a time threshold.

[0102] The third state control unit is used to control the flexible satellite to enter the working state based on the start control command.

[0103] It should be noted that the above modules can be functional modules or program modules, and can be implemented through software or hardware. For modules implemented through hardware, the above modules can reside in the same processor; or the above modules can be located in different processors in any combination.

[0104] In addition, combined Figure 4 The separation control method for a flexible satellite described in this application embodiment can be implemented using computer equipment. Figure 7 This is a schematic diagram of the hardware structure of a computer device according to an embodiment of this application.

[0105] The computer device may include a processor 71, a memory 72, a sensor module 73, and a display module 74, as well as a computer program stored in the memory 72 and executable on the processor 71. The sensor module 73 and the display module 74 are disposed on the flexible satellite and connected to the processor 71. When the processor 71 executes the computer program, it implements the separation control method of the flexible satellite as described above.

[0106] Specifically, the processor 71 may include a central processing unit (CPU), an application specific integrated circuit (ASIC), or one or more integrated circuits that can be configured to implement the embodiments of this application.

[0107] The memory 72 may include a mass storage device for data or instructions. For example, and not limitingly, the memory 72 may include a hard disk drive (HDD), a floppy disk drive, a solid-state drive (SSD), flash memory, an optical disk drive, a magneto-optical disk drive, magnetic tape, or a Universal Serial Bus (USB) drive, or a combination of two or more of these. Where appropriate, the memory 72 may include removable or non-removable (or fixed) media. Where appropriate, the memory 72 may be internal or external to a data processing device. In a particular embodiment, the memory 72 is non-volatile memory. In a particular embodiment, the memory 72 includes read-only memory (ROM) and random access memory (RAM). Where appropriate, the ROM may be a mask-programmed ROM, a programmable read-only memory (PROM), an erasable programmable read-only memory (EPROM), an electrically erasable programmable read-only memory (EEPROM), an electrically alterable read-only memory (EAROM), or flash memory, or a combination of two or more of these. Where appropriate, the RAM can be Static Random-Access Memory (SRAM) or Dynamic Random-Access Memory (DRAM). DRAM can be Fast Page Mode Dynamic Random-Access Memory (FPMDRAM), Extended Data Out Dynamic Random-Access Memory (EDODRAM), Synchronous Dynamic Random-Access Memory (SDRAM), etc.

[0108] The memory 72 can be used to store or cache various data files that need to be processed and / or communicated, as well as possible computer program instructions executed by the processor 71.

[0109] The processor 71 reads and executes computer program instructions stored in the memory 72 to implement any of the flexible satellite separation control methods in the above embodiments.

[0110] In some embodiments, the computer device may further include a communication module 75 and a bus 70. For example, Figure 7 As shown, the processor 71, memory 72, and communication module 75 are connected via bus 70 and communicate with each other.

[0111] The communication module 75 is used to enable communication between the various modules, devices, units, and / or equipment in the embodiments of this application. The communication module 75 can also enable data communication with other components such as external devices, image / data acquisition devices, databases, external storage, and image / data processing workstations.

[0112] Bus 70 includes hardware, software, or both, that couples components of a computer device together. Bus 70 includes, but is not limited to, at least one of the following: data bus, address bus, control bus, expansion bus, and local bus. For example, and not as a limitation, bus 70 may include an Accelerated Graphics Port (AGP) or other graphics bus, an Extended Industry Standard Architecture (EISA) bus, a Front Side Bus (FSB), a Hyper Transport (HT) interconnect, an Industry Standard Architecture (ISA) bus, an InfiniBand interconnect, a Low Pin Count (LPC) bus, a memory bus, a Micro Channel Architecture (MCA) bus, a Peripheral Component Interconnect (PCI) bus, a PCI-Express (PCI-X) bus, a Serial Advanced Technology Attachment (SATA) bus, a Video Electronics Standards Association Local Bus (VLB) bus, or other suitable buses, or a combination of two or more of these. Where appropriate, bus 70 may include one or more buses. Although specific buses are described and illustrated in the embodiments of this application, this application considers any suitable bus or interconnection.

[0113] The computer device can execute the flexible satellite separation control method in this application embodiment based on the acquired flexible satellite separation control method, thereby achieving the combination Figure 4 The method for separating and controlling flexible satellites is described.

[0114] Furthermore, in conjunction with the flexible satellite separation and control method in the above embodiments, this application embodiment can provide a computer-readable storage medium for implementation. This computer-readable storage medium stores computer program instructions; when executed by a processor, these computer program instructions implement any of the flexible satellite separation and control methods in the above embodiments.

[0115] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0116] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A separation control method of a flexible satellite, characterized by, The method comprises the following steps: acquiring a state signal of a flexible satellite surface; the state signal comprises a pressure signal and / or a light intensity signal; determining a current state of the flexible satellite based on the state signal; wherein the current state comprises a carrying state and a separation state; a sensor module is attached to the surface of the flexible satellite; the sensor module is a pressure sensor and / or a light-sensitive sensor; before the flexible satellite is separated, the flexible satellite is in a compressed state, and the pressure changes suddenly when the flexible satellite is ejected; when the pressure on the surface of the flexible satellite is greater, the resistance of the pressure sensor attached to the surface of the flexible satellite is smaller, and the voltage value shared by the pressure sensor is also smaller; before the flexible satellite is separated, the flexible satellite is in a launching box, and the light is dim; when the flexible satellite is ejected into space, the light intensity changes suddenly; when the light intensity on the surface of the flexible satellite is greater, the resistance of the light-sensitive sensor attached to the surface of the flexible satellite is smaller; when the pressure signal is less than a pressure threshold value and / or the light intensity signal is greater than a light intensity threshold value, it is determined that the flexible satellite is in the separation state; when the pressure signal is greater than the pressure threshold value and / or the light intensity signal is less than the light intensity threshold value, it is determined that the flexible satellite is in the carrying state; when the flexible satellite is in the separation state, a start control instruction is generated; the flexible satellite is controlled to enter a working state based on the start control instruction.

2. The separation control method of a flexible satellite according to claim 1, characterized by, The start control instruction comprises opening a solar panel and / or opening a communication channel.

3. The separation control method of a flexible satellite according to claim 1, characterized by, After the flexible satellite is controlled to enter the working state based on the start control instruction, the following steps are further included: when the light intensity signal is less than the light intensity threshold value, the solar panel is closed.

4. The separation control method of a flexible satellite according to claim 1, characterized by, After the flexible satellite is controlled to enter the working state based on the start control instruction, the following steps are further included: a working control instruction sent by a mother star is received and displayed in real time.

5. The separation control method of a flexible satellite according to claim 1, wherein The method further comprises the following steps: acquiring a running time of the flexible satellite; when the running time is greater than a time threshold value, a start control instruction is generated; the flexible satellite is controlled to enter a working state based on the start control instruction.

6. A separation control device for a flexible satellite, characterized by The method comprises the following steps: a signal acquisition unit is configured to acquire a state signal of a flexible satellite surface; the state signal comprises a pressure signal and / or a light intensity signal; a current state judgment unit is configured to determine a current state of the flexible satellite based on the state signal; wherein the current state comprises a carrying state and a separation state; a sensor module is attached to the surface of the flexible satellite; the sensor module is a pressure sensor and / or a light-sensitive sensor; before the flexible satellite is separated, the flexible satellite is in a compressed state, and the pressure changes suddenly when the flexible satellite is ejected; when the pressure on the surface of the flexible satellite is greater, the resistance of the pressure sensor attached to the surface of the flexible satellite is smaller, and the voltage value shared by the pressure sensor is also smaller; before the flexible satellite is separated, the flexible satellite is in a launching box, and the light is dim; when the flexible satellite is ejected into space, the light intensity changes suddenly; when the light intensity on the surface of the flexible satellite is greater, the resistance of the light-sensitive sensor attached to the surface of the flexible satellite is smaller; when the pressure signal is less than a pressure threshold value and / or the light intensity signal is greater than a light intensity threshold value, it is determined that the flexible satellite is in the separation state; when the pressure signal is greater than the pressure threshold value and / or the light intensity signal is less than the light intensity threshold value, it is determined that the flexible satellite is in the carrying state; The first instruction generating unit is configured to generate a start control instruction when the flexible satellite is in the separation state. The first state control unit is configured to control the flexible satellite to enter a working state based on the start control instruction. 7.A computer device, comprising a memory, a processor, a sensor module and a display module, and a computer program stored on the memory and executable on the processor, characterized in that, The sensor module display module is arranged on the flexible satellite and connected with the processor, and the processor implements the separation control method of the flexible satellite according to any one of claims 1 to 5 when executing the computer program.

8. A computer-readable storage medium having stored thereon a computer program, characterized in that, The program is executed by the processor to implement the separation control method of the flexible satellite according to any one of claims 1 to 5.

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