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

Abstract

The invention relates to an on-orbit fault diagnosis and health management method and system based on a satellite-borne photoelectric slip ring. The method comprises the steps that a photoelectric conversion system is constructed, 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; performing state monitoring on the platform conversion module and the baseline conversion module by using a platform integrated electronic and load management unit; state monitoring and safety management are carried out on a CAN bus between the satellite rotating cabin and the satellite platform cabin; and executing independent power distribution on the platform conversion module and the baseline conversion module, and autonomously controlling power-on and power-off according to a health criterion. According to the method provided by the invention, the dynamic threshold is designed for the secondary power supply, and seamless switching of the main power supply and the standby power supply is realized; the problems of delay and error codes of CAN bus communication between a satellite rotating cabin and a satellite platform cabin are solved by combining strategies such as double-bus handshake and FPGA reset.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite autonomous health management, and particularly to an on-orbit fault diagnosis and health management method and system based on an on-board optoelectronic slip ring. Background Art

[0002] Currently, there are a large number of on-orbit spacecrafts, which have developed from satellites without scientific instrument equipment at the beginning to space stations, deep space landers, etc. with complex functions. To adapt to complex scenarios or complete specific tasks, the mechanical mechanisms of spacecrafts need to rotate relatively. To ensure data transmission between relatively rotating spacecraft devices, a conductive slip ring is required to establish an electrical path for data transmission between the relatively moving devices.

[0003] Currently, products such as conductive slip rings are usually used for power supply and digital signal transmission in the rotating state of on-board rotating mechanisms. The electrical signal contact transmission is mainly achieved through the brush wire contact of the electrical slip ring. The signal stability during the transmission process is affected by the dynamic contact resistance of the conductive slip ring, and situations such as transmission error codes are likely to occur. The signal transmission and signal level conversion of common CAN bus, 422 bus, LVDS, optical signal, etc. are relatively mature in the application of ground rotating mechanism equipment. In the space application of satellites and other aircrafts, due to the influence of the life wear of the rotating mechanism and the signal transmission reliability, etc., the data volume and data rate transmitted between the rotating components of the traditional conductive slip ring and the fixed platform are limited. Currently, during the data transmission process between on-board satellite rotating cabins, there is a lack of means for monitoring the application status and health management of the power supply state and digital signal transmission, and the on-orbit maintenance means are poor.

[0004] During the rotation state, radio frequency signal transmission usually uses products such as smooth rings and radio frequency rotary joints. Currently, on-board radio frequency channels are mainly used for TT&C, data transmission, navigation and positioning, payloads, etc., and have high requirements for reliability. For the radio frequency transmission between on-board satellite rotating cabins, the on-orbit application of smooth rings has been realized, which has the characteristics of large data transmission volume and small insertion loss. On-board radio frequency signals usually interact mainly with space-ground and inter-satellite signals, and are usually closely related to the task application requirements of users, TT&C and operation control systems, etc. Therefore, the health management of smooth ring radio frequency signal transmission is particularly important.

[0005] Currently, in the field of on-board radio frequency signal transmission technology, it mainly includes products such as waveguide rotary joints and coaxial rotary joints, mainly focusing on the radio frequency signal transmission performance, and the digital signal transmission is mainly based on conductive slip ring contact transmission. There are certain limitations in the health management of the radio frequency signal transmission performance and the health status of the link transmission. With the characteristics of large transmission bandwidth, small insertion loss and small wear of the smooth ring, it has been successfully applied on orbit, but there are still many limitations in the on-orbit application reliability and safety of the smooth ring, especially in aspects such as health management. Summary of the Invention

[0006] In view of some or all of the problems in the prior art, the present invention provides an on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring, and the method includes the following steps:

[0007] Construct an optoelectronic conversion system, where the optoelectronic conversion system includes an optoelectronic slip ring, a baseline conversion module, and a platform conversion module. The baseline conversion module is located in the satellite rotating cabin, and the platform conversion module is located in the satellite platform cabin;

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

[0009] Real-time monitor 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, trigger the main and standby power supply switching instruction; and

[0010] When the platform integrated electronics and payload management unit is reset, save the secondary power supply monitoring status and configuration parameters of the platform conversion module and the baseline conversion module;

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

[0012] Perform independent power distribution on the platform conversion module and the baseline conversion module, and independently control power on and off according to the health criterion.

[0013] Further, real-time monitor 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, triggering the main and standby power supply switching instruction includes:

[0014] Real-time monitor the +5V main power supply voltage and -5V main power supply voltage of the platform conversion module and the baseline conversion module;

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

[0016] The set time is 5s;

[0017] When the voltage value exceeds the first preset threshold range or the second preset threshold range, and the duration exceeds the set time, the payload management unit sends an instruction to turn off the main power supply and turn on the standby power supply.

[0018] Further, it is characterized in that when the platform integrated electronics and payload management unit is reset, saving 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 payload management unit is reset, the secondary power supply monitoring status of the platform conversion module and the baseline conversion module is saved as the status before 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] Further, performing status monitoring and safety management on the CAN bus between the satellite rotating cabin and the satellite platform cabin includes:

[0022] The platform integrated electronics and payload management unit performs status monitoring on the CAN bus between the satellite rotating cabin and the satellite platform cabin through a dual-bus handshake mechanism;

[0023] When the payload management unit does not receive the platform integrated electronics CAN telemetry request signal for 10 consecutive seconds, reset the CAN bus chip;

[0024] When the payload management unit does not receive the platform integrated electronics CAN telemetry request signal for 45 consecutive seconds, the platform integrated electronics and payload management unit respectively reset the FPGAs of the platform conversion module and the baseline conversion module.

[0025] Further, performing independent power distribution on the platform conversion module and the baseline conversion module and autonomously controlling power on and off according to health criteria includes:

[0026] Power the satellite rotating cabin through an electrical slip ring; the platform integrated electronics performs autonomous power on and off management on the platform conversion module and the baseline conversion module according to health criteria.

[0027] Further, the optoelectronic slip ring is located in the turntable, and the optoelectronic slip ring includes a smooth ring and an electrical slip ring;

[0028] The smooth ring and the electrical slip ring are connected in series; the smooth ring includes a smooth ring stator and a smooth ring rotor; the electrical slip ring includes an electrical slip ring stator and an electrical slip ring rotor;

[0029] The smooth ring rotor and the electrical slip ring rotor are connected through a fork mechanism, the turntable stator is connected to the smooth ring stator and the electrical slip ring stator, the electrical slip ring is driven to rotate by the turntable lever, and then the smooth ring is driven to rotate by the electrical slip ring lever; and

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

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

[0033] An optoelectronic conversion system construction module, configured to construct 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 rotating cabin, and the platform conversion module being located in the satellite platform cabin;

[0034] A status monitoring module, configured to perform status monitoring on the platform conversion module and the baseline conversion module respectively using the platform integrated electronics and the payload management unit;

[0035] A CAN bus management module, configured to perform status monitoring and safety management on the CAN bus between the satellite rotating cabin and the satellite platform cabin; and

[0036] A power supply management module, configured to perform independent power distribution on the platform conversion module and the baseline conversion module, and autonomously control power-on and power-off according to the health criterion.

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

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

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

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

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

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

[0043] 1. The on-orbit fault diagnosis and health management method based on the spaceborne optoelectronic slip ring proposed by the present invention proposes an optoelectronic conversion system. The high-speed electrical signals of the satellite's rotating cabin are transmitted through the electrical slip ring, and the spaceborne digital signals, optical signals, and radio frequency signals are transmitted through the smooth ring, reducing signal entanglement and error code problems.

[0044] 2. The on-orbit fault diagnosis and health management method based on the spaceborne optoelectronic slip ring proposed by the present invention designs dynamic thresholds for the secondary power supply (+5V / -5V), achieving seamless switching between the main and backup power supplies.

[0045] 3. The on-orbit fault diagnosis and health management method based on the spaceborne optoelectronic slip ring proposed by the present invention combines strategies such as dual-bus handshake and FPGA reset to solve the problems of delay and error code in the CAN bus communication between the satellite's rotating cabin and the satellite platform cabin.

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

[0047] 5. The on-orbit fault diagnosis and health management method based on the spaceborne optoelectronic slip ring proposed by the present invention adopts independent power distribution for the optoelectronic conversion system to avoid the spread of abnormal power supply to other payload single units. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] To further clarify the above and other advantages and features of the embodiments of the present invention, a more specific description of the embodiments of the present invention will be presented with reference to the accompanying drawings. It can be understood that these drawings only depict typical embodiments of the present invention and will not be considered as limiting its scope. In the drawings, for clarity, the same or corresponding components will be denoted by the same or similar reference numerals.

[0049] Figure 1 Shows a schematic flow chart of the on-orbit fault diagnosis and health management method based on the spaceborne optoelectronic slip ring according to an embodiment of the present invention;

[0050] Figure 2 Shows a schematic diagram of the compartment design of the optoelectronic conversion system according to an embodiment of the present invention;

[0051] Figure 3 Shows a schematic diagram of the structure of the optoelectronic conversion system according to an embodiment of the present invention;

[0052] Figure 4 Shows a schematic diagram of the structure of the optoelectronic slip ring according to an embodiment of the present invention;

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

[0054] Figure 6 Shows a schematic diagram of the CAN bus connection of an embodiment of the present invention; and

[0055] Figure 7 Shows a schematic diagram of an on-orbit fault diagnosis and health management system based on a spaceborne optoelectronic slip ring of an embodiment of the present invention. Detailed implementation manners

[0056] In the following description, the present invention is described with reference to various embodiments. However, those skilled in the art will recognize that the embodiments can be implemented without one or more specific details or in combination with other alternative and / or additional methods or components. In other cases, well-known structures or operations are not shown or described in detail to avoid obscuring the inventive points of the present invention. Similarly, for purposes of explanation, specific numbers and configurations are set forth in order to provide a thorough understanding of the embodiments of the present invention. However, the present invention is not limited to these specific details.

[0057] In this specification, the reference to "an embodiment" or "the embodiment" means that the specific features, structures, or characteristics described in connection with the embodiment are included in at least one embodiment of the present invention. The phrase "in an embodiment" appearing throughout this specification does not necessarily all refer to the same embodiment.

[0058] In this specification, unless otherwise specified, "arranged on", "arranged above", and "arranged thereon" do not exclude the situation where there is an intermediate object between the two. In addition, "arranged on or above" only represents the relative positional relationship between two components, and in certain cases, such as after reversing the product direction, it can also be converted to "arranged under or below", and vice versa.

[0059] It should be noted that the embodiments of the present invention describe the method steps in a specific order, but this is only for explaining 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 requirements.

[0060] The present invention is directed to a satellite with a rotating cabin for earth observation. The satellite rotating cabin simultaneously bears the functions of earth observation measurement and control, data transmission, and payload antennas, and needs to have the transmission functions of radio frequency signals, digital signals, and power supply at the same time. In view of the multi-channel radio frequency signal transmission requirements of on-board rotating components, and to solve the problem that cable winding occurs when digital signals are transmitted through wires through the satellite rotating cabin, and the problem that the contact characteristics of the friction pairs of traditional electrical slip rings may cause transmission error codes and wear life, a photoelectric conversion system of a smooth ring and an electrical slip ring driven by a turntable is designed. The electrical slip ring is used to solve the problem of high-speed electrical signal transmission in the satellite rotating cabin, and the smooth ring is used to simultaneously realize the transmission of on-board digital signals, optical signals, and radio frequency signals in the rotating mode. In addition, some problems of transmission reliability and health management are proposed during the on-orbit application of on-board measurement and control signals, data transmission signals, and payload signals, including:

[0061] 1. The photoelectric conversion system includes an electrical slip ring, a smooth ring, a baseline conversion module, and a platform conversion module. The baseline conversion module is arranged on one side of the rotating cabin, and the platform conversion module is arranged 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, and the health status of the smooth ring path is affected by the health status of the two end modules, resulting in a coupling safety problem.

[0062] 2. The design and management problems of the CAN bus between the satellite rotating cabin and the satellite platform cabin.

[0063] 3. For the on-orbit application environment of the smooth ring, generally, the satellite power supply system (solar panels, battery packs) and the on-board integrated processing computer (integrated electronics) are usually at one end of the non-rotating cabin of the satellite. There is a problem of coupling between the health status monitoring of each single machine in the satellite rotating cabin and the power supply safety of the photoelectric conversion system.

[0064] The present invention proposes an on-orbit fault diagnosis and health management based on on-board photoelectric slip rings, which can be applied to the reliability of digital signals, radio frequency signals, and power supply between the satellite platform cabin and the satellite rotating cabin, and improve the fault-free time of the reliable and stable operation of the photoelectric conversion system. It is mainly used to solve the application status monitoring of bus remote control, bus telemetry data, and space-earth radio frequency signal transmission, the self-health monitoring of the photoelectric conversion system, and the safety monitoring of power supply when the electrical slip ring and the smooth ring are applied between the satellite platform cabin and the satellite rotating cabin, and can realize the autonomous management and recovery of on-orbit faults.

[0065] Figure 1 The flowchart of the on-orbit fault diagnosis and health management method based on on-board photoelectric slip rings according to an embodiment of the present invention is shown. The following is combined with Figure 1, a description is given of the on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring proposed by the present invention. In an embodiment of the present invention, the on-orbit fault diagnosis and health management method based on the spaceborne optoelectronic slip ring can be executed by a computer. As Figure 1 shown, the on-orbit fault diagnosis and health management method based on the spaceborne optoelectronic slip ring includes the following steps:

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

[0067] Figure 2 shows a schematic diagram of the sub-cabin design of the optoelectronic conversion system according to an embodiment of the present invention. As Figure 2 shown, the satellite rotating cabin 1, i.e., the satellite payload cabin, rotates at an angular velocity ω. The satellite rotating cabin 1 is connected to the turntable 2, and the satellite platform cabin 3 is stationary.

[0068] Figure 3 shows a schematic diagram of the structure of the optoelectronic conversion system according to an embodiment of the present invention. As Figure 3 shown, the radio frequency signal transmission system of the satellite rotating cabin based on the 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 an embodiment of the present invention, the baseline conversion module 10 is used to convert a radio frequency signal into an optical signal or convert an optical signal into a radio frequency signal, or the baseline conversion module 10 is used to convert a digital signal and an optical signal into a coupled optical signal or convert the coupled optical signal into a digital signal and an optical signal. The optoelectronic slip ring 20 is located in the turntable 2. The optoelectronic slip ring 20 includes a smooth ring and an electrical slip ring. The optoelectronic slip ring 20 is driven to rotate by the turntable 2, and the optoelectronic slip ring 20 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 an embodiment of the present invention, the platform conversion module 30 is used to convert a radio frequency signal into an optical signal or convert an optical signal into a radio frequency signal, or the platform conversion module 30 is used to convert a digital signal and an optical signal into a coupled optical signal or convert the coupled optical signal into a digital signal and an optical signal. In an embodiment of the present invention, the radio frequency signal includes one or more of a tracking and control radio frequency signal, a data transmission radio frequency signal, an opportunistic radio frequency signal, and a payload radio frequency signal. In an embodiment of the present invention, the digital signal includes one or more of a CAN signal, an RS422 signal, and an LVDS signal; and / or the optical signal includes one or more of a satellite rotating cabin optical signal and a satellite platform cabin optical signal.

[0069] Figure 4 shows a schematic diagram of the structure of the optoelectronic slip ring according to an embodiment of the present invention. As Figure 4As shown, the smooth slip ring 201 is connected in series with the electrical slip ring 202. The smooth slip ring 201 includes a smooth slip ring stator 205 and a smooth slip ring rotor 204; the electrical slip ring 202 includes an electrical slip ring stator 207 and an electrical slip ring rotor 208. The smooth slip ring rotor 204 and the electrical slip ring rotor 208 achieve driving torque transmission through a two-stage fork mechanism. The turntable stator 203 is connected to the smooth slip ring stator 205 and the electrical slip ring stator 207. The motor output shaft 210 drives the turntable fork, i.e., the first-stage fork mechanism 209, and then the first-stage fork mechanism 209 drives the electrical slip ring 202 to rotate, and then the electrical slip ring fork, i.e., the second-stage fork mechanism 206, drives the smooth slip ring 201 to rotate. The rotational angular velocity of the motor output shaft 210 is ω. The installation steps of the smooth slip ring 201 and the electrical slip ring 202 are as follows: First, install the electrical slip ring rotor 208 and the smooth slip ring rotor 204 through the fork mechanism, adjust the coaxiality and perpendicularity of the installation to achieve synchronous rotation of the two slip rings; then install the turntable stator 203, the smooth slip ring stator 205, and the electrical slip ring stator 207, adjust the coaxiality and perpendicularity of the installation between the slip ring and the turntable, connect the rotor end of the turntable motor to the rotor end of the optoelectronic slip ring, drive the electrical slip ring to rotate by the turntable fork, and then achieve synchronous drive of the smooth slip ring by the electrical slip ring fork; the fork mechanism adopts a clearance fit and has low requirements for the installation accuracy of the shafting. The smooth slip ring rotor 204 is connected to the baseline conversion module 10, and the smooth slip ring stator 205 is connected to the platform conversion module 30, thereby realizing the interconnection and intercommunication of the external signal channels of the smooth slip ring 201.

[0070] In an embodiment of the present invention, the platform conversion module 30 is connected to the corresponding single-unit power supply interface and the remote control and telemetry signals of the satellite platform cabin 3, and the baseline conversion module 10 is connected to the corresponding single-unit power supply interface and the remote control and telemetry signals of the satellite rotating cabin 1. The signal transmission mechanism is as follows: Data is sent by the corresponding single unit of the satellite rotating cabin 1, and the corresponding single unit of the satellite platform cabin 3 tests and receives the correctness of the data; or data is sent by the corresponding single unit of the satellite platform cabin 3, and the corresponding single unit of the satellite rotating cabin 1 tests and receives the correctness of the data.

[0071] Taking the transmission of on-board radio frequency signals in the rotating mode by the smooth slip ring as an example, the signal transmission between the platform conversion module and the baseline conversion module is described. Figure 5 The schematic diagram of the on-board single-channel optoelectronic slip ring radio frequency signal transmission method according to an embodiment of the present invention is shown. As Figure 5As shown in the figure, the transmission method includes: converting the input multiple radio frequency signals into multiple optical signals, and inputting the multiple optical signals into an optical transmitting wavelength division multiplexer. The input multiple radio frequency signals are output by an opportunistic antenna, or an S antenna, or a tracking and control antenna, or a data transmission phased array. After passing through an electro-optic converter, the radio frequency signals are converted into optical signals and transmitted through the internal optical cable of the radio frequency to optical transmission module. After the multiple radio frequency signals pass through the wavelength division multiplexer, the multiple optical 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 the opto-electronic slip ring 20. The opto-electronic slip ring 20 is continuously rotated by the turntable 2. The opto-electronic slip ring transmits the optical signals to the optical receiving wavelength division multiplexer. The optical receiving wavelength division multiplexer restores the coupled optical signals output by the opto-electronic slip ring into multiple optical signals and inputs the restored multiple optical signals into the optical to radio frequency receiving module. The optical to radio frequency receiving module converts the restored multiple optical signals into multiple restored radio frequency signals and outputs them.

[0072] As Figure 5 As shown in the figure, the baseline conversion module 10 includes a first electro-optic converter 114 for electro-optic conversion, a first opto-electronic converter 116 for opto-electronic conversion, and a first optical transmitting wavelength division multiplexer 111 and a second optical transmitting wavelength division multiplexer 112. The optical receiving wavelength division multiplexer includes a first optical receiving wavelength division multiplexer 311 and a second optical transmitting wavelength division multiplexer 312. The optical to radio frequency receiving module includes a second opto-electronic converter 314 for opto-electronic conversion and a first electro-optic converter 317 for electro-optic conversion.

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

[0074] Since the information flow between the satellite platform cabin single machines and the satellite rotating cabin single machines is transmitted through the electro-optic slip ring, the platform conversion module, and the baseline conversion module. Under normal circumstances, the space-ground tracking and control uplink signal passes through the smooth slip ring to achieve the tracking and control of the satellite. When the opto-electronic slip ring system fails, the traditional space-ground tracking and control uplink channel cannot achieve the tracking and control of the satellite, and the satellite cannot perform routine maintenance and payload tasks. Therefore, it is necessary to implement autonomous detection and autonomous recovery of routine faults for the platform conversion module and the baseline conversion module of the opto-electronic slip ring. Using the platform integrated electronics and payload management unit to perform status monitoring on the platform conversion module and the baseline conversion module respectively mainly includes 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 voltages 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 length, a main and standby power supply switching instruction is triggered. The secondary power supply status monitoring identifier can be set to EHF-GD-JX-2-1.00. The platform integrated electronics and the payload management unit respectively perform autonomous monitoring on the secondary power supply status of the platform conversion module and the baseline conversion module. The default monitoring is enabled. When the monitoring is "disabled", no autonomous monitoring is performed until the "platform secondary power supply monitoring status enable" or "baseline secondary power supply monitoring status enable" instruction is received, and the "baseline secondary power supply monitoring status" is set to "enabled".

[0076] The platform integrated electronics and the payload management unit are respectively responsible for the single-unit monitoring and management of the satellite platform module and the satellite payload module, that is, the satellite rotating module. The platform integrated electronics serves as the primary overall control, and the payload management unit serves as the secondary overall control. The payload management unit is responsible for reporting all the states of the single units in the satellite payload module to the satellite platform module at a frequency of once per second. If there are problems with the information interaction between the two, the on-board management system will handle the faults of the payload management unit or the optoelectronic conversion system. When the payload management unit detects a baseline fault, it will handle the baseline fault. If the on-board management system determines that it still has not received the telemetry data of all the single units in the satellite payload module several times after the payload management unit has completed the handling, and believes that the fault has not been eliminated, the payload management unit will perform a reset operation and a manual power-on restart.

[0077] Taking the baseline conversion module as an example, the specific operation process of exception handling is described as follows:

[0078] The +5V main power supply voltage and the -5V main power supply voltage of the baseline conversion module are monitored in real time;

[0079] The preset threshold range includes a first preset threshold range and a second preset threshold range. The first preset threshold range is that the +5V main power supply voltage telemetry is not less than 2.2V (directly collected by the payload management unit, configurable) and not higher than 3.2V (directly collected by the payload management unit, configurable); the second preset threshold range is that the -5V main power supply voltage telemetry is not less than 1.4V (directly collected by the payload management unit, configurable) and not higher than 2.2V (directly collected by the payload management unit, configurable);

[0080] When the voltage value exceeds the first preset threshold range and the duration exceeds the set time length, 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 time length, this condition can be set as the second criterion. Among them, the set time length is 5s. When any one of the first criterion and the second criterion is satisfied, the load management unit continuously sends 3 instructions to turn off the main power supply of the baseline conversion module and turn on the standby power supply, with an instruction interval of 5s. After sending 3 times, set the "baseline secondary power supply monitoring status" to "forbidden". It should be noted that the voltage values and set time values in the first criterion and the second criterion are proposed based on the device manufacturer and product usage constraints, and the range values of the voltage and the set time in the criterion can be adjusted according to the product characteristics.

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

[0082] Taking the baseline conversion module as an example, the abnormal handling of the reset is described. When the load management unit is reset, the "baseline secondary power supply monitoring status" remains the same as the status before reset, and the corresponding monitoring status configuration parameters "baseline secondary power +5V monitoring voltage configuration parameter 1", "baseline secondary power +5V monitoring voltage configuration parameter 2", "baseline secondary power +5V monitoring time configuration parameter", "baseline secondary power -5V monitoring voltage configuration parameter 1", "baseline secondary power -5V monitoring voltage configuration parameter 2", "baseline secondary power -5V monitoring time configuration parameter" remain unchanged.

[0083] In an embodiment of the present invention, when the platform integrated electronics and the load management unit are reset, the secondary power supply monitoring status of the platform conversion module and the baseline conversion module is saved as the status before 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, perform status monitoring and safety management on the CAN bus between the satellite rotating cabin and the satellite platform cabin.

[0085] Figure 6 The CAN bus connection schematic diagram of an embodiment of the present invention is shown. The CAN bus between the satellite payload cabin and the satellite platform cabin is a key channel for the integrated electronics to remotely control single machines and collect single machine telemetry status, and is the basis for the satellite to normally execute ground tasks. The satellite payload cabin and the satellite platform cabin adopt a dual-bus handshake mechanism and realize data forwarding through the platform conversion module and the baseline conversion module. Therefore, the health status of the module will affect the health status judgment of the single machines in the satellite payload cabin.

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

[0087] When the payload management unit does not receive the platform integrated electronics CAN telemetry request signal for 10 consecutive seconds, the CAN bus chip is reset according to the CAN protocol.

[0088] When the payload management unit does not receive the platform integrated electronics CAN telemetry request signal for 45 consecutive seconds, the FPGA reset enable of the baseline conversion module is sent, and at the same time, the relevant telemetry is updated. If it is still not restored through the telemetry record, this step is repeated.

[0089] It should be noted that the time here (10 seconds, 45 seconds) takes into account hierarchical control and is processed according to measures from light to heavy. There is no CAN bus telemetry between the two modules. First, the CAN bus chip is reset. It can be disposed of more than 3 times in 45s. If it is still not restored, then the data transmission node (baseline) between the two modules is disposed of, and its FPGA is reset. It should be noted that the primary and backup on-orbit reliability of the CAN bus between the two modules is very high, which can ensure the reliability of CAN bus communication between the two modules. A CAN bus failure will cause the telemetry of other subsystems not to be downlinked, and the single machine cannot respond to the CAN commands of the satellite bus. There is no risk of safe operation. The satellite bus can normally receive commands and independently reset the CAN bus interface chip and initialize the interface chips of each node according to the telemetry judgment of each single machine, with relatively high reliability.

[0090] Finally, independent power distribution is performed on the platform conversion module and the baseline conversion module, and power on and off are autonomously controlled according to the health criterion.

[0091] The single machines in the satellite rotating module are powered by an electrical slip ring. The power supply of the electrical slip ring has been maturely applied in orbit, and the power supply and distribution of the single machines in the payload module can be realized through a power controller. For the baseline conversion module, since the power supply reliability of the baseline conversion module will affect the channel signal transmission, independent power distribution is adopted. The platform integrated electronics autonomously controls the power on and off of the platform conversion module and the baseline conversion module according to the above criteria.

[0092] The on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring proposed by the present invention provides an optoelectronic conversion system. High-speed electrical signals of the satellite's rotating cabin are transmitted through an electrical slip ring, and spaceborne digital signals, optical signals, and radio frequency signals are transmitted through a smooth ring, reducing signal entanglement and error code problems; a dynamic threshold is designed for the secondary power supply (+5V / -5V) to achieve seamless switching between the main and backup power supplies; combined with strategies such as dual-bus handshaking and FPGA reset, the problems of delay and error code in the CAN bus communication between the satellite's rotating cabin and the satellite platform cabin are solved; key parameters are saved in a non-volatile memory to ensure automatic restoration of the configuration 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 by the present invention is independent of the satellite model for related anomaly handling and can adapt to different models of satellites.

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

[0094] An optoelectronic conversion system construction module, configured to construct 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's rotating cabin, and the platform conversion module being located in the satellite platform cabin;

[0095] A status monitoring module, configured to use the platform integrated electronics and the payload management unit to respectively perform status monitoring on the platform conversion module and the baseline conversion module;

[0096] A CAN bus management module, configured to perform status monitoring and safety management on the CAN bus between the satellite's rotating cabin and the satellite platform cabin; and

[0097] A power supply management module, configured to perform independent power distribution on the platform conversion module and the baseline conversion module, and independently control power on and off according to health criteria.

[0098] In an embodiment of the present invention, the present invention further provides an electronic device, including: 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 the spaceborne optoelectronic slip ring, and the processor is configured to execute the machine-readable instructions. When the processor and / or the graphics card execute 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 rotating cabin, and the platform conversion module being located in the satellite platform cabin; using the platform integrated electronics and payload management unit to respectively perform status monitoring on the platform conversion module and the baseline conversion module; performing status monitoring and safety management on the 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 on and off according to the health criterion.

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

[0100] The memory includes: various media such as a USB flash drive, a read-only memory (ROM), a random access memory (RAM), a mobile hard disk, a magnetic disk, or an optical disc that can store machine-readable instructions.

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

[0102] In an embodiment of the present invention, the present invention further provides a computer-readable storage medium, on which machine-readable instructions are stored. When the machine-readable instructions are executed by a processor, 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 rotating cabin, and the platform conversion module being located in the satellite platform cabin; using the platform integrated electronics and payload management unit to respectively perform status monitoring on the platform conversion module and the baseline conversion module; performing status monitoring and safety management on the 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 on and off according to the health criterion.

[0103] Although the embodiments of the present invention have been described above, it should be understood that they are presented only as examples and not as limitations. It will be apparent to those skilled in the relevant art that various combinations, variations, and changes can be made thereto without departing from the spirit and scope of the present invention. Therefore, the breadth and scope of the present invention disclosed herein should not be limited by the exemplary embodiments disclosed above, but should be defined in accordance with the technical solution of the present invention and its equivalent replacements.

Claims

1. An on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring, characterized in that It includes the following steps: Construct a photovoltaic 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 rotating cabin, and the platform conversion module is located in the satellite platform cabin; Use the platform integrated electronics and payload management unit to perform status monitoring on the platform conversion module and the baseline conversion module respectively, including the following steps: Monitor the secondary power supply voltage of the platform conversion module and the baseline conversion module in real time. When the voltage value exceeds the preset threshold range and the duration exceeds the set time, trigger the main and standby power supply switching instruction; And When the platform integrated electronics and payload management unit is reset, save the secondary power supply monitoring status and configuration parameters of the platform conversion module and the baseline conversion module; Perform status monitoring and safety management on the CAN bus between the satellite rotating cabin and the satellite platform cabin; And Perform independent power distribution on the platform conversion module and the baseline conversion module, and independently control power on and off according to the health criterion.

2. The on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring according to claim 1, characterized in that Monitoring the secondary power supply voltage of the platform conversion module and the baseline conversion module in real time. When the voltage value exceeds the preset threshold range and the duration exceeds the set time, triggering the main and standby power supply switching instruction includes: Monitor the +5V main power supply voltage and -5V main power supply voltage of the platform conversion module and the baseline conversion module 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 that the +5V main power supply voltage is not lower than 2.2V and not higher than 3.2V, and the second preset threshold range is that the -5V main power supply voltage is not lower than 1.4V and not higher than 2.2V; The set time is 5s; When the voltage value exceeds the first preset threshold range or the second preset threshold range, and the duration exceeds the set time, the payload management unit sends instructions to turn off the main power supply and turn on the standby power supply.

3. The on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring according to claim 1, wherein When the platform integrated electronics and payload management unit is reset, saving the secondary power supply monitoring status and configuration parameters of the platform conversion module and the baseline conversion module includes: When the platform integrated electronics and payload management unit is reset, the secondary power supply monitoring status of the platform conversion module and the baseline conversion module is saved as the status before reset; The configuration parameters are the configuration parameters of the +5V main power supply voltage and -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 a spaceborne optoelectronic slip ring according to claim 1, wherein Performing status monitoring and safety management on the CAN bus between the satellite rotating cabin and the satellite platform cabin includes: The platform integrated electronics and payload management unit perform status monitoring on the CAN bus between the satellite rotating cabin and the satellite platform cabin through a dual-bus handshake mechanism; When the payload management unit does not receive the platform integrated electronics CAN telemetry request signal for 10 consecutive seconds, reset the CAN bus chip; When the payload management unit does not receive the platform integrated electronics CAN telemetry request signal for 45 consecutive seconds, the platform integrated electronics and payload management unit respectively reset the FPGA of the platform conversion module and the baseline conversion module.

5. The on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring according to claim 1, wherein Independent power distribution is performed for the platform conversion module and the baseline conversion module, and autonomous control of power-on and power-off according to health criteria includes: Power the satellite rotating module through an electrical slip ring; the platform integrated electronics perform autonomous power-on and power-off management on the platform conversion module and the baseline conversion module according to health criteria.

6. The on-orbit fault diagnosis and health management method based on a spaceborne optoelectronic slip ring according to claim 1, wherein The optoelectronic slip ring is located in the turntable, and the optoelectronic slip ring includes a smooth ring and an electrical slip ring; The smooth ring and the electrical slip ring are connected in series; the smooth ring includes a smooth ring stator and a smooth ring rotor; the electrical slip ring includes an electrical slip ring stator and an electrical slip ring rotor; The smooth ring rotor and the electrical slip ring rotor are connected by a fork mechanism, the turntable stator is connected to the smooth ring stator and the electrical slip ring stator, the electrical slip ring is driven to rotate by the turntable lever, and then the smooth ring is driven to rotate by the electrical slip ring lever; and 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 a spaceborne optoelectronic slip ring according to claim 1, wherein The platform conversion module is connected to the corresponding single-machine power supply interface and the remote control and telemetry signals of the satellite platform module, and the baseline conversion module is connected to the corresponding single-machine power supply interface and the remote control and telemetry signals of the satellite rotating module.

8. A system for the on-orbit fault diagnosis and health management method of the spaceborne optoelectronic slip ring according to any one of claims 1-7, characterized in that, It includes: An optoelectronic conversion system construction module configured to construct 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 rotating module, and the platform conversion module being located in the satellite platform module; A status monitoring module configured to perform status monitoring on the platform conversion module and the baseline conversion module respectively using the platform integrated electronics and the payload management unit; A CAN bus management module configured to perform status monitoring and safety management on the CAN bus between the satellite rotating module and the satellite platform module; And A power supply management module configured to perform independent power distribution on the platform conversion module and the baseline conversion module, and autonomously control power-on and power-off according to health criteria.

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

10. A computer-readable storage medium, characterized in that, Machine-readable instructions are stored thereon, and the machine-readable instructions perform the steps of the method according to any one of claims 1-7 when executed by the processor.

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