Micro-vibration on-orbit measurement system of spacecraft and data processing method

Abstract

The embodiment of the invention provides a spacecraft micro-vibration on-orbit measurement system and a data processing method, and the system comprises an acceleration sensing module which is used for obtaining an acceleration signal, and determining acceleration information based on the acceleration signal; the signal conditioning module is used for supplying power to the acceleration sensing module, acquiring acceleration information and temperature information of the acceleration sensing module and conditioning the acceleration information and the temperature information; the rotation measurement module is used for acquiring an angular vibration signal and determining angular vibration information based on the angular vibration signal; and the control storage module is used for communicating with a spacecraft platform, controlling the acceleration sensing module, the signal conditioning module and the rotation measurement module, and receiving and storing data of the acceleration sensing module, the signal conditioning module and the rotation measurement module. Interference isolation is arranged between the modules, so that the data accuracy and the measurement precision are improved.

Description

Technical Field

[0001] The embodiments of this specification relate to the field of aerospace technology, and in particular to an on-orbit micro-vibration measurement system for spacecraft. Background Art

[0002] The micro-vibration generated by the momentum wheels used to adjust the attitude of the spacecraft and the refrigerators used to maintain the performance of the camera during operation is transmitted to the camera through the structure, which will cause blurred imaging. With the improvement of spacecraft performance, the observation resolution has been greatly improved, and the requirements for the control level of micro-vibration have been raised. The micro-vibration effect has become a technical bottleneck. In order to test the impact of micro-vibration on the quality of on-orbit imaging and correct the imaging through micro-vibration measurement data, it is necessary to arrange measurement points at key locations on the micro-vibration transmission path of the spacecraft to measure the micro-vibration response. The micro-vibration response is characterized by physical quantities such as micro-acceleration and micro-rotation of the imaging link. These physical quantities have small amplitudes and wide bandwidths. In order to effectively obtain the micro-vibration response on high-resolution spacecraft, it is necessary to develop a high-resolution micro-vibration on-orbit measurement system that meets the application requirements of the spacecraft.

[0003] The existing technology is aimed at the on-orbit micro-vibration measurement needs of conventional satellites, while large spacecraft have higher imaging resolution, longer measurement point distribution distance, higher reliability requirements, and larger data volume. Not only do they need to measure on-orbit acceleration, but they also need to measure on-orbit angular displacement with high precision and synchronization, which places higher requirements on the background noise, resolution, synchronization and other indicators of the micro-vibration measurement system. Therefore, a better solution is urgently needed. Summary of the invention

[0004] In view of this, the embodiments of this specification provide a micro-vibration on-orbit measurement system for spacecraft. One or more embodiments of this specification also relate to a micro-vibration on-orbit measurement data processing method, a micro-vibration on-orbit measurement data processing device, a computing device, a computer-readable storage medium and a computer program to solve the technical defects existing in the prior art.

[0005] According to a first aspect of an embodiment of this specification, there is provided an on-orbit micro-vibration measurement system for a spacecraft, comprising: An acceleration sensor module is used to obtain an acceleration signal and determine acceleration information based on the acceleration signal; A signal conditioning module, used to supply power to the acceleration sensor module, obtain acceleration information and temperature information of the acceleration sensor module, and condition the acceleration information and temperature information; A rotation measurement module is used to obtain angular vibration signals and angular vibration information; The control storage module is used to communicate with the spacecraft platform and control the signal conditioning module and the rotation measurement module, as well as receive and store data from the signal conditioning module and the rotation measurement module.

[0006] In a possible implementation, the acceleration sensing module includes an acceleration sensor and a temperature sensor.

[0007] In a possible implementation, the signal conditioning module includes a power supply unit, a control unit, and an acquisition unit; The power supply unit is used to supply power to the control unit and the acquisition unit, as well as the acceleration sensor module; The control unit is used to receive a synchronization signal for controlling the storage module, and control the acquisition unit to perform data acquisition based on the synchronization signal; The acquisition unit is used to receive the acceleration information and temperature information of the acceleration sensor module, and to condition the acceleration information and the temperature information.

[0008] In a possible implementation, the rotation measurement module includes a power conversion unit, a main control unit, and a sensor servo unit; The sensor unit is used to convert the primary power supply to obtain the secondary power supply, and to supply power to the main control unit and the sensor servo unit based on the secondary power supply; The main control unit is used to receive the synchronization signal of the control storage module and perform data acquisition according to the synchronization signal; The sensor servo unit is used to perform closed-loop control on the feedback loop of the sensor probe.

[0009] In a possible implementation, the control storage module includes a power supply and distribution unit and a data processing unit; The power supply and distribution unit is used to process and convert the primary power supply to obtain the secondary power supply, and supply power to the data processing unit based on the secondary power supply; The data processing unit is used to receive control signals from the spacecraft platform, maintain control status, collect data and send data.

[0010] In a possible implementation, the data processing unit includes an FPGA, a storage circuit, an AD acquisition circuit, and a 1553B bus communication circuit; The FPGA receives the control signal of the spacecraft platform through the 1553B bus communication circuit; wherein the control signal includes a data command signal and a time code signal; FPGA acquires data from the signal conditioning module and the rotation measurement module through the AD acquisition circuit for internal telemetry; The FPGA stores the data of the signal conditioning module and the rotation measurement module into the storage circuit, and reads the data based on the data instruction signal.

[0011] According to a second aspect of an embodiment of this specification, a method for processing micro-vibration on-orbit measurement data is provided, which is applied to a micro-vibration on-orbit measurement system of a spacecraft as described above, comprising: Set the data acquisition mode and downlink section, based on the on-orbit instructions and data storage section, perform data acquisition and downlink by controlling the storage module, determine the initial data, and send the initial data to the ground data processing end; The ground data processing end numbers the downloaded data based on the initial data and stores it in the corresponding working condition folder to obtain pre-processed data; The ground data processing end performs data decoding, data conversion to physical quantities, data coordinate direction conversion and data temperature correction based on the preprocessed data to obtain the target data.

[0012] According to a third aspect of the embodiments of this specification, a micro-vibration on-orbit measurement data processing device is provided, comprising: The data acquisition module is configured to set a series of on-orbit instructions and data routing, based on the on-orbit instructions and data routing, collect and transmit data through the control storage module, determine initial data, and send the initial data to the ground data processing end; The data sorting module is configured to perform downlink data numbering based on the initial data at the ground data processing end, and store the data in the corresponding working condition folder to obtain pre-processed data; The data processing module is configured to perform data decoding, data conversion to physical quantity, data direction conversion and data temperature correction on the ground data processing end based on the pre-processed data to obtain the target data.

[0013] According to a fourth aspect of an embodiment of this specification, a computing device is provided, including: Memory and processor; The memory is used to store computer executable instructions, and the processor is used to execute the computer executable instructions. When the computer executable instructions are executed by the processor, the steps of the above-mentioned micro-vibration on-orbit measurement data processing method are implemented.

[0014] According to a fifth aspect of the embodiments of this specification, a computer-readable storage medium is provided, which stores computer-executable instructions, and when the instructions are executed by a processor, the steps of the above-mentioned micro-vibration on-orbit measurement data processing method are implemented.

[0015] According to a sixth aspect of the embodiments of this specification, a computer program is provided, wherein when the computer program is executed in a computer, the computer is caused to execute the steps of the above-mentioned micro-vibration on-orbit measurement data processing method.

[0016] The embodiments of the present specification provide an on-orbit micro-vibration measurement system and data processing method for a spacecraft, wherein the system includes: an acceleration sensing module, used to obtain an acceleration signal and determine acceleration information based on the acceleration signal; a signal conditioning module, used to power the acceleration sensing module, obtain the acceleration information and temperature information of the acceleration sensing module, and condition the acceleration information and temperature information; a rotation measurement module, used to obtain an angular vibration signal and determine the angular vibration information based on the angular vibration signal; a control storage module, used to communicate with the spacecraft platform and control the acceleration sensing module, the signal conditioning module and the rotation measurement module, and receive and store data from the acceleration sensing module, the signal conditioning module and the rotation measurement module. Due to the modular design, the load position can be flexibly arranged, and interference isolation can be set between the modules, thereby improving the accuracy of the data and the measurement precision. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the architecture of an on-orbit micro-vibration measurement system for a spacecraft provided by an embodiment of this specification; Figure 2 This is a connection diagram of an on-orbit micro-vibration measurement system for a spacecraft provided by an embodiment of this specification; Figure 3 This is a first schematic diagram of a signal conditioning module of an on-orbit micro-vibration measurement system for a spacecraft provided by an embodiment of this specification; Figure 4 This is a second schematic diagram of a signal conditioning module of an on-orbit micro-vibration measurement system for a spacecraft provided by an embodiment of this specification; Figure 5 This is a third schematic diagram of a signal conditioning module of an on-orbit micro-vibration measurement system for a spacecraft provided by an embodiment of this specification; Figure 6 This is a schematic diagram of an acceleration sensor module of an on-orbit micro-vibration measurement system for a spacecraft provided by an embodiment of this specification; Figure 7 This is a schematic diagram of a control storage module of an on-orbit micro-vibration measurement system for a spacecraft provided by an embodiment of this specification; Figure 8 This is a schematic diagram of the working mode of an on-orbit micro-vibration measurement system for a spacecraft provided by an embodiment of this specification; Fig. 9 is a flow chart of a method for processing micro-vibration on-orbit measurement data provided by an embodiment of this specification; Fig.10 It is a structural schematic diagram of a micro-vibration on-orbit measurement data processing device provided by an embodiment of this specification; Fig.11It is a structural block diagram of a computing device provided by an embodiment of this specification. DETAILED DESCRIPTION

[0018] Many specific details are described in the following description to facilitate a full understanding of this specification. However, this specification can be implemented in many other ways than those described herein, and those skilled in the art can make similar generalizations without violating the connotation of this specification, so this specification is not limited to the specific implementation disclosed below.

[0019] The terms used in one or more embodiments of this specification are only for the purpose of describing specific embodiments, and are not intended to limit one or more embodiments of this specification. The singular forms of "a" and "the" used in one or more embodiments of this specification and the appended claims are also intended to include plural forms, unless the context clearly indicates other meanings. It should also be understood that the term "and / or" used in one or more embodiments of this specification refers to and includes any or all possible combinations of one or more associated listed items.

[0020] It should be understood that although the terms first, second, etc. may be used to describe various information in one or more embodiments of this specification, this information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of one or more embodiments of this specification, the first may also be referred to as the second, and similarly, the second may also be referred to as the first. Depending on the context, the word "if" as used herein may be interpreted as "at the time of" or "when" or "in response to determining".

[0021] In this specification, a micro-vibration on-orbit measurement system for a spacecraft is provided. One or more embodiments of this specification also relate to a micro-vibration on-orbit measurement data processing method, a micro-vibration on-orbit measurement data processing device, a computing device, a computer-readable storage medium, and a computer program, which are described in detail one by one in the following embodiments.

[0022] See also Figure 1 , Figure 1 A schematic diagram of the architecture of an on-orbit micro-vibration measurement system for a spacecraft provided according to an embodiment of the present specification is shown.

[0023] Among them, the acceleration sensing module is used to obtain the acceleration signal and determine the acceleration information based on the acceleration signal; the signal conditioning module is used to power the acceleration sensing module, obtain the acceleration information and temperature information of the acceleration sensing module, and condition the acceleration information and temperature information; the rotation measurement module is used to obtain the angular vibration signal and determine the angular vibration information based on the angular vibration signal; the control storage module is used to communicate with the spacecraft platform and control the acceleration sensing module, the signal conditioning module and the rotation measurement module, and receive and store data from the acceleration sensing module, the signal conditioning module and the rotation measurement module.

[0024] For details, see Figure 2 , Figure 2 is a connection diagram of the system, which may include an acceleration sensing module 1 , a signal conditioning module 2 , a control storage module 3 , a rotation measurement module 4 , a spacecraft platform 5 and a large camera 6 .

[0025] In actual applications, 16 acceleration sensor modules are installed on different vibration transmission paths of large spacecraft and directly connected to nearby signal conditioning modules. One signal conditioning module can connect to four acceleration sensor modules. The analog signal output by the acceleration sensor module to the signal conditioning module is conditioned locally, and the signal conditioning module transmits the conditioned digital quantity to the control storage module for storage. At the same time, the control storage module supplies power to the two rotation measurement modules, and the analog quantity of the rotation measurement module is directly transmitted to the control communication and storage module after local conditioning.

[0026] It should be noted that, in order to meet the requirements of high-precision micro-vibration acquisition, this embodiment uses a high-resolution acceleration sensor to form an acceleration sensing module, and uses a high-resolution spatial quad-frequency laser gyroscope as an angular vibration sensor of the rotation measurement module.

[0027] In a possible implementation, the acceleration sensing module includes an acceleration sensor and a temperature sensor.

[0028] In practical applications, the acceleration sensor module consists of a mounting base, three high-resolution acceleration sensors, three electrical connectors for acceleration sensors, one temperature measurement electrical connector, and four temperature sensors. The acceleration sensor is designed to be floating at the installation location, and the signal ground and the chassis ground are short-circuited at the signal conditioning module. According to the selected acceleration sensor, the structural form of the mounting base is determined, and the envelope size, total weight, natural frequency, electrical connector, and on-board installation method of the mounting base and acceleration sensor combination should meet the requirements.

[0029] Since the temperature variation range on orbit is large, the impact of temperature change on measurement accuracy must be considered. The impact of temperature change on the sensor is manifested as a deviation in measurement sensitivity. The present invention adopts a synchronous temperature measurement and re-compensation method to ensure test accuracy. Synchronous temperature measurement refers to measuring the temperature of the sensor while measuring the micro-vibration response. Re-compensation refers to transmitting the temperature data and micro-vibration data back to the ground together, and then performing data compensation correction on the ground according to the corresponding relationship between temperature and sensitivity. The above process is to determine the acceleration information.

[0030] In one possible implementation, the signal conditioning module includes a power supply unit, a control unit and an acquisition unit; the power supply unit is used to supply power to the control unit and the acquisition unit, as well as the acceleration sensing module; the control unit is used to receive a synchronization signal that controls the storage module, and controls the acquisition unit to perform data acquisition based on the synchronization signal; the acquisition unit is used to receive acceleration information and temperature information from the acceleration sensing module, and condition the acceleration information and temperature information.

[0031] In practical applications, see Figure 3 The signal conditioning module is a single-piece design, which is mainly composed of three modules, namely the power supply module, the control module and the acquisition module, namely the power supply unit, the control unit and the acquisition unit mentioned above. The acquisition module mainly provides constant current power for the sensor, and conditions (amplifies and filters) and converts the output signal of the sensor into analog-to-digital signals, where SDI is the input interface, SDO is the output interface, SCK is the clock interface, and CNV is the conversion interface; the control module is responsible for receiving the sampling clock synchronization signal sent by the control communication and storage module and sending it to the acquisition module, and at the same time receiving the sampled data processed by the AD chip (in the acquisition module). The sampled data is finally sent to the micro-vibration measurement signal control communication and storage module through the LVDS interface (control module). The power supply and control modules are each 1 circuit board, and the acquisition module is 2 circuit boards, totaling 4 circuit boards.

[0032] Furthermore, in order to maintain the acquisition accuracy and resolution, the circuit adopts multi-stage transformation. A fuse protection circuit is set at the power inlet, and the protection circuit adopts the fuse parallel form to avoid causing a permanent short circuit of the platform power bus. The surge suppression circuit adopts the form of a soft start circuit, which is composed of a PMOS tube, a resistor and a capacitor. It has the advantages of high reliability, low static power consumption and simple circuit implementation. In order to improve the reliability of the surge suppression circuit and avoid the loss of backup due to a circuit breaker failure in the soft start circuit, the surge suppression circuit adopts a parallel design.

[0033] See also Figure 4The power supply interface of the acceleration sensor is an IEPE interface, so a constant current source circuit is designed. The +28V power supply is converted into a +24V output for the sensor using LDCD / (20-50)-12-15F / D1, and a 3~5mA constant current source excitation is provided to the sensor. The voltage signal output by the sensor is a dynamic signal superimposed on the 8~12V DC component.

[0034] See also Figure 5 , power supply noise greatly affects the accuracy of analog-to-digital conversion. To reduce the impact of DCDC output ripple on the acquisition circuit, LM117 / LM137 is used to convert the ±12V output of DCDC to ±6V for use in the acquisition circuit. AD also uses a separate LDO to convert +12V to +5V and +2.5V power. The chip power supply uses 0.01uF, 0.1uF, and 2.2uF ground capacitors to filter noise of different frequencies, and a 100uF ground capacitor is added to the power supply end of the acquisition board to filter out low-frequency noise.

[0035] Furthermore, in the process from the generation of sensor signals to the transmission to the acquisition module for data acquisition, it is inevitable that high-frequency interference signals will be aliased in the useful signals. When the frequency of these signals exceeds the range specified by the sampling theorem, some uncertain signals will be collected and interfere with the useful signals, which is called frequency aliasing. In order to minimize or eliminate the influence of aliasing on the dynamic signal acquisition of the acquisition and storage module, it is necessary to perform anti-aliasing filtering on the electrical signals output by the sensor to attenuate and filter out useless or interfering signals.

[0036] Furthermore, the filter circuit uses a Butterworth low-pass filter, the frequency response curve of which is maximally flat in its passband, with very little fluctuation, and gradually drops to zero in the stopband. The filter specifically uses a 5th-order Butterworth low-pass filter, which has a fast attenuation speed in the stopband and has a good anti-aliasing effect.

[0037] Furthermore, the analog input of the AD is in differential form, and the input signal is conditioned to condition the single-ended waveform signal into a suitable differential signal.

[0038] In one possible implementation, the rotation measurement module includes a power conversion unit, a main control unit and a sensor servo unit; the sensor unit is used to convert the primary power supply to obtain the secondary power supply, and power the main control unit and the sensor servo unit based on the secondary power supply; the main control unit is used to receive the synchronization signal of the control storage module, and perform data acquisition according to the synchronization signal; the sensor servo unit is used to perform closed-loop control on the feedback loop of the sensor probe.

[0039] In practical applications, see Figure 6, the number of main control boards is 1, the main control board is the above-mentioned main control unit, its function is to perform task scheduling management, coordinate the normal operation of each module, collect angular displacement signals and process data according to the synchronous clock signal, and send data through the LVDS interface. The main function of FPGA is to receive instructions and clock synchronization signals through the LVDS interface, calculate the TTL pulses output by the sensor servo board, the resolution frequency is 100MHz, judge the sensor health signal, package the measurement data, and send the measurement data and telemetry data through the LVDS interface, where the sensor servo board is the sensor servo unit. The number of power supply and distribution boards is 1, single design, the power supply and distribution board is the above-mentioned power conversion unit, the main function is to convert 28V power into secondary power for equipment use, in the secondary power supply, the main control board needs +5V power supply (3W), the sensor servo board, high-voltage board, and preamplifier board need ±5V and +15V power supplies. The number of sensor servo boards is 1, single design, based on volume, power consumption and other considerations, the servo control of the three sensor probes uses a servo control circuit. The main function of the sensor servo board is to perform closed-loop control on the feedback loops of the three sensor probes, provide a stable frequency drive signal to keep the resonant cavity length of the sensor probe stable, and convert the analog signal output by the sensor probe into a frequency modulated square wave output. The above process is to determine the angular vibration information.

[0040] Furthermore, there is one high-voltage board, which is designed as a single unit. Its function is to provide high-voltage power supply for three sensor probes and gain for the laser through a high-voltage current stabilization circuit. This part of the circuit uses a single-ended flyback DC / DC converter based on a current feedback PWM controller to achieve high-voltage output. There are three preamplifier boards, each corresponding to one sensor probe, and all are designed as a single unit. The main function of the preamplifier board is to amplify and condition the current signal output by the photoelectric converter into a suitable voltage signal for subsequent processing. Part of the signal is used for frequency stabilization control and power monitoring, and the other part of the signal is the analog signal of the gyroscope output to the sensor servo board, which is converted into a frequency-modulated wave signal output.

[0041] In one possible implementation, the control storage module includes a power supply and distribution unit and a data processing unit; the power supply and distribution unit is used to process and convert the primary power supply to obtain the secondary power supply, and power the data processing unit based on the secondary power supply; the data processing unit is used to receive control signals of the spacecraft platform, maintain the control status, collect data and send data.

[0042] In practical applications, see Figure 7 The control storage module consists of two types of sub-modules, namely the control sub-module and the power supply and distribution electronic module. The control sub-module is the data processing unit, and the power supply and distribution electronic module is the power supply and distribution unit. Considering the improvement of reliability, the default is the primary-backup design, and the primary-backup functions of each module are completely consistent.

[0043] The control storage module is composed of FPGA, CPU, EEPROM, AD acquisition, LVDS circuit, Ethernet interface circuit, 1553B interface circuit, relay instruction drive circuit, reset circuit, clock circuit, power conversion circuit, etc.

[0044] A fuse protection circuit is set at the busbar entrance, and the busbar control relay uses a magnetic latching relay. The main and backup power supply boards are each equipped with a filter and a power module to convert the primary voltage 100V into +5V and ±12V for use by the control storage module. The filter has a surge suppression circuit, so there is no need to design a surge suppression circuit separately in the circuit. In addition, the DC / DC circuit of the control storage module converts the busbar 100V into 28V as the power supply for the lower load.

[0045] In the specific implementation, the control storage module main / backup power supply distribution unit board receives the primary power supply +100V. The primary power supply +100V is controlled by the input program control instruction. After the primary power is turned on, it passes through the fuse, surge suppression circuit, and EMI filter, and then obtains the secondary power supply +5V, ±12V through DC / DC conversion for use by the control communication and storage module main board.

[0046] Furthermore, in order to deal with the single-particle upset problem of SRAM-based FPGA, an FPGA dynamic refresh configuration area strategy is adopted. An anti-fuse FPGA is added between the main FPGA and the configuration data storage PROM device. The anti-fuse FPGA acts as the configuration controller of the main FPGA and is responsible for global configuration or dynamic refresh of the main FPGA.

[0047] To improve reliability, storage array management supports the removal of damaged chips. When any one or more chips in the storage array are damaged (or there are too many bad blocks, etc.), they can be removed from the storage array and no longer used.

[0048] The control storage module needs to complete the acquisition of telemetry analog quantities of itself and the lower load, so an analog switch + AD conversion is designed to achieve this. The analog quantity conditioning circuit uses an operational amplifier to implement an emitter-follower circuit, adjusts the analog quantity output impedance to a low-resistance state, and uses the high input impedance of the operational amplifier to ensure a high common-mode rejection ratio of the acquisition circuit, suppressing interference from other signals other than the measured parameters.

[0049] In one possible implementation, the data processing unit includes an FPGA, a storage circuit, an AD acquisition circuit and a 1553B bus communication circuit; the FPGA receives a control signal from the spacecraft platform through the 1553B bus communication circuit; wherein the control signal includes a data command signal and a time code signal; the FPGA obtains data from the signal conditioning module and the rotation measurement module through the AD acquisition circuit to perform internal telemetry; the FPGA stores the data from the signal conditioning module and the rotation measurement module in the storage circuit, and reads the data based on the data command signal.

[0050] In practical applications, FPGA, storage circuit, AD acquisition circuit, 1553B bus communication circuit and other circuits include the following specific functions.

[0051] 1) FPGA Receive data instructions and time code and other signals injected by the platform through 1553B; Send telemetry data via 1553B interface protocol; generating a relay driving command signal according to the injected command; Sending synchronous sampling signal; Control multi-channel analog switches and AD acquisition devices to complete AD acquisition function (internal telemetry); Receive detection data of each load unit through LVDS interface; FPGA completes the data combination storage function from signal conditioning modules 1, 2, 3, 4, rotation measurement modules 1 and 2; the function of replaying and reading data in FLASH according to the above data instructions; bad block management of large-capacity FLASH; EEPROM read and write functions; 2) Large-capacity storage FLASH is used for large-capacity storage. The main function of EEPROM is to store the "read" and "write" addresses of FLASH units, which can be automatically loaded after each power-on to improve processing speed and reliability.

[0052] 3) Collection circuit Under the control of FPGA, AD acquisition is completed for the input multi-channel analog signals, and general voltage telemetry / temperature telemetry signals are completed. 4) LVDS circuit The main function is to convert the CMOS signal output by the FPGA into a differential signal at the LVDS level.

[0053] 5) Relay command drive circuit Used to convert the CMOS signal output by FPGA into OC signal output.

[0054] 6) Power conversion circuit The power conversion circuit is used to convert the +5V voltage into +3.3V and +1.5V, where +3.3V is used for the logic interface circuit (including the FPGA's IO port) and +1.5V is the FPGA core voltage.

[0055] 7) 1553B interface 1553B protocol communication.

[0056] 8) Timed refresh The control storage module adopts partial reconfiguration (refresh) to enhance the reliability against single-particle events, adopts triple-module redundancy design for the fault-tolerant target FPGA to alleviate SEU, and implements periodic refresh operation to prevent SEU accumulation.

[0057] It should be noted that see Figure 8 In this embodiment, the control storage module has four working modes, namely self-test mode, standby mode, measurement mode and download mode. The control communication and storage module enters the self-test mode by default when powered on, and enters the standby mode after the self-test is completed.

[0058] In the self-test mode, only the control communication and storage module is powered on, and the other load units are not powered on. The control communication and storage module enters the self-test mode by default after powering on. In the self-test mode, the status of each module of the host is mainly tested, and the standby mode is entered after the self-test is completed.

[0059] In standby mode, the tasks completed by the control communication and storage module include: (1) receiving the time code and injection data sent by the platform through 1553B; (2) maintaining the status of the control communication and storage module itself, including the large-capacity storage unit, AD acquisition unit, time code calibration, etc.; (3) collecting engineering parameters and analog data, and regularly sending the current telemetry status of the control communication and storage module.

[0060] The measurement mode is to start the measurement and store data according to the instructions. The completed tasks include: (1) receiving the time code and injection data sent by the platform through 1553B; (2) maintaining the status of the control communication and storage module itself, including the large-capacity storage unit, AD acquisition unit, time code calibration, etc.; (3) collecting engineering parameters and analog data, and sending the current telemetry status regularly; (4) sending synchronous acquisition control to the lower-level payload; (5) receiving the micro-vibration measurement data of the lower-level payload and packaging and storing it.

[0061] In the download mode, after receiving the instruction allowing download, the FPGA is controlled to read the measurement data from the specified address of FLASH and send the measurement data to the platform via Ethernet.

[0062] The embodiments of the present specification provide an on-orbit micro-vibration measurement system and data processing method for a spacecraft, wherein the system includes: an acceleration sensing module, used to obtain acceleration signals and determine acceleration information based on the acceleration signals; a signal conditioning module, used to power the acceleration sensing module, obtain acceleration information and temperature information of the acceleration sensing module, and condition the acceleration information and temperature information; a rotation measurement module, used to obtain angular vibration signals and determine angular vibration information based on the angular vibration signals; a control storage module, used to communicate with the spacecraft platform and control the signal conditioning module and the rotation measurement module, and receive and store data from the signal conditioning module and the rotation measurement module. Due to the modular design, the load position can be flexibly arranged, and interference isolation can be set between the modules, thereby improving the accuracy of the data and the measurement precision.

[0063] See also Fig. 9 , Fig. 9 A flow chart of a method for processing micro-vibration on-orbit measurement data provided according to an embodiment of the present specification is shown, which is applied to a micro-vibration on-orbit measurement system of a spacecraft as described above, and specifically includes the following steps.

[0064] Step 901: setting a data collection interval, performing data collection by controlling a storage module based on the data collection interval, determining initial data, and sending the initial data to a ground data processing terminal; Step 902: The ground data processing terminal performs downlink data numbering based on the initial data and stores it in the corresponding working condition folder to obtain pre-processed data; Step 903: The ground data processing end performs data decoding, data conversion to physical quantity, data direction conversion and data temperature correction based on the pre-processed data to obtain target data.

[0065] In practical applications, during the ground test of the spacecraft, thousands of micro-vibration on-orbit tests and data transmission under various working conditions need to be completed. The automatic collection and transmission functions are designed on the ground software side. The application method is as follows: 1) Use the 1553B command of the load, set the automatic completion interval according to the test conditions, and automatically send the collection preparation, collection start, collection end, data download and other commands according to the set interval.

[0066] 2) In terms of ground data reception, the software function can automatically create working condition folders, automatically number the downloaded data, and automatically record data collection logs; 3) In terms of ground data analysis, according to the coordinates of the measurement points and the measured temperature, the system automatically completes measurement data decoding, data conversion to physical quantities, data coordinate direction conversion, and data temperature correction.

[0067] The embodiments of this specification realize automatic data collection and downloading during spacecraft testing through the design of ground control software, thereby improving research and development efficiency.

[0068] Corresponding to the above method embodiment, this specification also provides an embodiment of a micro-vibration on-orbit measurement data processing device, Fig. 9 FIG. 1 is a schematic diagram showing the structure of a micro-vibration on-orbit measurement data processing device provided by an embodiment of the present specification. Fig. 9 As shown, the device comprises: The data acquisition module 1001 is configured to set a data acquisition interval, perform data acquisition based on the data acquisition interval by controlling the storage module, determine initial data, and send the initial data to the ground data processing terminal; The data sorting module 1002 is configured to perform downlink data numbering based on the initial data at the ground data processing end, and store the data in the corresponding working condition folder to obtain pre-processed data; The data processing module 1003 is configured to perform data decoding, data conversion to physical quantity, data direction conversion and data temperature correction on the ground data processing end based on the pre-processed data to obtain the target data.

[0069] The above is a schematic scheme of a micro-vibration on-orbit measurement data processing device of this embodiment. It should be noted that the technical scheme of the micro-vibration on-orbit measurement data processing device and the technical scheme of the above-mentioned micro-vibration on-orbit measurement data processing method belong to the same concept, and the details not described in detail in the technical scheme of the micro-vibration on-orbit measurement data processing device can be referred to the description of the technical scheme of the above-mentioned micro-vibration on-orbit measurement data processing method.

[0070] Fig.11 The block diagram of a computing device 1100 according to one embodiment of the present specification is shown. The components of the computing device 1100 include but are not limited to a memory 1110 and a processor 1120. The processor 1120 is connected to the memory 1110 via a bus 1130, and a database 1150 is used to store data.

[0071] The computing device 1100 also includes an access device 1140 that enables the computing device 1100 to communicate via one or more networks 1160. Examples of these networks include a public switched telephone network (PSTN), a local area network (LAN), a wide area network (WAN), a personal area network (PAN), or a combination of communication networks such as the Internet. The access device 1140 may include one or more of any type of network interface (e.g., a network interface card (NIC)) of wired or wireless, such as an IEEE 802.11 wireless local area network (WLAN) wireless interface, a world-wide interoperability for microwave access (Wi-MAX) interface, an Ethernet interface, a universal serial bus (USB) interface, a cellular network interface, a Bluetooth interface, and a near field communication (NFC).

[0072] In one embodiment of the present specification, the above components of the computing device 1100 and Fig.11 Other components not shown in the figure may also be connected to each other, for example, via a bus. It should be understood that Fig.11 The computing device structure block diagram shown is only for the purpose of illustration, and is not intended to limit the scope of this specification. Those skilled in the art can add or replace other components as needed.

[0073] The computing device 1100 may be any type of stationary or mobile computing device, including a mobile computer or mobile computing device (e.g., a tablet computer, a personal digital assistant, a laptop computer, a notebook computer, a netbook, etc.), a mobile phone (e.g., a smart phone), a wearable computing device (e.g., a smart watch, smart glasses, etc.), or other types of mobile devices, or a stationary computing device such as a desktop computer or a personal computer (PC). The computing device 1100 may also be a mobile or stationary server.

[0074] Among them, the processor 1120 is used to execute the following computer executable instructions, which, when executed by the processor, implement the steps of the above-mentioned micro-vibration on-orbit measurement data processing method. The above is a schematic scheme of a computing device of this embodiment. It should be noted that the technical scheme of the computing device and the technical scheme of the above-mentioned micro-vibration on-orbit measurement data processing method belong to the same concept. For details not described in detail in the technical scheme of the computing device, please refer to the description of the technical scheme of the above-mentioned micro-vibration on-orbit measurement data processing method.

[0075] An embodiment of the present specification further provides a computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, implement the steps of the above-mentioned micro-vibration on-orbit measurement data processing method.

[0076] The above is a schematic scheme of a computer-readable storage medium of this embodiment. It should be noted that the technical scheme of the storage medium and the technical scheme of the above-mentioned micro-vibration on-orbit measurement data processing method belong to the same concept, and the details not described in detail in the technical scheme of the storage medium can be referred to the description of the technical scheme of the above-mentioned micro-vibration on-orbit measurement data processing method.

[0077] An embodiment of the present specification further provides a computer program, wherein when the computer program is executed in a computer, the computer is caused to execute the steps of the above-mentioned micro-vibration on-orbit measurement data processing method.

[0078] The above is a schematic scheme of a computer program of this embodiment. It should be noted that the technical scheme of the computer program and the technical scheme of the above-mentioned micro-vibration on-orbit measurement data processing method belong to the same concept, and the details not described in detail in the technical scheme of the computer program can be referred to the description of the technical scheme of the above-mentioned micro-vibration on-orbit measurement data processing method.

[0079] The above is a description of a specific embodiment of the specification. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in an order different from that in the embodiments and still achieve the desired results. In addition, the processes depicted in the drawings do not necessarily require the specific order or continuous order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0080] The computer instructions include computer program codes, which may be in source code form, object code form, executable files or some intermediate forms, etc. The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording medium, USB flash drive, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electric carrier signal, telecommunication signal and software distribution medium, etc. It should be noted that the content contained in the computer-readable medium may be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable media do not include electric carrier signals and telecommunication signals.

[0081] It should be noted that, for the convenience of description, the aforementioned method embodiments are all described as a series of action combinations, but those skilled in the art should be aware that the embodiments of this specification are not limited by the order of the actions described, because according to the embodiments of this specification, some steps can be performed in other orders or simultaneously. Secondly, those skilled in the art should also be aware that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily required by the embodiments of this specification.

[0082] In the above embodiments, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0083] The preferred embodiments of this specification disclosed above are only used to help explain this specification. The optional embodiments do not describe all the details in detail, nor do they limit the invention to only the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of the embodiments of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the embodiments of this specification, so that technicians in the relevant technical field can well understand and use this specification. This specification is only limited by the claims and their full scope and equivalents.

Claims

1. A micro-vibration on-orbit measurement system for a spacecraft, characterized in that: include: An acceleration sensing module, used to obtain an acceleration signal and determine acceleration information based on the acceleration signal; A signal conditioning module, used to supply power to the acceleration sensing module, obtain acceleration information and temperature information of the acceleration sensing module, and condition the acceleration information and the temperature information; A rotation measurement module, used to obtain an angular vibration signal and determine angular vibration information based on the angular vibration signal; The control storage module is used to communicate with the spacecraft platform and control the signal conditioning module and the rotation measurement module, and receive and store data from the signal conditioning module and the rotation measurement module.

2. The micro-vibration on-orbit measurement system for spacecraft according to claim 1, characterized in that: The acceleration sensing module includes an acceleration sensor and a temperature sensor.

3. The micro-vibration on-orbit measurement system for spacecraft according to claim 1, characterized in that: The signal conditioning module includes a power supply unit, a control unit and an acquisition unit; The power supply unit is used to supply power to the control unit and the acquisition unit, as well as the acceleration sensor module; The control unit is used to receive the synchronization signal of the control storage module, and control the acquisition unit to perform data acquisition based on the synchronization signal; The acquisition unit is used to receive the acceleration information and the temperature information of the acceleration sensor module, and to condition the acceleration information and the temperature information.

4. The micro-vibration on-orbit measurement system for spacecraft according to claim 1, characterized in that: The rotation measurement module includes a power conversion unit, a main control unit and a sensor servo unit; The sensor unit is used to convert the primary power supply to obtain the secondary power supply, and supply power to the main control unit and the sensor servo unit based on the secondary power supply; The main control unit is used to receive the synchronization signal of the control storage module and perform data acquisition according to the synchronization signal; The sensor servo unit is used to perform closed-loop control on the feedback loop of the sensor probe.

5. The micro-vibration on-orbit measurement system for spacecraft according to claim 1, characterized in that: The control storage module includes a power supply and distribution unit and a data processing unit; The power supply and distribution unit is used to process and convert the primary power supply to obtain the secondary power supply, and supply power to the data processing unit based on the secondary power supply; The data processing unit is used to receive control signals from the spacecraft platform, maintain control status, collect data and send data.

6. The micro-vibration on-orbit measurement system for spacecraft according to claim 5, characterized in that: The data processing unit includes FPGA, storage circuit, AD acquisition circuit and 1553B bus communication circuit; The FPGA receives a control signal from a spacecraft platform through the 1553B bus communication circuit; wherein the control signal includes a data instruction signal and a time code signal; The FPGA acquires data from the signal conditioning module and the rotation measurement module through the AD acquisition circuit to perform internal telemetry; The FPGA stores the data of the signal conditioning module and the rotation measurement module in the storage circuit, and reads the data based on the data instruction signal.

7. A method for processing micro-vibration on-orbit measurement data, characterized in that: An on-orbit micro-vibration measurement system for a spacecraft according to any one of claims 1 to 6, comprising: Setting a data collection interval, performing data collection by controlling a storage module based on the data collection interval, determining initial data, and sending the initial data to a ground data processing terminal; The ground data processing terminal performs downlink data numbering based on the initial data and stores the data in a corresponding working condition folder to obtain pre-processed data; The ground data processing end performs data decoding, data conversion to physical quantity, data coordinate direction conversion and data temperature correction based on the pre-processed data to obtain target data.

8. A micro-vibration on-orbit measurement data processing device, characterized in that: include: A data acquisition module is configured to set a data acquisition interval, perform data acquisition based on the data acquisition interval by controlling the storage module, determine initial data, and send the initial data to a ground data processing terminal; A data sorting module is configured to cause the ground data processing end to perform downlink data numbering based on the initial data and store the data in a corresponding working condition folder to obtain pre-processed data; The data processing module is configured to perform data decoding, data conversion to physical quantity, data coordinate direction conversion and data temperature correction on the ground data processing end based on the pre-processed data to obtain target data.

9. A computing device, characterized in that include: Memory and processor; The memory is used to store computer executable instructions, and the processor is used to execute the computer executable instructions. When the computer executable instructions are executed by the processor, the steps of the micro-vibration on-orbit measurement data processing method according to claim 7 are implemented.

10. A computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, implement the steps of the micro-vibration on-orbit measurement data processing method according to claim 7.

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