On-orbit fault diagnosis and health management method and system based on satellite-borne photoelectric slip ring

Abstract

The application relates to a method and system for on-orbit fault diagnosis and health management based on a spaceborne photoelectric slip ring. The method comprises the following steps: constructing a photoelectric conversion system, wherein the photoelectric conversion system comprises a photoelectric slip ring, a baseline conversion module and a platform conversion module, the baseline conversion module is located in a satellite rotating cabin, and the platform conversion module is located in a satellite platform cabin; using a platform integrated electronic and load management unit to perform state monitoring on the platform conversion module and the baseline conversion module respectively; performing state monitoring and safety management on a CAN bus between the satellite rotating cabin and the satellite platform cabin; and performing independent power distribution on the platform conversion module and the baseline conversion module, and autonomously controlling power-off according to health criteria. According to the method, a dynamic threshold is designed for a secondary power supply, seamless switching of a main and standby power supply is realized, and the delay and error code problems of CAN bus communication between the satellite rotating cabin and the satellite platform cabin are solved by combining a double bus handshake and an FPGA reset strategy.

Description

Technical Field

[0001] This invention relates to the field of satellite autonomous health management technology, and in particular to an on-orbit fault diagnosis and health management method and system based on a spaceborne optoelectronic slip ring. Background Technology

[0002] Currently, there are numerous spacecraft in orbit, evolving from satellites that initially carried no scientific instruments to space stations and deep-space landers with complex functions. To adapt to complex environments or complete specific missions, spacecraft mechanical mechanisms need to rotate relative to each other. To ensure data transfer between relatively rotating spacecraft components, conductive slip rings are needed to establish electrical pathways for data transmission between these components.

[0003] Currently, power supply and digital signal transmission in the rotating state of onboard rotating mechanisms typically employ products such as conductive slip rings. These systems primarily achieve electrical signal transmission through the contact of the slip ring's brush filaments. The signal stability during transmission is affected by the dynamic contact resistance of the conductive slip ring, making it prone to transmission errors. While common signal transmission and signal level conversion methods such as CAN bus, 422 bus, LVDS, and optical signals are relatively mature in ground-based rotating mechanism equipment, their application in space applications such as satellites is limited by factors such as the lifespan and wear of the rotating mechanism and the reliability of signal transmission. This restricts the amount and rate of data transmitted between traditional conductive slip ring rotating components and fixed platforms. Currently, there is a lack of monitoring and health management methods for power supply status and digital signal transmission during data transmission between onboard satellite rotating modules, resulting in poor on-orbit maintenance capabilities.

[0004] Radio frequency (RF) signal transmission in a rotating state typically employs products such as smooth loops and RF rotary joints. Currently, spaceborne RF channels are mainly used for telemetry, tracking, command and control (TT&C), data transmission, navigation and positioning, and payloads, requiring high reliability. For RF transmission between rotating modules of spaceborne satellites, smooth loops have already been implemented in orbit, offering advantages such as large data transmission capacity and low insertion loss. Spaceborne RF signals primarily interact with ground and inter-satellite signals, and are closely related to the mission application needs of users and TT&C systems. Therefore, health management of smooth loop RF signal transmission is particularly important.

[0005] Currently, in the field of spaceborne radio frequency (RF) signal transmission technology, the main products include waveguide rotary joints and coaxial rotary joints, focusing primarily on RF signal transmission performance. Digital signal transmission mainly relies on conductive slip ring contact transmission. However, there are limitations in managing the performance of RF signal transmission, the health status of the link, and health management. While smooth slip rings, with their large transmission bandwidth, low insertion loss, and low wear characteristics, have been successfully applied in orbit, many limitations still exist regarding their reliability and safety in orbit, particularly in terms of health management. Summary of the Invention

[0006] To address some or all of the problems in existing technologies, this invention provides an on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring, the method comprising the following steps:

[0007] A photoelectric conversion system is constructed, which includes a photoelectric slip ring, a baseline conversion module, and a platform conversion module. The baseline conversion module is located in the satellite rotation cabin, and the platform conversion module is located in the satellite platform cabin.

[0008] The platform integrated electronics and payload management unit is used to perform status monitoring on the platform conversion module and the baseline conversion module, respectively, including the following steps:

[0009] The secondary power supply voltages of the platform conversion module and the baseline conversion module are monitored in real time. When the voltage value exceeds a preset threshold range and the duration exceeds a set time, a primary / backup power switching command is triggered; and

[0010] When the platform integrated electronics and load management unit is reset, the secondary power supply monitoring status and configuration parameters of the platform conversion module and the baseline conversion module are saved.

[0011] Perform status monitoring and safety management on the CAN bus between the satellite rotating cabin and the satellite platform cabin; and

[0012] Independent power distribution is performed on the platform conversion module and the baseline conversion module, and power is autonomously controlled to be added or cut off based on health criteria.

[0013] Furthermore, the secondary power supply voltages of the platform conversion module and the baseline conversion module are monitored in real time. When the voltage value exceeds a preset threshold range and the duration exceeds a set time, a main / backup power switching command is triggered, including:

[0014] The +5V main power supply voltage and -5V main power supply voltage of the platform conversion module and the baseline conversion module are monitored in real time.

[0015] The preset threshold range includes a first preset threshold range and a second preset threshold range. The first preset threshold range is a +5V main power supply voltage of not less than 2.2V and not more than 3.2V, and the second preset threshold range is a -5V main power supply voltage of not less than 1.4V and not more than 2.2V.

[0016] The set duration is 5 seconds;

[0017] When the voltage value exceeds the first preset threshold range or the second preset threshold range, and the duration exceeds the set duration, the load management unit sends an instruction to shut down the main power supply and turn on the backup power supply.

[0018] Furthermore, the feature is that when the platform integrated electronics and load management unit is reset, the saving of the secondary power supply monitoring status and configuration parameters of the platform conversion module and the baseline conversion module includes:

[0019] When the platform integrated electronics and load management unit is reset, the secondary power supply monitoring status of the platform conversion module and the baseline conversion module is saved as the state before the reset.

[0020] The configuration parameters are the configuration parameters of the +5V main power supply voltage and the -5V main power supply voltage of the platform conversion module and the baseline conversion module.

[0021] Furthermore, the status monitoring and safety management of the CAN bus between the satellite rotating cabin and the satellite platform cabin includes:

[0022] The platform's integrated electronics and payload management unit monitors the status of the CAN bus between the satellite rotating cabin and the satellite platform cabin through a dual-bus handshake mechanism.

[0023] When the load management unit does not receive a CAN telemetry request signal from the platform's integrated electronic CAN for 10 consecutive seconds, it will reset the CAN bus chip.

[0024] If the load management unit does not receive a CAN telemetry request signal from the platform integrated electronics for 45 consecutive seconds, the platform integrated electronics and the load management unit will respectively perform a reset on the platform conversion module and the baseline conversion module FPGA.

[0025] Furthermore, independent power distribution is performed on the platform conversion module and the baseline conversion module, and autonomous power-on / off control is implemented based on health criteria, including:

[0026] The satellite's rotating cabin is powered via an electric slip ring; the platform's integrated electronics autonomously manage the power-on and power-off of the platform conversion module and the baseline conversion module based on health criteria.

[0027] Furthermore, the photoelectric slip ring is located in the turntable, and the photoelectric slip ring includes a smooth ring and an electric slip ring;

[0028] The smooth ring is connected in series with the electric slip ring; the smooth ring includes a smooth ring stator and a smooth ring rotor; the electric slip ring includes an electric slip ring stator and an electric slip ring rotor;

[0029] The smooth ring rotor and the electric slip ring rotor are connected via a shift fork mechanism. The turntable stator is connected to both the smooth ring stator and the electric slip ring stator. The electric slip ring is driven to rotate by a turntable shift lever, and the smooth ring is driven to rotate by an electric slip ring shift lever.

[0030] The smooth ring rotor is connected to the baseline conversion module, and the smooth ring stator is connected to the platform conversion module.

[0031] Furthermore, the platform conversion module is connected to the corresponding single-unit power supply interface and remote control and telemetry signals of the satellite platform cabin, and the baseline conversion module is connected to the corresponding single-unit power supply interface and remote control and telemetry signals of the satellite rotating cabin.

[0032] The present invention also provides a system for the aforementioned on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip rings, the system comprising:

[0033] A photoelectric conversion system construction module is configured to construct a photoelectric conversion system, which includes a photoelectric slip ring, a baseline conversion module, and a platform conversion module. The baseline conversion module is located in the satellite rotation cabin, and the platform conversion module is located in the satellite platform cabin.

[0034] The status monitoring module is configured to use the platform integrated electronics and load management unit to perform status monitoring on the platform conversion module and the baseline conversion module, respectively.

[0035] The CAN bus management module is configured to perform status monitoring and security management of the CAN bus between the satellite rotating cabin and the satellite platform cabin; and

[0036] The power supply management module is configured to perform independent power distribution to the platform conversion module and the baseline conversion module, and to autonomously control power on / off based on health criteria.

[0037] The present invention also provides an electronic device, comprising:

[0038] A processor, configured to execute machine-readable instructions;

[0039] A graphics card equipped with an artificial intelligence chip is configured to train an on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring; and

[0040] The memory is configured to store machine-readable instructions that, when executed by a processor and / or graphics card, perform the steps of the on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring.

[0041] The present invention also provides a computer-readable storage medium storing machine-readable instructions thereon, which, when executed by a processor, perform the steps of the on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring.

[0042] The technical solution provided by this invention has the following advantages:

[0043] 1. The present invention proposes an on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring. It proposes an optoelectronic conversion system that transmits high-speed electrical signals from the satellite's rotating cabin through an electric slip ring and transmits spaceborne digital signals, optical signals, and radio frequency signals through a smooth ring, thereby reducing signal entanglement and bit error problems.

[0044] 2. The on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip ring proposed in this invention designs dynamic thresholds for secondary power supplies (+5V / -5V) to achieve seamless switching between primary and backup power supplies.

[0045] 3. The on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip ring proposed in this invention, combined with strategies such as dual-bus handshake and FPGA reset, solves the problems of delay and bit error in CAN bus communication between the satellite rotating cabin and the satellite platform cabin.

[0046] 4. The on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip ring proposed in this invention saves key parameters through non-volatile memory to ensure automatic configuration recovery after reset.

[0047] 5. The on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip ring proposed in this invention uses independent power distribution for the optoelectronic conversion system to avoid power supply abnormalities spreading to other payload units. Attached Figure Description

[0048] To further illustrate the above and other advantages and features of the various embodiments of the present invention, a more specific description of the various embodiments of the present invention will be presented with reference to the accompanying drawings. It is to be understood that these drawings depict only typical embodiments of the invention and are therefore not intended to limit its scope. In the drawings, identical or corresponding parts will be indicated by identical or similar reference numerals for clarity.

[0049] Figure 1 A flowchart illustrating an embodiment of the present invention for an on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring is shown.

[0050] Figure 2 A schematic diagram of the compartment design of a photoelectric conversion system according to an embodiment of the present invention is shown;

[0051] Figure 3 A schematic diagram of a photoelectric conversion system according to an embodiment of the present invention is shown;

[0052] Figure 4 A schematic diagram of a photoelectric slip ring structure according to an embodiment of the present invention is shown;

[0053] Figure 5 A schematic diagram of a spaceborne single-channel optoelectronic slip ring radio frequency signal transmission method according to an embodiment of the present invention is shown;

[0054] Figure 6 A schematic diagram of a CAN bus connection according to an embodiment of the present invention is shown; and

[0055] Figure 7 A schematic diagram of an on-orbit fault diagnosis and health management system based on a spaceborne optoelectronic slip ring, according to an embodiment of the present invention, is shown. Detailed Implementation

[0056] In the following description, the invention is described with reference to various embodiments. However, those skilled in the art will recognize that the embodiments may be practiced without one or more specific details or with other alternatives and / or additional methods or components. In other instances, well-known structures or operations are not shown or described in detail so as not to obscure the inventive points of the invention. Similarly, for illustrative purposes, specific numbers and configurations are set forth to provide a comprehensive understanding of embodiments of the invention. However, the invention is not limited to these specific details.

[0057] In this specification, references to "an embodiment" or "this embodiment" mean that a particular feature, structure, or characteristic described in connection with that embodiment is included in at least one embodiment of the invention. The phrase "in one embodiment" appearing throughout this specification does not necessarily refer to the same embodiment in all instances.

[0058] In this specification, unless otherwise specified, "arranged on," "arranged above," and "arranged on top of" do not exclude the possibility of an intermediate element between them. Furthermore, "arranged on or above" merely indicates the relative positional relationship between two components, and in certain cases, such as when the product orientation is reversed, it can also be converted to "arranged below or under," and vice versa.

[0059] It should be noted that the embodiments of the present invention describe the method steps in a specific order; however, this is only for illustrating the specific embodiment and not for limiting the order of the steps. On the contrary, in different embodiments of the present invention, the order of the steps can be adjusted according to actual needs.

[0060] This invention addresses the needs of satellites with rotating cabins that simultaneously support ground control, data transmission, and payload antennas. These cabins require the transmission of radio frequency (RF) signals, digital signals, and power supply. The invention addresses the multi-channel RF signal transmission requirements of the rotating components, the problem of cable entanglement during digital signal transmission via wires through the rotating cabin, and the potential transmission errors and wear-out issues associated with traditional slip rings. It proposes a photoelectric conversion system using a turntable-driven smooth ring and an electric slip ring. The electric slip ring solves the problem of high-speed electrical signal transmission within the rotating cabin, while the smooth ring simultaneously enables the transmission of digital, optical, and RF signals during rotation. Furthermore, the invention addresses several reliability and health management issues related to the on-orbit application of RF signals, data transmission signals, and payload signals, including:

[0061] 1. The photoelectric conversion system includes an electric slip ring, a smooth ring, a baseline conversion module, and a platform conversion module. The baseline conversion module is located on one side of the rotating cabin, and the platform conversion module is located on one side of the platform cabin. The status monitoring data and control data of the baseline conversion module need to be transmitted to the satellite platform cabin through the smooth ring. However, the health status of the smooth ring path is affected by the health status of the modules at both ends, which presents a coupling safety issue.

[0062] 2. Design and management issues of the CAN bus between the satellite rotating cabin and the satellite platform cabin.

[0063] 3. In the on-orbit application environment of smooth rings, the satellite power supply system (solar panels, battery packs) and the on-board integrated processing computer (integrated electronics) are usually located at the non-rotating end of the satellite. The health status monitoring of each unit in the rotating module and the power supply safety of the photoelectric conversion system are coupled.

[0064] This invention proposes an on-orbit fault diagnosis and health management system based on a spaceborne optoelectronic slip ring. It can be applied to the reliability of digital signals, radio frequency signals, and power supply between the satellite platform module and the satellite rotating module, improving the fault-free time for reliable and stable operation of the optoelectronic conversion system. It is mainly used to solve the application status monitoring of bus remote control, bus telemetry data, and satellite-to-ground radio frequency signal transmission between the two modules when electric slip rings and smooth slip rings are used between the satellite platform module and the satellite rotating module, as well as the health monitoring of the optoelectronic conversion system itself and the safety monitoring of power supply. It can realize autonomous management and recovery of on-orbit faults.

[0065] Figure 1 A flowchart illustrating an embodiment of the present invention, namely, an on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring, is shown below. Figure 1This invention describes the on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring. In one embodiment, the on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring can be executed by a computer. Figure 1 As shown, the on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip rings includes the following steps:

[0066] First, a photoelectric conversion system is constructed, which includes a photoelectric slip ring, a baseline conversion module, and a platform conversion module. The baseline conversion module is located in the satellite rotation cabin, and the platform conversion module is located in the satellite platform cabin.

[0067] Figure 2 A schematic diagram of the compartmentalized design of a photoelectric conversion system according to an embodiment of the present invention is shown. Figure 2 As shown, the satellite rotating cabin 1, also known as the satellite payload cabin, rotates at an angular velocity ω. The satellite rotating cabin 1 is connected to the turntable 2, while the satellite platform cabin 3 remains stationary.

[0068] Figure 3 A schematic diagram of a photoelectric conversion system according to an embodiment of the present invention is shown. Figure 3 As shown, the satellite rotating cabin radio frequency signal transmission system based on an optoelectronic slip ring includes a baseline conversion module 10, an optoelectronic slip ring 20, and a platform conversion module 30. The baseline conversion module 10 is located in the satellite rotating cabin 1. In one embodiment of the invention, the baseline conversion module 10 is used to convert radio frequency signals into optical signals or optical signals into radio frequency signals, or to convert digital signals and optical signals into coupled optical signals or to convert coupled optical signals into digital signals and optical signals. The optoelectronic slip ring 20 is located in the turntable 2. The optoelectronic slip ring 20 includes a smooth ring and an electric slip ring. The optoelectronic slip ring 20 is driven to rotate by the turntable 2 and is used for non-contact transmission of optical signals or radio frequency signals. The platform conversion module 30 is located in the satellite platform cabin 3. In one embodiment of the invention, the platform conversion module 30 is used to convert radio frequency signals into optical signals or optical signals into radio frequency signals, or to convert digital signals and optical signals into coupled optical signals or to convert coupled optical signals into digital signals and optical signals. In one embodiment of the present invention, the radio frequency signal includes one or more of the following: telemetry and control radio frequency signal, data transmission radio frequency signal, incidental radio frequency signal, or payload radio frequency signal. In one embodiment of the present invention, the digital signal includes one or more of the following: CAN signal, RS422 signal, or LVDS signal; and / or the optical signal includes one or more of the following: satellite rotation cabin optical signal or satellite platform cabin optical signal.

[0069] Figure 4 A schematic diagram of a photoelectric slip ring structure according to an embodiment of the present invention is shown. Figure 4As shown, the smooth ring 201 and the electric slip ring 202 are connected in series. The smooth ring 201 includes a smooth ring stator 205 and a smooth ring rotor 204; the electric slip ring 202 includes an electric slip ring stator 207 and an electric slip ring rotor 208. The smooth ring rotor 204 and the electric slip ring rotor 208 transmit driving torque through a two-stage shift fork mechanism. The turntable stator 203 is connected to the smooth ring stator 205 and the electric slip ring stator 207. The turntable shift lever, i.e., the first-stage shift fork mechanism 209, is driven by the motor output shaft 210. The first-stage shift fork mechanism 209 then drives the electric slip ring 202 to rotate, and the electric slip ring shift lever, i.e., the second-stage shift fork mechanism 206, then drives the smooth ring 201 to rotate. The angular velocity of the motor output shaft 210 is ω. The installation steps for the smooth ring 201 and the electric slip ring 202 are as follows: First, install the electric slip ring rotor 208 and the smooth ring rotor 204 through a shift fork mechanism, adjusting the coaxiality and perpendicularity of the installation to achieve synchronous rotation of the two slip rings; then, install the turntable stator 203 with the smooth ring stator 205 and the electric slip ring stator 207, adjusting the coaxiality and perpendicularity of the slip ring and the turntable installation, connecting the turntable motor rotor end to the photoelectric slip ring rotor end, driving the electric slip ring to rotate by the turntable shift fork, and then achieving synchronous drive of the smooth ring by the electric slip ring shift fork; the shift fork mechanism adopts a clearance fit, and the requirements for shaft system installation accuracy are not high. The smooth ring rotor 204 is connected to the baseline conversion module 10, and the smooth ring stator 205 is connected to the platform conversion module 30, thereby realizing the interconnection of the external signal channels of the smooth ring 201.

[0070] In one embodiment of the present invention, the platform conversion module 30 is connected to the power supply interface and remote control / telemetry signal of the corresponding unit in the satellite platform cabin 3, and the baseline conversion module 10 is connected to the power supply interface and remote control / telemetry signal of the corresponding unit in the satellite rotating cabin 1. The signal transmission mechanism is as follows: data is sent through the corresponding unit in the satellite rotating cabin 1, and the corresponding unit in the satellite platform cabin 3 tests the correctness of the received data; or data is sent through the corresponding unit in the satellite platform cabin 3, and the corresponding unit in the satellite rotating cabin 1 tests the correctness of the received data.

[0071] Taking the transmission of onboard radio frequency signals in rotation mode using a smooth ring as an example, this illustrates the transmission of signals between the platform conversion module and the baseline conversion module. Figure 5 A schematic diagram of a spaceborne single-channel optoelectronic slip ring radio frequency signal transmission method according to an embodiment of the present invention is shown. Figure 5As shown, the transmission method includes: converting multiple input radio frequency (RF) signals into multiple optical signals, and inputting the multiple optical signals into an optical transmitting wavelength division multiplexer (OTDM). The input RF signals are output by a random antenna, an S-antenna, a telemetry and control antenna, or a data transmission phased array. The RF signals are converted into optical signals after passing through an electro-optical converter, and transmitted through the optical cable inside the RF-to-optical transmitting module. After passing through the wavelength division multiplexer, the multiple RF signals are converted into one or more optical signals of different wavelengths. The optical transmitting wavelength division multiplexer couples the input optical signals into the same optical fiber and inputs the coupled optical signals into an optoelectronic slip ring 20. The optoelectronic slip ring 20 is driven to rotate continuously by a turntable 2. The optoelectronic slip ring transmits the optical signals to an optical receiving wavelength division multiplexer (ORM). The optical receiving wavelength division multiplexer recovers the coupled optical signals output by the optoelectronic slip ring into multiple optical signals and inputs the recovered multiple optical signals into an optical-to-RF receiving module. The optical-to-RF receiving module converts the recovered multiple optical signals into multiple recovered RF signals and outputs them.

[0072] like Figure 5 As shown, the baseline conversion module 10 includes a first electro-optic converter 114 for electro-optic conversion, a first photoelectric converter 116 for photoelectric conversion, and a first optical transmission wavelength division multiplexer 111 and a second optical transmission wavelength division multiplexer 112; the optical receiving wavelength division multiplexer includes a first optical receiving wavelength division multiplexer 311 and a second optical transmission wavelength division multiplexer 312; the optical-to-RF receiving module includes a second photoelectric converter 314 for photoelectric conversion and a first electro-optic converter 317 for electro-optic conversion.

[0073] Next, the platform integrated electronics and load management unit is used to perform status monitoring on the platform conversion module and the baseline conversion module, respectively.

[0074] Because the information flow between the satellite platform module and the satellite rotating module is transmitted through an electrical slip ring and the platform conversion module and baseline conversion module, under normal circumstances, the satellite-to-ground telemetry and control uplink signal passes through the slip ring to achieve telemetry and control of the satellite. When the optoelectronic slip ring system malfunctions, the traditional satellite-to-ground uplink telemetry and control channel cannot achieve telemetry and control of the satellite, and the satellite cannot perform routine daily maintenance and payload tasks. Therefore, it is necessary to enable the platform conversion module and baseline conversion module of the optoelectronic slip ring to achieve autonomous detection and recovery of routine faults. The platform integrated electronics and payload management unit are used to monitor the status of the platform conversion module and baseline conversion module, mainly including power supply status monitoring and communication status (i.e., reset monitoring).

[0075] Power supply status monitoring refers to the real-time monitoring of the secondary power supply voltage of the platform conversion module and the baseline conversion module. When the voltage value exceeds the preset threshold range and the duration exceeds the set time, a primary / backup power supply switching command is triggered. The secondary power supply status monitoring identifier can be set to EHF-GD-JX-2-1.00. The platform integrated electronics and load management unit autonomously monitors the secondary power supply status of the platform conversion module and the baseline conversion module respectively. By default, monitoring is enabled. When monitoring is "disabled", no autonomous monitoring is performed until a "Platform secondary power supply monitoring status enabled" or "Baseline secondary power supply monitoring status enabled" command is received, at which point the "Baseline secondary power supply monitoring status" is set to "enabled".

[0076] The platform integrated electronics and payload management unit are responsible for the individual unit monitoring and management of the satellite platform module and the satellite payload module (i.e., the satellite rotation module), respectively. The platform integrated electronics acts as the primary overall control, and the payload management unit acts as the secondary overall control. The payload management unit is responsible for reporting the status of all individual units in the satellite payload module to the satellite platform module once per second. If there is a problem with the information exchange between the two, the satellite maintenance personnel will handle the fault in the payload management unit or the photoelectric conversion system. When the payload management unit detects a baseline fault, it will handle the baseline fault. If, within several times the time after the payload management unit has completed its handling, the satellite maintenance personnel determine that they have not received telemetry data from all individual units in the satellite payload module, they consider the fault not to have been eliminated, and the payload management unit will perform a reset operation and manually power on to restart.

[0077] Taking the baseline conversion module as an example, the specific operation process for exception handling is explained:

[0078] Real-time monitoring of the +5V and -5V main power supply voltages of the baseline conversion module;

[0079] The preset threshold range includes a first preset threshold range and a second preset threshold range. The first preset threshold range is a +5V main power supply voltage that is telemetry measured to be no lower than 2.2V (directly sampled by the load management unit, configurable) and no higher than 3.2V (directly sampled by the load management unit, configurable). The second preset threshold range is a -5V main power supply voltage that is telemetry measured to be no lower than 1.4V (directly sampled by the load management unit, configurable) and no higher than 2.2V (directly sampled by the load management unit, configurable).

[0080] When the voltage value exceeds the first preset threshold range and the duration exceeds the set duration, this condition can be set as the first criterion; when the voltage value exceeds the second preset threshold range and the duration exceeds the set duration, this condition can be set as the second criterion. The set duration is 5 seconds. When either the first or second criterion is met, the load management unit continuously sends three commands to shut down the main power supply and turn on the backup power supply of the baseline conversion module, with a 5-second interval between commands. After sending these three commands, the "Baseline Secondary Power Supply Monitoring Status" is set to "Disabled". It should be noted that the voltage values ​​and set duration values ​​in the first and second criters are based on the device manufacturer and product usage constraints. The voltage range and set duration in the criters can be adjusted according to product characteristics.

[0081] When the platform integrated electronics and load management unit is reset, the secondary power supply monitoring status and configuration parameters of the platform conversion module and baseline conversion module are saved. The platform integrated electronics and load management unit reset identifier can be set to EHF-GD-JX-3-1.00.

[0082] The abnormal handling of a reset is illustrated using the baseline conversion module. When the load management unit resets, the "Baseline Secondary Power Supply Monitoring Status" remains in the state before the reset, and the corresponding monitoring status configuration parameters "Baseline Secondary Power Supply +5V Monitoring Voltage Configuration Parameter 1", "Baseline Secondary Power Supply +5V Monitoring Voltage Configuration Parameter 2", "Baseline Secondary Power Supply +5V Monitoring Time Configuration Parameter", "Baseline Secondary Power Supply -5V Monitoring Voltage Configuration Parameter 1", "Baseline Secondary Power Supply -5V Monitoring Voltage Configuration Parameter 2", and "Baseline Secondary Power Supply -5V Monitoring Time Configuration Parameter" remain unchanged.

[0083] In one embodiment of the present invention, when the platform integrated electronics and load management unit is reset, the secondary power supply monitoring status of the platform conversion module and the baseline conversion module is saved as the state before the reset; the configuration parameters are the configuration parameters of the +5V main power supply voltage and the -5V main power supply voltage of the platform conversion module and the baseline conversion module.

[0084] Next, status monitoring and safety management will be performed on the CAN bus between the satellite rotating cabin and the satellite platform cabin.

[0085] Figure 6 A schematic diagram of a CAN bus connection according to an embodiment of the present invention is shown. The CAN bus between the satellite payload compartment and the satellite platform compartment is a key channel for the integrated electronic control of individual units and the acquisition of individual unit telemetry status, which is the foundation for the normal execution of ground missions by the satellite. The satellite payload compartment and the satellite platform compartment adopt a dual-bus handshake mechanism, and data forwarding is realized through the platform conversion module and the baseline conversion module. Therefore, the health status of the modules will affect the health status judgment of the individual units in the satellite payload compartment.

[0086] The platform's integrated electronics and payload management unit monitors the status of the CAN bus between the satellite's rotating module and platform module via a dual-bus handshake mechanism. The monitoring identifier can be set to EHF-GD-JX-1-1.00. Taking the payload management unit sending a switch command to the baseline conversion module as an example, the abnormal handling of the CAN bus is explained.

[0087] When the load management unit does not receive the platform's integrated electronic CAN telemetry request signal for 10 consecutive seconds, it will reset the CAN bus chip according to the CAN protocol.

[0088] If the load management unit does not receive a telemetry request signal from the platform's integrated electronic CAN for 45 consecutive seconds, it sends a reset enable signal to the baseline conversion module FPGA, updates the relevant telemetry, and records the telemetry. If the problem is still not resolved, the process is repeated.

[0089] It should be noted that the timeframes (10 seconds, 45 seconds) here take into account tiered control, handling cases from mild to severe. If there is no CAN bus telemetry between the two modules, the CAN bus chip is reset first. If this is attempted more than three times within 45 seconds, and if recovery is still not achieved, the data transmission node (baseline) between the two modules is then addressed, and its FPGA is reset. It should be noted that the on-orbit reliability of the CAN bus between the two modules is very high, ensuring reliable CAN bus communication. A CAN bus failure will cause other subsystems to be unable to perform downlink telemetry, and individual units will be unable to respond to the spacecraft's CAN commands. However, there is no safety risk; the spacecraft can receive commands normally and autonomously reset the CAN bus interface chip and initialize the interface chip of each node based on the telemetry assessment of each individual unit, demonstrating high reliability.

[0090] Finally, independent power distribution is performed on the platform conversion module and the baseline conversion module, and power is autonomously controlled to be added or cut off based on health criteria.

[0091] Power is supplied to the satellite's rotating module via electric slip rings. Conductive slip ring power supply has been proven and maturely implemented in orbit, and power supply and distribution for individual payload modules can be achieved through a power controller. For the baseline conversion module, since its power supply reliability affects channel signal transmission, independent power distribution is used. The platform's integrated electronics system autonomously controls the power on / off of both the platform conversion module and the baseline conversion module based on the aforementioned criteria.

[0092] This invention proposes an on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring. It presents an optoelectronic conversion system that transmits high-speed electrical signals from the satellite's rotating module via an electric slip ring, and transmits on-orbit digital, optical, and radio frequency signals via a smooth slip ring, reducing signal entanglement and bit error issues. A dynamic threshold is designed for the secondary power supply (+5V / -5V), enabling seamless switching between primary and backup power supplies. By combining dual-bus handshake and FPGA reset strategies, the delay and bit error issues in CAN bus communication between the satellite's rotating module and platform module are resolved. Key parameters are stored in non-volatile memory, ensuring automatic configuration recovery after reset. The optoelectronic conversion system uses independent power distribution to prevent power supply anomalies from spreading to other payload units. The on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring proposed in this invention is independent of the satellite model and can be adapted to different satellite types.

[0093] In one embodiment of the present invention, the present invention also provides a system for the aforementioned on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring, such as... Figure 7 As shown, the system includes:

[0094] A photoelectric conversion system construction module is configured to construct a photoelectric conversion system, which includes a photoelectric slip ring, a baseline conversion module, and a platform conversion module. The baseline conversion module is located in the satellite rotation cabin, and the platform conversion module is located in the satellite platform cabin.

[0095] The status monitoring module is configured to use the platform integrated electronics and load management unit to perform status monitoring on the platform conversion module and the baseline conversion module, respectively.

[0096] The CAN bus management module is configured to perform status monitoring and security management of the CAN bus between the satellite rotating cabin and the satellite platform cabin; and

[0097] The power supply management module is configured to perform independent power distribution to the platform conversion module and the baseline conversion module, and to autonomously control power on / off based on health criteria.

[0098] In one embodiment of the present invention, an electronic device is also provided, comprising: a processor, a graphics card with an artificial intelligence chip, and a memory. The memory is configured to store machine-readable instructions, the graphics card is configured to train the on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring, and the processor is configured to execute the machine-readable instructions. When the processor and / or the graphics card executes the machine-readable instructions, the following processing steps are implemented: constructing an optoelectronic conversion system, the optoelectronic conversion system including an optoelectronic slip ring, a baseline conversion module, and a platform conversion module, the baseline conversion module being located in the satellite rotation cabin, and the platform conversion module being located in the satellite platform cabin; using a platform integrated electronics and payload management unit to perform status monitoring on the platform conversion module and the baseline conversion module respectively; performing status monitoring and safety management on the CAN bus between the satellite rotation cabin and the satellite platform cabin; and performing independent power distribution on the platform conversion module and the baseline conversion module, and autonomously controlling power on / off according to health criteria.

[0099] The graphics card used can preferably be a model with a GPU computing power higher than 5.0. Since the amount of data to be trained is large, providing a graphics card configuration can significantly improve the training speed.

[0100] The memory includes various media capable of storing machine-readable instructions, such as USB flash drives, read-only memory (ROM), random access memory (RAM), portable hard drives, magnetic disks, or optical disks.

[0101] It is understood that, in addition to the memory and processor mentioned above, the computer system described above also includes other hardware and software components not listed in this specification. The specific components can be determined according to the model of the specific data processing equipment in different application scenarios, and will not be listed and described in detail in this specification.

[0102] In one embodiment of the present invention, a computer-readable storage medium is also provided, on which machine-readable instructions are stored. When executed by a processor, the machine-readable instructions perform the following processing steps: constructing a photoelectric conversion system, the photoelectric conversion system including a photoelectric slip ring, a baseline conversion module, and a platform conversion module, the baseline conversion module being located in a satellite rotation cabin, and the platform conversion module being located in a satellite platform cabin; using a platform integrated electronics and payload management unit to perform status monitoring on the platform conversion module and the baseline conversion module respectively; performing status monitoring and safety management on the CAN bus between the satellite rotation cabin and the satellite platform cabin; and performing independent power distribution on the platform conversion module and the baseline conversion module, and autonomously controlling power on / off according to health criteria.

[0103] Although various embodiments of the present invention have been described above, it should be understood that they are presented by way of example only and not as limitations. It will be apparent to those skilled in the art that various combinations, modifications, and alterations can be made without departing from the spirit and scope of the invention. Therefore, the breadth and scope of the invention disclosed herein should not be limited by the exemplary embodiments disclosed above, but should be defined according to the technical solutions of the invention and their equivalents.

Claims

1. A method for on-orbit fault diagnosis and health management based on a spaceborne optoelectronic slip ring, characterized in that, Includes the following steps: A photoelectric conversion system is constructed, which includes a photoelectric slip ring, a baseline conversion module, and a platform conversion module. The baseline conversion module is located in the satellite rotation cabin, and the platform conversion module is located in the satellite platform cabin. The platform integrated electronics and payload management unit is used to perform status monitoring on the platform conversion module and the baseline conversion module, respectively, including the following steps: The secondary power supply voltages of the platform conversion module and the baseline conversion module are monitored in real time. When the voltage value exceeds the preset threshold range and the duration exceeds the set time, a main / backup power supply switching command is triggered. as well as When the platform integrated electronics and load management unit is reset, the secondary power supply monitoring status and configuration parameters of the platform conversion module and the baseline conversion module are saved. The CAN bus between the satellite rotating cabin and the satellite platform cabin is subject to status monitoring and safety management. as well as Independent power distribution is implemented for the platform conversion module and the baseline conversion module, and power is autonomously controlled to be applied or removed based on health criteria; The photoelectric slip ring is located in the turntable, and the photoelectric slip ring includes a smooth ring and an electric slip ring; the smooth ring and the electric slip ring are connected in series. The baseline conversion module and the platform conversion module are used to convert radio frequency signals into optical signals, optical signals into radio frequency signals, digital signals and optical signals into coupled optical signals, or coupled optical signals into digital signals and optical signals; the photoelectric slip ring is used for non-contact transmission of optical signals or radio frequency signals.

2. The on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip rings according to claim 1, characterized in that, The secondary power supply voltages of the platform conversion module and the baseline conversion module are monitored in real time. When the voltage value exceeds a preset threshold range and the duration exceeds a set time, a main / backup power switching command is triggered, including: The +5V main power supply voltage and -5V main power supply voltage of the platform conversion module and the baseline conversion module are monitored in real time. The preset threshold range includes a first preset threshold range and a second preset threshold range. The first preset threshold range is a +5V main power supply voltage of not less than 2.2V and not more than 3.2V, and the second preset threshold range is a -5V main power supply voltage of not less than 1.4V and not more than 2.2V. The set duration is 5 seconds; When the voltage value exceeds the first preset threshold range or the second preset threshold range, and the duration exceeds the set duration, the load management unit sends an instruction to shut down the main power supply and turn on the backup power supply.

3. The on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip rings according to claim 1, characterized in that, When the platform integrated electronics and load management unit is reset, the secondary power supply monitoring status and configuration parameters of the platform conversion module and the baseline conversion module are saved, including: When the platform integrated electronics and load management unit is reset, the secondary power supply monitoring status of the platform conversion module and the baseline conversion module is saved as the state before the reset. The configuration parameters are the configuration parameters of the +5V main power supply voltage and the -5V main power supply voltage of the platform conversion module and the baseline conversion module.

4. The on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip rings according to claim 1, characterized in that, The status monitoring and safety management of the CAN bus between the satellite rotating cabin and the satellite platform cabin includes: The platform's integrated electronics and payload management unit monitors the status of the CAN bus between the satellite rotating cabin and the satellite platform cabin through a dual-bus handshake mechanism. When the load management unit does not receive a CAN telemetry request signal from the platform's integrated electronic CAN for 10 consecutive seconds, it will reset the CAN bus chip. If the load management unit does not receive a CAN telemetry request signal from the platform integrated electronics for 45 consecutive seconds, the platform integrated electronics and the load management unit will respectively perform a reset on the platform conversion module and the baseline conversion module FPGA.

5. The on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip rings according to claim 1, characterized in that, Independent power distribution is performed on the platform conversion module and the baseline conversion module, and the autonomous control of power on / off based on health criteria includes: The satellite's rotating cabin is powered via an electric slip ring; the platform's integrated electronics autonomously manage the power-on and power-off of the platform conversion module and the baseline conversion module based on health criteria.

6. The on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip rings according to claim 1, characterized in that, The smooth ring includes a smooth ring stator and a smooth ring rotor; the electric slip ring includes an electric slip ring stator and an electric slip ring rotor; The smooth ring rotor and the electric slip ring rotor are connected via a shift fork mechanism. The turntable stator is connected to both the smooth ring stator and the electric slip ring stator. The electric slip ring is driven to rotate by a turntable shift lever, and the smooth ring is driven to rotate by an electric slip ring shift lever. The smooth ring rotor is connected to the baseline conversion module, and the smooth ring stator is connected to the platform conversion module.

7. The on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip rings according to claim 1, characterized in that, The platform conversion module is connected to the corresponding single-unit power supply interface and remote control and telemetry signals of the satellite platform cabin, and the baseline conversion module is connected to the corresponding single-unit power supply interface and remote control and telemetry signals of the satellite rotating cabin.

8. A system for the on-orbit fault diagnosis and health management method based on spaceborne optoelectronic slip rings as described in any one of claims 1-7, characterized in that, include: A photoelectric conversion system construction module is configured to construct a photoelectric conversion system, which includes a photoelectric slip ring, a baseline conversion module, and a platform conversion module. The baseline conversion module is located in the satellite rotation cabin, and the platform conversion module is located in the satellite platform cabin. The status monitoring module is configured to use the platform integrated electronics and load management unit to perform status monitoring on the platform conversion module and the baseline conversion module, respectively. The CAN bus management module is configured to perform status monitoring and safety management of the CAN bus between the satellite rotating cabin and the satellite platform cabin. as well as The power supply management module is configured to perform independent power distribution to the platform conversion module and the baseline conversion module, and to autonomously control power on / off based on health criteria. The photoelectric slip ring is located in the turntable, and the photoelectric slip ring includes a smooth ring and an electric slip ring; the smooth ring and the electric slip ring are connected in series. The baseline conversion module and the platform conversion module are used to convert radio frequency signals into optical signals, optical signals into radio frequency signals, digital signals and optical signals into coupled optical signals, or coupled optical signals into digital signals and optical signals; the photoelectric slip ring is used for non-contact transmission of optical signals or radio frequency signals.

9. An electronic device, characterized in that, include: A processor, configured to execute machine-readable instructions; A graphics card equipped with an artificial intelligence chip is configured to train an on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring; and A memory configured to store machine-readable instructions that, when executed by a processor and / or a graphics card, perform the steps of the method according to any one of claims 1-7.

10. A computer-readable storage medium, characterized in that, It stores machine-readable instructions that, when executed by a processor, perform the steps of the method according to any one of claims 1-7.

Images