Lightweight high-precision spaceflight electronic system based on self-calibration inertial measurement unit

Abstract

The invention discloses a lightweight high-precision spaceflight electronic system based on a self-calibration inertial measurement unit, and the system is characterized in that a comprehensive information processing module provides an operation environment for flight control, multi-information comprehensive processing, guidance, attitude control, radar height measurement and terrain matching, and is responsible for inertial measurement unit self-calibration, inertial measurement error compensation, signal collection and logic judgment, and external communication; and performing satellite navigation solution and Beidou short message communication. The three-self-inertial-unit module is used for measuring apparent acceleration and angular velocity in three directions of a coordinate system of a spaceflight electronic system; the double-shaft indexing mechanism controls the frame shaft system to drive the inner table body to rotate and position; the satellite guide radio frequency module is responsible for down-conversion, filtering amplification and anti-interference processing of radio frequency signals and outputting digital intermediate frequency signals; the power supply electric control module is responsible for secondary power supply conversion, primary power supply and distribution, ignition time sequence control, ignition circuit self-inspection and time sequence voltage telemetering acquisition; the electrical interconnection assembly is responsible for the electrical interconnection function in the aerospace electronic system.

Description

Technical Field

[0001] The invention relates to a lightweight and high-precision aerospace electronic system based on a self-calibration inertial group, and belongs to the field of aerospace equipment. Background Art

[0002] The rapid progress of science and technology at home and abroad, especially the breakthrough development in artificial intelligence, big data, new materials and new power, has profoundly reshaped the existence of the modern technological revolution. The increasing maturity of these technologies has injected strong impetus into the innovation of aerospace equipment, resulting in fundamental changes in its response capabilities and methods. At the same time, as the aerospace industry and aircraft systems move to a higher level, the discrete layout of traditional aerospace electronic equipment can no longer meet the current needs of lightweight, miniaturization and high precision. Therefore, it is important to realize the lightweight miniaturization and high-precision measurement functions of aerospace electronic systems and maintain competitive advantages in the complex and changing battlefield environment in the future.

[0003] Patent "Integrated Missile-borne Integrated Electronic System" (CN116165949A), the system adopts a mutually stacked layout design to integrate various functional modules into the integrated electronic system, integrating traditional discrete functional stand-alone equipment into an integrated integrated electronic device, and realizing the integration and miniaturization of its electrical system. However, the system does not have the function of self-calibration of inertial measurement parameters, and cannot meet the current demand for long-term storage of inertial measurement accuracy of aerospace electronic systems. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a lightweight and high-precision aerospace electronic system based on a self-calibrated inertial group, to give priority to mature and reliable structural, electrical and functional solutions to ensure the reliability of the aerospace electronic system; to reduce weight and save space as the goal, to effectively improve the lightweight and miniaturization level of the aerospace electronic system.

[0005] The technical solution of the present invention is: a lightweight and high-precision aerospace electronic system based on a self-calibrated inertial group, including: an integrated information processing module, a three-self-inertial group module, a satellite navigation radio frequency module, a power supply electronic control module, and an electrical interconnection component, wherein:

[0006] The integrated information processing module includes a main control processor, a coprocessor, a peripheral interface, and a satellite navigation baseband chip: the main control processor provides an operating environment for flight control, multi-information integrated processing, guidance, attitude control, radar altimetry, and terrain matching; the coprocessor is responsible for inertial group self-calibration, inertial measurement error compensation, signal acquisition and logic judgment, and external communication; the peripheral interface is responsible for information exchange with other modules; the satellite navigation baseband chip is responsible for satellite navigation solution and Beidou short message communication;

[0007] The three-auto-inertial group module includes an inertial measurement component and a dual-axis transfer mechanism, wherein the inertial measurement component includes three-axis fiber optic gyroscopes, three accelerometers and an IF conversion circuit, which is used to measure the apparent acceleration and angular velocity in three directions of the aerospace electronic system coordinate system, and send the measured acceleration and angular velocity information to the comprehensive information processing module; the dual-axis transfer mechanism includes an inner frame axis system, an outer frame axis system and an electrical control system, the electrical control system includes a rotary lock circuit and related circuits, and torque motors and multi-stage rotary angle measuring devices are installed at both ends of the inner frame axis system and the outer frame axis system, respectively, and a closed-loop control circuit is formed with the rotary lock circuit to jointly control the frame axis system to drive the rotation and positioning of the inner platform of the transfer mechanism;

[0008] The satellite navigation RF module is responsible for down-conversion, filtering and amplification, and anti-interference processing of RF signals, and outputs digital intermediate frequency signals to the comprehensive information processing module;

[0009] The power electronic control module is responsible for the secondary power conversion of each functional module of the aerospace electronic system and the primary power supply and distribution, ignition timing control, ignition circuit self-test and timing voltage telemetry collection of the remaining single units of the aircraft;

[0010] The electrical interconnection components are responsible for the electrical interconnection functions within the aerospace electronic system.

[0011] Preferably, the satellite navigation radio frequency module includes a device Beidou radio frequency channel, an airborne Beidou radio frequency channel and a Beidou short message radio frequency channel, wherein:

[0012] The satellite signal received by the device's Beidou RF channel is processed by low-noise amplifier, mixed by the RF chip, and then linearly moved to the intermediate frequency. After anti-interference processing, the digital intermediate frequency signal of the device's Beidou RF channel is output to the comprehensive information processing module;

[0013] The airborne Beidou RF channel receives the airborne satellite signal and processes it through low-noise amplifier, then down-converts it through the RF chip, and outputs the digital intermediate frequency signal of the airborne Beidou RF channel to the integrated information processing module for processing;

[0014] The Beidou short message radio frequency channel receives the RDSS signal generated by the Beidou satellite, and after low noise amplification processing, it is down-converted through the radio frequency chip, and outputs the Beidou short message radio frequency channel digital intermediate frequency signal to the comprehensive information processing module for processing;

[0015] The anti-interference processing unit collects the satellite analog intermediate frequency signal through the analog-to-digital converter, outputs it to the FPGA chip in the satellite RF module for anti-interference processing and outputs it in the form of digital intermediate frequency.

[0016] Preferably, the three-axis fiber optic gyroscopes, three accelerometers and IF conversion circuit of the inertial measurement assembly are all assembled in the inner platform of the indexing mechanism, wherein:

[0017] The three-axis fiber optic gyroscope adopts a three-axis integrated fiber optic gyroscope design based on a fully digital closed-loop solution;

[0018] The accelerometer uses a quartz flexible accelerometer, and a digital temperature sensor is installed on the end face of the internal core of the accelerometer;

[0019] The main function of the IF conversion circuit is to convert the current analog signal output by the accelerometer into a digital signal and send it to the integrated information processing module; it includes three conversion channels, which respectively complete the analog-to-digital conversion of the output signals of the three-axis accelerometer X, Y, and Z.

[0020] Preferably, the power supply electronic control module includes a power distribution unit and an electronic control unit, wherein:

[0021] The power distribution unit is responsible for secondary power conversion, primary power supply and distribution, and power control functions;

[0022] The electronic control unit realizes power drive, timing control processing and self-test telemetry functions.

[0023] Preferably, in the electronic control unit of the power electronic control module:

[0024] The power drive design adopts a multi-channel timing circuit parallel redundancy design;

[0025] The timing control design uses the FMQL20S processor as the hardware platform, which includes two types of resources: the programmable logic part PL and the processing system part PS. The programmable logic part PL is responsible for multi-channel electrical timing, switching quantity, data acquisition, and communication interface logic control functions, and the processing system part PS is responsible for receiving the data from the programmable logic part PL and performing analysis and processing as well as online upgrade functions.

[0026] The self-test telemetry design controls the on and off of the self-test power supply through self-test enable to realize the resistance detection function of the pyrotechnic device; by unlocking the power supply fuse and responding to the timing control instruction, the voltage telemetry function of the corresponding timing channel is realized.

[0027] Preferably, when the three-inertial group module is self-calibrated, a system-level calibration method based on a dual-axis rotation structure is adopted:

[0028] The comprehensive information processing module uses the measured acceleration and angular velocity information to establish a mathematical model, and uses the Kalman filtering technology to estimate the error of the established mathematical model in real time, obtain all error parameters in the mathematical model, improve the navigation accuracy of the inertial navigation system in a dynamic environment, and realize the self-calibration function of the system inertial measurement parameters.

[0029] Preferably, the main control processor and the coprocessor of the integrated information processing module constitute a minimum system unit for information processing, wherein:

[0030] The main control processor uses the FT-M6678 chip, of which four cores complete guidance, attitude control calculations, radar height calculations and terrain matching, and the remaining four cores serve as backup;

[0031] The coprocessor uses the FMQL45T chip, in which the programmable logic part PL is responsible for interface logic control and inertial measurement signal acquisition, and the processing system part PS is responsible for inertial measurement error compensation and FMQL45T software online update;

[0032] The FT-M6678 chip and the FMQL45T chip are interconnected through the EMIF bus and the SRIO bus, and the external memory is expanded.

[0033] Preferably, the integrated information processing module also includes a peripheral interface unit, which includes interfaces for data storage, RS422A, RS232, input and output switch quantities, and 1553B.

[0034] Preferably, the maximum outer envelope size of the system equipment is 260mm×220mm×150mm, and the equipment shell material is 2A12 grade T4 state aluminum alloy;

[0035] The system equipment adopts a domain-divided design concept, and the areas of each module are isolated from each other. At the same time, each module adopts a staggered arrangement of high and low devices to make full use of the internal space. The three-auto inertial group module is arranged in the center of the product to reduce the eccentricity of the inertial group module.

[0036] Preferably, the electrical interconnection component adopts a flexible design, and each functional module completes signal transmission and power supply through the flexible electrical interconnection component, thereby reducing space occupancy.

[0037] Compared with the prior art, the present invention has the following advantages:

[0038] (1) The present invention adopts a standardized modular, lightweight, and miniaturized design architecture, gives priority to mature and reliable structural, electrical, and functional solutions, and for the first time integrates the self-calibration inertial group module with the comprehensive information processing module, the satellite navigation radio frequency module, and the power supply and electronic control module in a miniaturized and lightweight manner through a domain-based design, a mosaic layout, and full flexible interconnection, thus solving the versatility problem of current aerospace electronic systems;

[0039] (2) The present invention adopts a three-axis integrated fiber optic gyroscope design method based on a fully digital closed-loop solution to achieve the precise and stable measurement function of the three-axis angular velocity; adopts a "flexible quartz accelerometer (large meter) + high-precision I / F conversion circuit" design method to achieve the high-precision and high-reliability measurement function of the three-axis acceleration; adopts a system-level calibration method based on a dual-axis rotation structure to enable the system to have an inertial measurement parameter self-calibration function, greatly improving the accuracy of the aerospace electronic system inertial measurement under long-term storage conditions;

[0040] (3) The advanced electronic technology for centralized information control and electrical timing optimization described in the present invention adopts microsystem technology to realize multiple information centralized processing functions such as satellite navigation, Beidou short messages, high-precision inertial measurement, electrical timing control, power supply and distribution, etc.; it adopts a power-driven multi-channel parallel redundant design scheme to improve the reliability level of the system's electrical timing control, and realize the system's stable and reliable electrical timing control, timing voltage telemetry collection and other functions. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 This is a functional block diagram of a lightweight and high-precision aerospace electronic system based on a self-calibration inertial group according to the present invention;

[0042] Figure 2 This is a schematic diagram of the structure and appearance of a lightweight and high-precision aerospace electronic system based on a self-calibration inertial group according to the present invention;

[0043] Figure 3 The present invention is a block diagram of a lightweight, high-precision aerospace electronic system with three self-inertial group devices based on a self-calibration inertial group. DETAILED DESCRIPTION

[0044] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0045] like Figure 1 The figure shows a schematic diagram of the structure of a lightweight, high-precision aerospace electronic system based on a self-calibrated inertial group. The maximum outer envelope size of the system equipment is 260mm×220mm×150mm, and the shell material is 2A12 grade T4 aluminum alloy, which has the advantages of low density and high strength. From the perspective of system function and its modularization, the structural layout adopts "domain design", "airtight design", "inlaid" layout, "full flexible interconnection" and "efficient thermal management":

[0046] a) "Divided domain design": The system is divided into inertial measurement area (three-inertial group module), information processing area (comprehensive information processing module), power drive area (power electronic control module) and radio frequency transceiver area (satellite navigation radio frequency module) according to the function. Each area is isolated from each other to prevent mutual interference between strong and weak electricity, radio frequency and other signals, and enhance the electromagnetic compatibility of the system; the three-inertial group module is arranged in the center of the product, which is conducive to reducing the eccentricity of the inertial group module and ensuring the shock absorption effect of the shock absorber;

[0047] b) “Airtight design”: The inertial measurement area (three-inertial group module) is designed to be airtight separately to ensure that the accuracy of the electronic equipment meets the requirements during long-term storage, prevent the internal precision components from being disturbed by the external environment, and achieve the best sealing effect;

[0048] c) "Inlay" layout: A modular inlay structure layout design is adopted to maximize space utilization. The integrated information processing module, three-auto inertial group module, satellite navigation radio frequency module, and power supply electronic control module are designed by adopting a high-low device staggered layout method to make full use of the space between boards and reduce the overall height of the equipment;

[0049] d) “Fully flexible interconnection”: Each functional module realizes signal transmission and power supply through flexible interconnection components (electrical interconnection components), and there is no cable routing between modules, which reduces space occupation;

[0050] e) "Efficient thermal management": The system adopts a miniaturized thermal design solution of "high thermal conductivity material + phase change heat storage + time-sharing power supply management". High thermal conductivity materials are used to transfer heat from areas with higher power density to areas with lower temperature. Phase change materials are used to absorb heat conducted from the internal environment, thereby improving the heat dissipation efficiency of the equipment. The surface of the equipment is treated with high thermal conductivity blackening, which is conducive to achieving thermal balance inside the equipment.

[0051] The functional design scheme of the present invention mainly includes a comprehensive information processing module, a three-auto inertial group module, a satellite navigation radio frequency module, a power supply electronic control module, and an electrical interconnection component, which are specifically as follows:

[0052] a) The integrated information processing module adopts the mature "FT-M6678+FMQL45T+BP2020" domestic processor overall architecture design scheme, and exchanges information with other modules through peripheral interfaces. Among them, FT-M6678 is used as the main control processor to provide an operating environment for flight control, multi-information integrated processing, guidance, attitude control, radar altimetry, terrain matching and other functions; SOPC chip FMQL45T is used as a coprocessor to complete the functions of inertial group self-calibration, inertial measurement error compensation, signal acquisition and logic judgment, external communication, etc., and exchanges information with the FT-M6678 chip through the EMIF bus and SRIO bus interconnection method; BP2020 is a satellite navigation baseband chip, which completes satellite navigation solution and Beidou short message communication and other functions, and exchanges information with the FMQL45T chip through serial communication; peripheral interfaces include data storage, RS422A, RS232, input and output switch quantity and 1553B interface, which are responsible for various controls and information exchanges;

[0053] b) The three-auto-inertial group module consists of an inertial measurement unit and a dual-axis transfer mechanism, wherein the inertial measurement unit includes a three-axis fiber optic gyroscope and an accelerometer, which are placed in the inner frame of the dual-axis transfer mechanism; the dual-axis transfer mechanism is mainly composed of an inner and outer frame shaft system and an electrical control system, the electrical control system includes a rotation lock circuit and related circuits, and torque motors and multi-stage rotary angle measuring devices are installed at both ends of the inner and outer frame shaft systems, and a closed-loop control loop is formed with the rotation lock circuit to jointly control the frame shaft system to drive the rotation and positioning of the internal platform of the transfer mechanism, and complete the apparent acceleration and angular velocity measurement function of the three directions of the aerospace electronic system coordinate system;

[0054] c) The satellite navigation RF module completes the down-conversion, filtering and amplification, and anti-interference processing of the RF signal, and outputs the digital intermediate frequency signal to the comprehensive information processing module. It mainly includes the equipment Beidou RF channel, the airborne Beidou RF channel, and the Beidou short message RF channel. Among them:

[0055] The Beidou RF channel, airborne Beidou RF channel and Beidou short message RF channel are respectively equipped with Beidou RF chip, airborne Beidou RF chip and short message RF chip, and low noise amplifier units are set in all three channels.

[0056] The satellite signal received by the device's Beidou RF channel is processed by the low noise amplifier unit, mixed by the device's Beidou RF chip, and then linearly moved to the intermediate frequency. After being processed by the anti-interference processing unit, the digital intermediate frequency signal of the device's Beidou RF channel is output to the comprehensive information processing module for processing;

[0057] The airborne Beidou RF channel receives the airborne satellite signal and processes it through the low noise amplifier unit, then down-converts it through the airborne Beidou RF chip, and outputs the airborne Beidou RF channel digital intermediate frequency signal to the integrated information processing module for processing;

[0058] The Beidou short message RF channel receives the RDSS (Radio Determination Satellite Service) signal of the Beidou satellite, passes through the low noise amplifier unit, performs down-conversion processing through the short message RF chip, and outputs the Beidou short message RF channel digital intermediate frequency signal to the comprehensive information processing module for processing; the RDSS (Radio Determination Satellite Service) signal transmission channel baseband signal is generated in the comprehensive information processing module, modulated and mixed by the short message RF chip, and then output to the Beidou short message RF channel through the amplification channel;

[0059] The anti-interference processing unit collects the satellite analog intermediate frequency signal through the AD (analog-to-digital converter), outputs it to the FPGA chip in the satellite radio frequency module for anti-interference processing and outputs it in the form of digital intermediate frequency;

[0060] d) The power electronic control module mainly completes the secondary power conversion of various functional modules of the aerospace electronic system and the primary power supply and distribution, ignition timing control, ignition circuit self-test and timing voltage telemetry collection of other single units of the aircraft. It mainly includes two parts: power distribution unit (realizing secondary power conversion, power distribution and power control, etc.) and electronic control unit (realizing power drive, timing control processing and self-test telemetry, etc.). The power distribution unit realizes the secondary power conversion and power distribution functions of the electronic control unit.

[0061] e) The electrical interconnection components realize the internal electrical interconnection function of the aerospace electronic system through a fully flexible circuit design.

[0062] like Figure 2 The figure shows a block diagram of a lightweight, high-precision, aerospace electronic system three-self-inertial group device based on a self-calibration inertial group of the present invention. The three-self-inertial group module is mainly composed of two parts: an inertial measurement assembly and a dual-axis indexing mechanism. The inertial measurement assembly includes three axial fiber optic gyroscopes, three accelerometers, and an IF conversion circuit. The fiber optic gyroscope, accelerometer, and IF conversion circuit are all assembled in the inner platform of the indexing mechanism to complete the measurement function of the apparent acceleration and angular velocity in three directions of the aerospace electronic system coordinate system; the dual-axis indexing mechanism is mainly composed of an inner frame axis system (including the inner platform of the indexing mechanism), an outer frame axis system, and an electrical control system. The electrical control system includes a rotary lock circuit and related circuits. A torque motor and a multi-stage rotary angle meter are installed at both ends of the inner and outer frame axis systems, respectively, and a closed-loop control circuit is formed with the rotary lock circuit to jointly control the frame axis system to drive the rotation and positioning of the inner platform.

[0063] Among them, the inner table of the indexing mechanism is designed in a modular and integrated manner, and is equipped with three-axis gyroscopes, three accelerometers and an IF conversion circuit.

[0064] a) The three-axis integrated fiber optic gyroscope design based on a fully digital closed-loop solution can greatly reduce the impact of light source power fluctuations on gyroscope performance, effectively avoid long-term drift caused by changes in electronic circuit parameters, and improve the linearity and stability of the gyroscope scale factor;

[0065] b) The accelerometer uses a quartz flexible accelerometer (measuring range ±50g). In order to realize the temperature collection function of the accelerometer, a digital temperature sensor is installed on the end face of the internal core of the accelerometer to realize the real-time temperature output of the accelerometer;

[0066] c) The main function of the IF conversion circuit is to convert the current analog signal output by the accelerometer into a digital signal and send it to the comprehensive information processing module. It includes three conversion channels, which respectively complete the analog-to-digital conversion of the output signals of the three-axis accelerometer of X, Y, and Z;

[0067] When the three-inertial navigation system module of the present invention performs self-calibration, a system-level calibration method based on a dual-axis rotation structure is adopted, a mathematical model is established in a comprehensive information processing module using the acceleration and angular velocity information measured by the three-inertial navigation system module, and the error parameters of the existing model are estimated in real time through the Kalman filtering technology to obtain all error parameters in the IMU calibration model (the established mathematical model), thereby improving the navigation accuracy of the inertial navigation system in a dynamic environment and realizing the self-calibration function of the system inertial measurement parameters.

[0068] like Figure 3 The figure shows a functional block diagram of a lightweight and high-precision aerospace electronic system based on a self-calibration inertial group according to the present invention. The aerospace electronic system comprises an integrated information processing module, a three-self-inertial group module, a satellite navigation radio frequency module, a power supply electronic control module, and interconnection components. The advanced electronic technology of centralized information control and electrical timing optimization in the present invention is realized by the electronic control unit in the integrated information processing module and the power supply electronic control module.

[0069] The comprehensive information processing module realizes the functions of guidance and control solution, integrated navigation solution, satellite navigation baseband, Beidou short message baseband, security control, signal acquisition and logic judgment, inertial group error compensation, transfer mechanism control and inertial group self-calibration. The module is divided into three parts: information processing minimum system unit, peripheral interface unit and satellite navigation baseband information processing unit: the information processing minimum system unit is based on the FT-M6678 main control processor and FMQL45T coprocessor, interconnected through EMIF bus and SRIO bus, and expanded with external memory such as DDR3 and FLASH; the peripheral interface unit contains a variety of control and communication interfaces; the satellite navigation baseband information processing unit completes satellite navigation and Beidou short message baseband processing.

[0070] a) The information processing minimum system unit processor adopts the domestically produced solution of "FT-M6678+FMQL45T". FT-M6678 cores 0 to 3 complete guidance, attitude control calculations, radar height calculations and terrain matching, and the remaining 4 cores are used as backups. The PL (programmable logic part) in the FMQL45T is responsible for functions such as interface logic control and inertial measurement signal acquisition, among which the PS (processing system part) is responsible for inertial measurement error compensation and FMQL45T software online update;

[0071] b) The peripheral interface unit includes interfaces such as large-capacity data storage, RS422A, RS232, input and output switch quantity and 1553B (1M, 4M, 1.0625Gbps);

[0072] c) The satellite navigation baseband information processing unit is mainly composed of the minimum system circuit of the satellite navigation baseband chip BP2020 (Beidou-3 baseband chip). The digital intermediate frequency signal is directly provided to the Beidou-3 baseband chip through the off-chip bus. The baseband chip completes the signal capture and tracking processing to obtain the original measurement information, and despreads and demodulates the signal to obtain the original telegram information.

[0073] The electronic control unit in the power supply electronic control module mainly realizes functions such as electrical timing control, timing voltage telemetry acquisition and line self-test, and mainly includes power drive, timing control processing and self-test telemetry.

[0074] a) The power drive design adopts a multi-channel timing circuit parallel redundant design to achieve high-reliability electrical timing control function;

[0075] b) The timing control design uses the FMQL20S processor as the hardware platform, which includes two types of resources: PL and PS. The PL side is responsible for the interface logic control functions such as multi-channel electrical timing, switching quantity, data acquisition, and communication, and the PS side is responsible for receiving the PL side data and performing analysis and processing and online upgrade functions;

[0076] c) The self-test telemetry design controls the on and off of the self-test power supply through self-test enable to realize the resistance detection function of the pyrotechnic device; by unlocking the power supply fuse and responding to the timing control instruction, the voltage telemetry function of the corresponding timing channel is realized.

[0077] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in this field.

Claims

1. A lightweight and high-precision aerospace electronic system based on a self-calibrated inertial group, characterized in that include: Comprehensive information processing module, three-auto inertial group module, satellite navigation radio frequency module, power supply and electronic control module, electrical interconnection components, including: The integrated information processing module includes a main control processor, a coprocessor, a peripheral interface, and a satellite navigation baseband chip: the main control processor provides an operating environment for flight control, multi-information integrated processing, guidance, attitude control, radar altimetry, and terrain matching; the coprocessor is responsible for inertial group self-calibration, inertial measurement error compensation, signal acquisition and logic judgment, and external communication; the peripheral interface is responsible for information exchange with other modules; the satellite navigation baseband chip is responsible for satellite navigation solution and Beidou short message communication; The three-auto-inertial group module includes an inertial measurement component and a dual-axis transfer mechanism, wherein the inertial measurement component includes three-axis fiber optic gyroscopes, three accelerometers and an IF conversion circuit, which is used to measure the apparent acceleration and angular velocity in three directions of the aerospace electronic system coordinate system, and send the measured acceleration and angular velocity information to the comprehensive information processing module; the dual-axis transfer mechanism includes an inner frame axis system, an outer frame axis system and an electrical control system, the electrical control system includes a rotary lock circuit and related circuits, and torque motors and multi-stage rotary angle measuring devices are installed at both ends of the inner frame axis system and the outer frame axis system, respectively, and a closed-loop control circuit is formed with the rotary lock circuit to jointly control the frame axis system to drive the rotation and positioning of the inner platform of the transfer mechanism; The satellite navigation RF module is responsible for down-conversion, filtering and amplification, and anti-interference processing of RF signals, and outputs digital intermediate frequency signals to the comprehensive information processing module; The power electronic control module is responsible for the secondary power conversion of each functional module of the aerospace electronic system and the primary power supply and distribution, ignition timing control, ignition circuit self-test and timing voltage telemetry collection of the remaining single units of the aircraft; The electrical interconnection components are responsible for the electrical interconnection functions within the aerospace electronic system.

2. A lightweight, high-precision aerospace electronic system based on a self-calibration inertial group according to claim 1, characterized in that: The satellite navigation RF module includes the equipment Beidou RF channel, the airborne Beidou RF channel and the Beidou short message RF channel, among which: The satellite signal received by the device's Beidou RF channel is processed by low-noise amplifier, mixed by the RF chip, and then linearly moved to the intermediate frequency. After anti-interference processing, the digital intermediate frequency signal of the device's Beidou RF channel is output to the comprehensive information processing module; The airborne Beidou RF channel receives the airborne satellite signal and processes it through low-noise amplifier, then down-converts it through the RF chip, and outputs the digital intermediate frequency signal of the airborne Beidou RF channel to the integrated information processing module for processing; The Beidou short message radio frequency channel receives the RDSS signal generated by the Beidou satellite, and after low noise amplification processing, it is down-converted through the radio frequency chip, and outputs the Beidou short message radio frequency channel digital intermediate frequency signal to the comprehensive information processing module for processing; The anti-interference processing unit collects the satellite analog intermediate frequency signal through the analog-to-digital converter, outputs it to the FPGA chip in the satellite RF module for anti-interference processing and outputs it in the form of digital intermediate frequency.

3. The lightweight and high-precision aerospace electronic system based on a self-calibration inertial group according to claim 1 is characterized in that: The three-axis fiber optic gyroscopes, three accelerometers and IF conversion circuit of the inertial measurement unit are all assembled in the inner platform of the indexing mechanism, where: The three-axis fiber optic gyroscope adopts a three-axis integrated fiber optic gyroscope design based on a fully digital closed-loop solution; The accelerometer uses a quartz flexible accelerometer, and a digital temperature sensor is installed on the end face of the internal core of the accelerometer; The main function of the IF conversion circuit is to convert the current analog signal output by the accelerometer into a digital signal and send it to the integrated information processing module; it includes three conversion channels, which respectively complete the analog-to-digital conversion of the output signals of the three-axis accelerometer X, Y, and Z.

4. The lightweight and high-precision aerospace electronic system based on a self-calibration inertial group according to claim 1 is characterized in that: The power supply and electronic control module includes a power distribution unit and an electronic control unit, wherein: The power distribution unit is responsible for secondary power conversion, primary power supply and distribution, and power control functions; The electronic control unit realizes power drive, timing control processing and self-test telemetry functions.

5. A lightweight, high-precision aerospace electronic system based on a self-calibration inertial group according to claim 4, characterized in that: In the electronic control unit of the power electronic control module: The power drive design adopts a multi-channel timing circuit parallel redundancy design; The timing control design uses the FMQL20S processor as the hardware platform, which includes two types of resources: the programmable logic part PL and the processing system part PS. The programmable logic part PL is responsible for multi-channel electrical timing, switching quantity, data acquisition, and communication interface logic control functions, and the processing system part PS is responsible for receiving the data from the programmable logic part PL and performing analysis and processing as well as online upgrade functions. The self-test telemetry design controls the on and off of the self-test power supply through self-test enable to realize the resistance detection function of the pyrotechnic device; by unlocking the power supply fuse and responding to the timing control instruction, the voltage telemetry function of the corresponding timing channel is realized.

6. The lightweight and high-precision aerospace electronic system based on a self-calibration inertial group according to claim 1, characterized in that: When the three-inertial group module is self-calibrated, a system-level calibration method based on a dual-axis rotation structure is adopted: The comprehensive information processing module uses the measured acceleration and angular velocity information to establish a mathematical model, and uses the Kalman filtering technology to estimate the error of the established mathematical model in real time, obtain all error parameters in the mathematical model, improve the navigation accuracy of the inertial navigation system in a dynamic environment, and realize the self-calibration function of the system inertial measurement parameters.

7. The lightweight and high-precision aerospace electronic system based on a self-calibration inertial group according to claim 1 is characterized in that: The main control processor and coprocessor of the integrated information processing module constitute the minimum system unit for information processing, where: The main control processor uses the FT-M6678 chip, of which four cores complete guidance, attitude control calculations, radar height calculations and terrain matching, and the remaining four cores serve as backup; The coprocessor uses the FMQL45T chip, in which the programmable logic part PL is responsible for interface logic control and inertial measurement signal acquisition, and the processing system part PS is responsible for inertial measurement error compensation and FMQL45T software online update; The FT-M6678 chip and the FMQL45T chip are interconnected through the EMIF bus and the SRIO bus, and the external memory is expanded.

8. The lightweight and high-precision aerospace electronic system based on a self-calibration inertial group according to claim 1 is characterized in that: The comprehensive information processing module also includes a peripheral interface unit, which includes interfaces of data storage, RS422A, RS232, input and output switch quantities and 1553B.

9. The lightweight and high-precision aerospace electronic system based on a self-calibration inertial group according to claim 1, characterized in that: The maximum outer envelope size of the system equipment is 260mm×220mm×150mm, and the equipment shell material is 2A12 grade T4 aluminum alloy; The system equipment adopts a domain-divided design concept, and the areas of each module are isolated from each other. At the same time, each module adopts a staggered arrangement of high and low devices to make full use of the internal space. The three-auto inertial group module is arranged in the center of the product to reduce the eccentricity of the inertial group module.

10. The lightweight and high-precision aerospace electronic system based on a self-calibration inertial group according to claim 1, characterized in that: The electrical interconnection components adopt a flexible design, and each functional module completes signal transmission and power supply through flexible electrical interconnection components, reducing space occupancy.

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