Multi-channel temperature acquisition and analysis system based on aerospace sensor system

Abstract

The invention discloses a multichannel temperature acquisition and analysis system based on a spaceflight sensor system, and relates to the technical field of heat measurement. Comprising spaceflight sensors, the multiple spaceflight sensors are combined and assembled inside and outside a spacecraft and used for capturing data inside and outside the spacecraft, and a data transmission channel is composed of any two of the multiple spaceflight sensors and used for transmitting data. By analyzing the heat energy data collected by different aerospace sensors inside and outside the spacecraft and comprehensively considering the structural parameters, the heat energy duration and the heat energy change frequency of the spacecraft, intelligent opening and closing of a data transmission channel are achieved, the deviation and lag phenomena of temperature data in the transmission process are reduced, and the reliability of the system is improved. The synchronization of coordination work between the aerospace sensors is guaranteed to a certain extent, and the accuracy and the real-time performance of the aerospace sensors on overall temperature data analysis are indirectly enhanced.

Description

Technical Field

[0001] The invention relates to the technical field of heat measurement, and in particular to a multi-channel temperature acquisition and analysis system based on an aerospace sensor system. Background Art

[0002] Due to the rapid development of aerospace technology, spacecraft plays an increasingly important role in space exploration, communication, navigation and other fields. However, when a spacecraft is operating in space, its temperature state has an important impact on its performance and life. Traditional temperature monitoring methods can often only measure at a single point and cannot fully reflect the temperature state of the spacecraft. In addition, the accuracy and efficiency are low. Therefore, in order to meet the spacecraft's demand for accurate and comprehensive temperature monitoring, a multi-channel temperature acquisition and analysis system based on aerospace sensor systems came into being.

[0003] After searching, the Chinese invention patent with publication number "CN118706289A" discloses "a multi-layer seawater temperature optimization acquisition and analysis system and method". This application can significantly improve the accuracy and reliability of seawater temperature data measurement by arranging multiple temperature sensors at different depths and adopting a multi-layer temperature synchronization optimization algorithm and a multi-layer seawater temperature dynamic correction algorithm; in addition, a multi-layer temperature synchronization optimization algorithm is introduced to synchronously optimize the original multi-layer seawater temperature data, thereby reducing the error between temperature sensors and improving the consistency of seawater temperature data; a multi-layer seawater temperature dynamic correction algorithm is introduced to further correct the optimized multi-layer seawater temperature data using the error matrix and correction coefficient to eliminate the impact of environmental changes and temperature sensor errors.

[0004] The Chinese invention patent with publication number "CN117589330A" discloses "a method for collecting and analyzing the temperature field data of the coke oven wall". This application automatically collects temperature data, and the temperature of the entire furnace wall can be measured within 1 day. The temperature measurement period is shorter than the previous 7 to 14 days, which is convenient for the heating system to adjust the gas volume in time, reduce furnace temperature fluctuations, avoid local overheating, protect the furnace body, save energy and reduce consumption, and reduce emissions. At the same time, it solves the problem that the high-level temperature of the coke oven carbonization chamber wall is difficult to evaluate in the past.

[0005] During the operation of the spacecraft, due to the temperature difference between the outside and inside of the spacecraft, the temperature data will deviate and lag in the transmission process. Although the methods and systems disclosed in the above patents have improved the efficiency and accuracy of temperature data collection and analysis to a certain extent, in actual applications, these technologies fail to ensure the synchronous and coordinated operation of the internal and external sensors of the spacecraft, which affects the accuracy and real-time performance of the spacecraft's overall temperature data analysis to a certain extent. Summary of the invention

[0006] The purpose of the present invention is to provide a multi-channel temperature acquisition and analysis system based on an aerospace sensor system to solve the problems raised in the above background technology.

[0007] To achieve the above object, the present invention provides the following technical solution: a multi-channel temperature acquisition and analysis system based on an aerospace sensor system, comprising: Space sensors: multiple space sensors are combined and installed inside and outside the spacecraft and are used to capture data inside and outside the spacecraft; A data transmission channel, formed by any two aerospace sensors among the plurality of aerospace sensors, for transmitting data; The real-time temperature recording module is embedded in the aerospace sensor and is used to match the temperature data and time series recorded by the aerospace sensor, and after leaving the backup data, the recorded temperature data and time series are packaged into a data packet and sent to the data transmission channel; A frequency acquisition module, embedded in the aerospace sensor and matched with the real-time temperature recording module, is used to acquire the frequency of the aerospace sensor when collecting data, and attach the frequency data to the outside of the data packet to form a suffix of the data packet; A data packet coordination module is provided in the data transmission channel, and is used to temporarily store data packets acquired at both ends of the data transmission channel, and classify the data packets based on the suffixes of the data packets; a channel closure unit, embedded in the data packet coordination module, and selectively opening connectivity of the data channel based on any of the length of the data transmission channel, the speed at which the data packet is placed in the data transmission channel, and the content of the data packet; The transmission unit is selected and configured in the data transmission channel. It is responsible for feeding back the data packets captured in the data transmission channel to the aerospace sensors at both ends of the data transmission channel according to the data transmission channel enabled by the channel closing unit, ensuring that the aerospace sensors at both ends send the collected data packets synchronously to the aerospace sensor system.

[0008] As a further preferred embodiment of the present technical solution, under the scene constraints, the positions of the aerospace sensors at both ends of the data transmission channel in the spacecraft are not fixed; In the scenario of spacecraft external temperature monitoring, the space sensors at both ends of the data transmission channel are deployed at different positions on the outer surface of the spacecraft. When the channel closing unit obtains the temperature difference on the outer surface of the spacecraft based on the data packet, the channel closing unit selectively opens the data transmission channel based on the temperature gradient to preferentially transmit the data packets with the temperature difference. For the scenario of temperature monitoring inside the spacecraft, the aerospace sensors at both ends of the data transmission channel are placed at different positions inside the spacecraft. The channel closing unit selectively opens the data transmission channel based on the frequency of temperature data obtained by the aerospace sensors and the control instructions of the temperature control system inside the spacecraft. In the monitoring scenario where the external temperature of the spacecraft affects the internal temperature, the aerospace sensors at both ends of the data transmission channel are deployed on the outside and inside of the spacecraft respectively. Through the synergy of the temperature difference analysis unit and the channel closing unit, the collection and transmission strategy of the internal temperature data is adjusted when the external temperature of the spacecraft changes.

[0009] As a further preferred embodiment of the present technical solution, in a scenario for monitoring the external temperature of a spacecraft, the operation method of the channel closing unit includes: The temperature data recorded by any two aerospace sensors installed outside the spacecraft are collected and marked as first temperature data and second temperature data respectively; Acquire a vertical distance between aerospace sensors corresponding to the first temperature data and the second temperature data; According to the temperature gradient calculation formula, the calibration temperature gradient is calculated, and the calibration temperature gradient is the ratio of the difference between the first temperature data and the second temperature data to the vertical distance between the two; Substitute the average value of the temperature data recorded by the aerospace sensors outside the spacecraft and the vertical distance between the two aerospace sensors with the longest vertical distance outside the spacecraft into the temperature gradient calculation formula to calculate the temperature gradient threshold; The channel closing unit controls the connectivity of the data transmission channel based on the difference between the calibration temperature gradient and the temperature gradient threshold; If the calibration temperature gradient is greater than a preset temperature gradient threshold, the channel closing unit opens the data transmission channel; If the calibration temperature gradient is not greater than the preset temperature gradient threshold, the channel closing unit keeps the data transmission channel closed.

[0010] As a further preferred embodiment of the present technical solution, the calculation formula of the temperature gradient is: ;in Used to represent temperature gradient, It is used to represent the difference between the second temperature data and the first temperature data, that is, , Used to represent the vertical distance between the aerospace sensors corresponding to the second temperature data and the first temperature data.

[0011] As a further preferred embodiment of the present technical solution, in the scenario of temperature monitoring inside a spacecraft, the operation method of the channel closing unit includes: Collect temperature data recorded by various space sensors inside the spacecraft, and divide the temperature data into different data groups according to the installation position of the sensors inside the spacecraft; performing frequency analysis on the group temperature data to obtain frequency characteristics of the temperature data group; Compare the frequency characteristics of the temperature data set with the control instructions of the spacecraft's internal temperature control system; The channel closing unit selectively opens the data transmission channel based on the comparison result; If the frequency characteristic of the temperature data set is consistent with the control instruction, the channel closing unit selectively activates the data transmission channel based on the frequency characteristic of the temperature data set; If the frequency characteristic of the temperature data group is inconsistent with the control instruction, the channel closing unit keeps the data transmission channel closed.

[0012] As a further preferred embodiment of the present technical solution, a method for comparing the frequency characteristics of the temperature data set with the control instructions of the temperature control system inside the spacecraft includes: Optimize and adjust the control instructions of the temperature control system so that the control instructions form associated instructions that match the temperature fluctuations. The associated instructions include temperature range instructions and temperature change rate instructions. Perform quantitative analysis on the frequency characteristics of the acquired temperature data set and the associated instructions; Construct a matching model between frequency characteristics and associated instructions; The matching model includes a matching degree calculation model between the frequency characteristics of the temperature data set and the temperature range instruction and a matching degree calculation model between the frequency characteristics of the temperature data set and the temperature change rate instruction; The matching model assigns corresponding weights to the matching degree calculation model of the temperature data set frequency characteristics and the temperature range instruction and the matching degree calculation model of the temperature data set frequency characteristics and the temperature change rate instruction according to the mission performed by the spacecraft; Based on the assigned weights, a comparison result between the frequency characteristics of the temperature data set and the associated instructions is obtained.

[0013] As a further preferred embodiment of the present technical solution, the operating formula of the matching degree calculation model of the temperature data set frequency characteristic and the temperature range instruction includes: ;in Used to indicate the matching degree between the frequency characteristics of the temperature data set and the temperature range instruction; in is the indicator function, when Falling When the exponential function is within the range, the value of the exponential function is 1. Did not fall When it is within the range, the value of the exponential function is 0; in is the total number of temperature datasets.

[0014] As a further preferred embodiment of the present technical solution, the operating formula of the matching degree calculation model of the temperature data set frequency characteristic and the temperature change rate instruction includes: ;in It is used to indicate the matching degree between the frequency characteristic of the temperature data set and the temperature change rate instruction. The value of is between 0 and 1; in Used to indicate and The absolute distance between the values ​​and the instruction range, The value used to ensure the match is between 0 and 1.

[0015] As a further preferred embodiment of the present technical solution, in a monitoring scenario where the external temperature of a spacecraft affects the internal temperature, the method of the temperature difference analysis unit and the channel closing unit working in coordination includes: The temperature data recorded by the external and internal space sensors of the spacecraft are collected and marked as external temperature data and internal temperature data respectively; Calculate the temperature difference between the external temperature data and the internal temperature data; Setting a temperature difference threshold, which is artificially set based on the material properties of the spacecraft, external environmental factors, and the performance of the spacecraft's internal temperature control system; The temperature difference analysis unit compares the calculated temperature difference value with the set temperature difference threshold; If the temperature difference exceeds the temperature difference threshold, the temperature difference analysis unit triggers the channel closing unit to adjust the collection and transmission strategy of the internal temperature data; If the temperature difference value does not exceed the temperature difference threshold, the channel closing unit maintains the current data collection and transmission strategy unchanged.

[0016] Compared with the prior art, the present invention has the following beneficial effects: The multi-channel temperature acquisition and analysis system based on the aerospace sensor system analyzes the thermal energy data collected by different aerospace sensors inside and outside the spacecraft, and comprehensively considers the structural parameters, thermal energy duration and thermal energy change frequency of the spacecraft, so as to realize the intelligent opening and closing of the data transmission channel, reduce the redundancy of data transmission, improve the data transmission efficiency, and ensure the timely transmission and processing of key data. In addition, in actual operation, it also reduces the deviation and lag of temperature data in the transmission process, guarantees the synchronization of coordinated work between aerospace sensors to a certain extent, and indirectly enhances the accuracy and real-time performance of the overall temperature data analysis of aerospace sensors; It should be added that the present invention effectively monitors the impact of the external temperature of the spacecraft on the internal temperature through the coordinated work of the temperature difference analysis unit and the channel closing unit. When it is detected that the temperature difference between the external and internal temperature data exceeds the preset threshold, the temperature difference analysis unit will quickly activate the channel closing unit and adjust the collection and transmission strategy of the internal temperature data, thereby ensuring the stability and safety of the internal temperature of the spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a diagram of the system structure disclosed in the present invention; Figure 2 This is a step diagram of the operation method of the channel closing unit in the spacecraft external temperature monitoring scenario of the present invention; Figure 3 This is a step diagram of the operation method of the channel closing unit in the spacecraft internal temperature monitoring scenario of the present invention; Figure 4 This is a method step diagram of the present invention for the coordinated action of the temperature difference analysis unit and the channel closing unit in a monitoring scenario where the external temperature of a spacecraft affects the internal temperature. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0019] Before discussing in depth the solution proposed by the present invention, it is necessary to clarify that the aerospace sensors involved in this application can be divided into external aerospace sensors and internal aerospace sensors according to the application scenarios.

[0020] Specifically, the external aerospace sensor is a surface temperature sensor of model JCW1(1A)-11. It should be pointed out that the JCW1(1A)-11 surface temperature sensor uses a Pt100 platinum resistor as the temperature measurement medium. The working principle of the JCW1(1A)-11 surface temperature sensor is based on the change in the resistivity of the thin film platinum resistor element at different temperatures, thereby establishing the corresponding relationship between the resistance value and the temperature. It should be noted that the surface temperature sensor of model JCW1(1A)-11 has a measurement range of -40°C to 500°C, has high precision and long-term stability, and is suitable for temperature monitoring in harsh environments outside the spacecraft.

[0021] As for the internal aerospace sensor, the JCW6-32 air temperature sensor was selected. The JCW6-32 air temperature sensor uses an NTC negative temperature coefficient thermistor as a sensitive element and is installed on the outer wall of the spacecraft's internal shell to measure the air temperature. It should be noted that the measurement range of the JCW6-32 air temperature sensor is between -30°C and 120°C. It has the advantages of fast response, small size, light weight, and low power consumption. It is suitable for temperature monitoring in limited spaces and complex environments inside spacecraft. In addition, the JCW6-32 air temperature sensor also demonstrates good stability and reliability, and can continuously provide accurate temperature data during the long-term operation of the spacecraft, providing key support for the temperature control and maintenance of the spacecraft.

[0022] Based on the above description, the present invention provides a technical solution: a multi-channel temperature acquisition and analysis system based on an aerospace sensor system, which is mainly used to solve the temperature data deviation and lag in the transmission process due to the temperature difference between the outside and inside of the spacecraft during the operation of the spacecraft.

[0023] Specifically, refer to Figure 1 It can be seen that the multi-channel temperature acquisition and analysis system based on the aerospace sensor system proposed in the present invention includes: an aerospace sensor, a plurality of aerospace sensors are combined and assembled inside and outside the spacecraft, and are used to capture data inside and outside the spacecraft.

[0024] It should be noted that the aerospace sensors mentioned in the present invention are specifically the JCW1(1A)-11 surface temperature sensor and the JCW6-32 air temperature sensor, which together constitute the aerospace sensor system.

[0025] The data transmission channel is composed of any two aerospace sensors among the multiple aerospace sensors and is used to transmit data.

[0026] The real-time temperature recording module is designed to be embedded in the aerospace sensor. The main function of the real-time temperature recording module is to record and monitor the temperature changes of the spacecraft in different environments in real time. The real-time temperature recording module can accurately match the temperature data recorded by the aerospace sensor with the corresponding time series information to ensure that each temperature record is accompanied by an accurate timestamp. While recording the temperature data, the real-time temperature recording module will also retain a complete backup data. Once the data recording and backup are completed, the real-time temperature recording module will package the recorded temperature data and time series information into a data packet. Subsequently, this data packet will be sent to the data transmission channel of the spacecraft so that these key information can be transmitted back to the ground control center for researchers and engineers to analyze and monitor the operating status of the spacecraft.

[0027] Frequency acquisition module,The frequency acquisition module is designed to be embedded in the aerospace sensor and work closely with the real-time temperature recording module. The main function of the frequency acquisition module is to monitor and obtain the working frequency of the aerospace sensor during the data acquisition process. In addition, the frequency acquisition module is also responsible for appending the acquired frequency information to the end of the data packet, thereby forming a data packet with a frequency suffix to facilitate subsequent data processing and analysis.

[0028] A data packet coordination module is provided in the data transmission channel, and is used to temporarily store data packets acquired at both ends of the data transmission channel, and classify the data packets based on the suffixes of the data packets; Channel closure unit, the frequency acquisition module is a functional component embedded in the data packet coordination module. The frequency acquisition module is responsible for selectively opening the connectivity of the data channel based on the length of the data transmission channel, the speed at which the data packet is placed in the data transmission channel, and any one of the data packet contents. It should be noted that the frequency acquisition module ensures the efficiency and security of data transmission. Through intelligent analysis and decision-making, the channel closure unit can dynamically adjust the state of the data channel, thereby optimizing the transmission efficiency of the data packet.

[0029] Specifically, when a data packet needs to pass through a specific transmission channel, the channel closing unit will decide whether to allow the data packet to pass, or when and under what conditions to open the channel based on preset parameters and conditions to ensure smooth and accurate data transmission.

[0030] The transmission unit is selected and configured in the data transmission channel. It is responsible for feeding back the data packets captured in the data transmission channel to the aerospace sensors at both ends of the data transmission channel according to the data transmission channel enabled by the channel closing unit, ensuring that the aerospace sensors at both ends send the collected data packets synchronously to the aerospace sensor system.

[0031] As a preferred implementation, in actual use, based on scenario constraints, the positions of the aerospace sensors at both ends of the data transmission channel in the spacecraft are not fixed.

[0032] Specifically, in the scenario of monitoring the external temperature of a spacecraft, the aerospace sensors at both ends of the data transmission channel are deployed at different positions on the external surface of the spacecraft. When the channel closing unit obtains a temperature difference on the external surface of the spacecraft based on the data packet, the channel closing unit selectively opens the data transmission channel based on the temperature gradient to preferentially transmit data packets with temperature difference.

[0033] It should be noted that the reference Figure 2 It can be seen that in the scenario of spacecraft external temperature monitoring, the operation method of the channel closure unit includes: Step S100: collecting temperature data recorded by any two aerospace sensors installed outside the spacecraft, and marking them as first temperature data and second temperature data respectively; Step S200: Acquire the vertical distance between the aerospace sensors corresponding to the first temperature data and the second temperature data; Step S300: Calculate the calibration temperature gradient according to the temperature gradient calculation formula, where the calibration temperature gradient is the ratio of the difference between the first temperature data and the second temperature data to the vertical distance between the two. It should also be noted that in step S200, the measurement of the vertical distance between the aerospace sensors is first performed by establishing a three-dimensional coordinate axis with the center point of the spacecraft as the origin in the spacecraft electronic modeling, obtaining the coordinate coefficients of the aerospace sensors in the three-dimensional coordinate axis through the spacecraft electronic modeling, and obtaining the vertical distance between the aerospace sensors based on the coordinate coefficients.

[0034] It should be further explained that the calculation formula for the temperature gradient in step S300 is: ;in Used to represent temperature gradient, It is used to represent the difference between the second temperature data and the first temperature data, that is, , Used to represent the vertical distance between the aerospace sensors corresponding to the second temperature data and the first temperature data.

[0035] When T2, the second temperature data, is higher than T1, the first temperature data, it indicates that there is a temperature gradient outside the spacecraft. At this time, the size and direction of the temperature gradient are crucial to the thermal protection design and temperature control strategy of the spacecraft. If there is a difference between T2 and T1, it means that the temperature distribution outside the spacecraft is uneven, and there are local overheating or overcooling areas.

[0036] Specifically, when T2 is an extreme high temperature value recorded by the JCW1(1A)-11 surface temperature sensor, such as 500°C, and T1 is a relatively low temperature value, such as -35°C, the position of the aerospace sensor corresponding to the first temperature data in the three-dimensional coordinate axis is (20, 3.5, 10), and the position of the aerospace sensor corresponding to the second temperature data in the three-dimensional coordinate axis is (-10, 7.5, 20). At this time, = , = =500-(-35)=535℃, = =535 / 32=16.7 (keep one decimal place). At this time, the direction of the temperature gradient is from the low temperature area to the high temperature area, that is, from the position (20,3.5,10) to the position (-10,7.5,20). The existence of this temperature gradient may produce different thermal stresses on the structural materials and thermal protection system of the spacecraft, thereby affecting the stability and safety of the spacecraft. Therefore, in the design and operation of the spacecraft, the influence of the temperature gradient must be fully considered, and corresponding measures must be taken to reduce or eliminate its adverse effects. For example, by optimizing the design and material selection of the thermal protection system, and adjusting the attitude and orbit of the spacecraft, the impact of the temperature gradient on the spacecraft can be reduced to ensure the normal operation and safety of the spacecraft.

[0037] Step S400: Substituting the average value of the temperature data recorded by the aerospace sensors outside the spacecraft and the vertical distance between the two aerospace sensors with the longest vertical distance outside the spacecraft into the temperature gradient calculation formula to calculate the temperature gradient threshold; Step S500: the channel closing unit selects an open data transmission channel based on the difference between the calibration temperature gradient and the temperature gradient threshold.

[0038] It should be noted that in step S500, if the calibration temperature gradient is greater than the preset temperature gradient threshold, the channel closing unit opens the data transmission channel; if the calibration temperature gradient is not greater than the preset temperature gradient threshold, the channel closing unit keeps the data transmission channel closed.

[0039] As a preferred implementation, in the scenario of internal temperature monitoring of a spacecraft, the aerospace sensors at both ends of the data transmission channel are placed at different positions inside the spacecraft, and the channel closing unit selectively opens the data transmission channel based on the frequency of temperature data acquired by the aerospace sensors and the control instructions of the internal temperature control system of the spacecraft.

[0040] In this embodiment, reference Figure 3 For the application scenario of spacecraft internal temperature monitoring, the operation method of the channel closure unit specifically includes: Step S001: Collect temperature data recorded by various aerospace sensors inside the spacecraft, and divide the temperature data into different data groups according to the installation positions of the sensors inside the spacecraft.

[0041] Step S002: Perform frequency analysis on each set of temperature data to obtain the frequency characteristics of the temperature data set.

[0042] Step S003: Compare the frequency characteristics of the temperature data set with the control instructions of the spacecraft internal temperature control system.

[0043] Step S004: The channel closing unit controls the connectivity of the data transmission channel based on the difference between the calibration temperature gradient and the temperature gradient threshold.

[0044] It should be pointed out that in step S004, if the frequency characteristics of the temperature data group are consistent with the control instructions, the channel closing unit selectively activates the data transmission channel based on the frequency characteristics of the temperature data group; if the frequency characteristics of the temperature data group are inconsistent with the control instructions, the channel closing unit keeps the data transmission channel closed.

[0045] Specifically, the comparison method between the frequency characteristics of the temperature data group and the control instructions of the temperature control system inside the spacecraft includes: Step S1: Optimize and adjust the control instructions of the temperature control system so that the control instructions form associated instructions that match the temperature fluctuations. The associated instructions include a temperature range instruction and a temperature change rate instruction.

[0046] Step S2: Performing quantitative analysis on the frequency characteristics of the collected temperature data set and the associated instructions.

[0047] Step S3: Construct a matching model between frequency characteristics and associated instructions.

[0048] Step S4: the matching model includes a matching degree calculation model between the frequency characteristics of the temperature data set and the temperature range instruction and a matching degree calculation model between the frequency characteristics of the temperature data set and the temperature change rate instruction.

[0049] Step S5: The matching model assigns corresponding weights to the matching degree calculation model of the temperature data set frequency characteristics and the temperature range instruction and the matching degree calculation model of the temperature data set frequency characteristics and the temperature change rate instruction respectively according to the mission to be performed by the spacecraft.

[0050] Step S6: Based on the assigned weights, a comparison result between the frequency characteristics of the temperature data set and the associated instructions is obtained.

[0051] It should be noted that in the present invention, the internal temperature control system of the spacecraft specifically includes a temperature control actuator and a temperature data processing unit. The temperature control actuator adjusts the temperature inside the spacecraft according to the instructions issued by the temperature data processing unit, and the temperature data processing unit is responsible for receiving data from the temperature sensor, analyzing and processing it, so as to generate control instructions for the temperature control actuator.

[0052] In this embodiment, the control instructions of the spacecraft's internal temperature control system are formulated based on factors such as the spacecraft's mission requirements, external environment, and internal temperature conditions. The specific content of the control instructions includes temperature range instructions and temperature change rate instructions, which are used to specify the range within which the spacecraft's internal temperature should be maintained and the rate of temperature change that should be controlled within.

[0053] During actual operation, the spacecraft's internal temperature control system will continuously receive data from temperature sensors and analyze and process this data through control algorithms. When it is found that there is a deviation between the actual temperature and the requirements of the control instructions, the temperature control system will adjust the output of the temperature control actuator according to the size and direction of the deviation, thereby achieving precise control of the internal temperature of the spacecraft.

[0054] It should also be noted that the operating formula of the matching degree calculation model of the temperature data set frequency characteristic and the temperature range instruction disclosed in step S4 includes: ;in Used to indicate the matching degree between the frequency characteristics of the temperature data set and the temperature range instruction; in is the indicator function, when Falling When the exponential function is within the range, the value of the exponential function is 1. Did not fall When it is within the range, the value of the exponential function is 0; in is the total number of frequency characteristics of the temperature data set.

[0055] It should be noted that during the actual operation, the operating formula of the matching calculation model of the temperature data set frequency characteristics and the temperature range instruction is when the temperature data set contains 5 temperature data points: (T1 = 22, T2 = 25, T3 = 32, T4 = 28, T5 = 19).

[0056] According to the above formula, the matching degree is calculated : According to the indicator function Definition: (22)=1, (25)=1, (32)=0, (28)=1, (19)=0, so: = =0.6 Therefore, the matching degree between the frequency characteristic of this temperature data set and the temperature range instruction is 0.6, which means that in the given temperature data set, 60% of the data points meet the requirements of the temperature range instruction.

[0057] In addition, it should be added that the operating formula of the matching degree calculation model of the temperature data set frequency characteristic and the temperature change rate instruction in step S4 includes: ;in It is used to indicate the matching degree between the frequency characteristic of the temperature data set and the temperature change rate instruction. The value of is between 0 and 1; in Used to indicate and The absolute distance between the values ​​and the instruction range, The value used to ensure a good match is between 0 and 1, where n is the total number of frequency features in the temperature dataset.

[0058] It should be noted that the operating formula of the matching degree calculation model of the temperature data set frequency characteristic and the temperature change rate instruction is actually running when the instruction value R mid is 50, R min =40,R max is 60,r i When is 25 and n is 5, = ,It should be explained that this means that in a given temperature data set, the rate of temperature change does not match the instruction requirements to a low degree, and only 20% of the data points meet the requirements of the temperature change rate instruction.

[0059] It should be further explained that in step S6, based on the assigned weights and the results of the above two matching calculation models, the system can comprehensively evaluate the matching degree between the temperature data set and the temperature control system control instructions. If the comparison result shows a high matching degree, it means that the current temperature control system control strategy is coordinated with the temperature condition inside the spacecraft, and can effectively maintain the spacecraft operating within a suitable temperature range. On the contrary, if the matching degree is low, it may be necessary to adjust the temperature control system control strategy to improve the accuracy and efficiency of temperature control.

[0060] In practical applications, if the control instruction of the temperature control system is to change the temperature control change rate, a high weight is artificially given to the matching degree between the frequency characteristics of the temperature data set and the temperature change rate instruction, so as to more accurately evaluate the control ability of the temperature control system control instruction on the temperature change rate. At the same time, if the control instruction of the temperature control system focuses on maintaining a specific temperature range, the weight of the matching degree between the temperature data set and the target temperature instruction of the temperature control system can be increased accordingly. It should be noted that through this flexible adjustment of weights, the system can intelligently select appropriate evaluation criteria according to different mission requirements and the internal temperature conditions of the spacecraft, thereby realizing the optimization adjustment of the temperature control system control strategy, which not only improves the accuracy and efficiency of temperature control, but also enhances the adaptability and stability of the spacecraft in complex environments.

[0061] As a preferred implementation, in a monitoring scenario where the external temperature of a spacecraft affects the internal temperature, the aerospace sensors at both ends of the data transmission channel are respectively deployed on the outside and inside of the spacecraft. Through the synergistic effect of the temperature difference analysis unit and the channel closing unit, the collection and transmission strategy of the internal temperature data is adjusted when the external temperature of the spacecraft changes.

[0062] It should be added that reference Figure 4 It can be seen that in the monitoring scenario where the external temperature of the spacecraft affects the internal temperature, the method of the temperature difference analysis unit and the channel closing unit working together includes: Step S010: collecting temperature data recorded by aerospace sensors outside and inside the spacecraft, and marking them as external temperature data and internal temperature data respectively.

[0063] Step S020: Calculate the temperature difference between the external temperature data and the internal temperature data.

[0064] Step S030: Setting a temperature difference threshold, which is artificially set based on the material properties of the spacecraft, external environmental factors, and the performance of the spacecraft's internal temperature control system.

[0065] Specifically, the method for manually setting the temperature difference threshold in step S030 is to use temperature simulation tools or experimental data in the prior art, based on the specific parameters of the spacecraft and the performance indicators of the temperature control system, to comprehensively evaluate the temperature change law of the spacecraft under different external environments, so as to determine a suitable temperature difference range as the temperature difference threshold. The temperature difference threshold is used to ensure that when the external temperature change has a significant impact on the internal temperature, the spacecraft can respond quickly and adjust the temperature control strategy to maintain the stability of the internal temperature of the spacecraft.

[0066] In step S040, the system compares the temperature difference value calculated in real time with a preset temperature difference threshold.

[0067] Step S040: The temperature difference analysis unit compares the calculated temperature difference value with the set temperature difference threshold.

[0068] It should be noted that if the temperature difference value exceeds the temperature difference threshold, the temperature difference analysis unit triggers the channel closing unit to adjust the internal temperature data collection and transmission strategy. If the temperature difference value does not exceed the temperature difference threshold, the channel closing unit maintains the current data collection and transmission strategy unchanged.

[0069] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is limited by the attached embodiments and their equivalents.

Claims

1. A multi-channel temperature acquisition and analysis system based on aerospace sensor system, characterized in that: include: Space sensors: multiple space sensors are combined and installed inside and outside the spacecraft and are used to capture data inside and outside the spacecraft; A data transmission channel, formed by any two aerospace sensors among the plurality of aerospace sensors, for transmitting data; The real-time temperature recording module is embedded in the aerospace sensor and is used to match the temperature data and time series recorded by the aerospace sensor, and after leaving the backup data, the recorded temperature data and time series are packaged into a data packet and sent to the data transmission channel; A frequency acquisition module, embedded in the aerospace sensor and matched with the real-time temperature recording module, is used to acquire the frequency of the aerospace sensor when collecting data, and attach the frequency data to the outside of the data packet to form a suffix of the data packet; A data packet coordination module is provided in the data transmission channel, and is used to temporarily store data packets acquired at both ends of the data transmission channel, and classify the data packets based on the suffixes of the data packets; a channel closure unit, embedded in the data packet coordination module, and selectively opening connectivity of the data channel based on any of the length of the data transmission channel, the speed at which the data packet is placed in the data transmission channel, and the content of the data packet; The transmission unit is selected and configured in the data transmission channel. It is responsible for feeding back the data packets captured in the data transmission channel to the aerospace sensors at both ends of the data transmission channel according to the data transmission channel enabled by the channel closing unit, ensuring that the aerospace sensors at both ends send the collected data packets synchronously to the aerospace sensor system.

2. The multi-channel temperature acquisition and analysis system based on aerospace sensor system according to claim 1, characterized in that: Under the constraints of the scenario, the positions of the aerospace sensors at both ends of the data transmission channel in the spacecraft are not fixed; In the scenario of spacecraft external temperature monitoring, the space sensors at both ends of the data transmission channel are deployed at different positions on the outer surface of the spacecraft. When the channel closing unit obtains the temperature difference on the outer surface of the spacecraft based on the data packet, the channel closing unit selectively opens the data transmission channel based on the temperature gradient to preferentially transmit the data packets with the temperature difference. For the scenario of temperature monitoring inside the spacecraft, the aerospace sensors at both ends of the data transmission channel are placed at different positions inside the spacecraft. The channel closing unit selectively opens the data transmission channel based on the frequency of temperature data obtained by the aerospace sensors and the control instructions of the temperature control system inside the spacecraft. In the monitoring scenario where the external temperature of the spacecraft affects the internal temperature, the aerospace sensors at both ends of the data transmission channel are deployed on the outside and inside of the spacecraft respectively. Through the synergy of the temperature difference analysis unit and the channel closing unit, the collection and transmission strategy of the internal temperature data is adjusted when the external temperature of the spacecraft changes.

3. The multi-channel temperature acquisition and analysis system based on aerospace sensor system according to claim 2, characterized in that: In the scenario of spacecraft external temperature monitoring, the operation method of the channel closure unit includes: The temperature data recorded by any two aerospace sensors installed outside the spacecraft are collected and marked as first temperature data and second temperature data respectively; Acquire a vertical distance between aerospace sensors corresponding to the first temperature data and the second temperature data; According to the temperature gradient calculation formula, the calibration temperature gradient is calculated, and the calibration temperature gradient is the ratio of the difference between the first temperature data and the second temperature data to the vertical distance between the two; Substitute the average value of the temperature data recorded by the aerospace sensors outside the spacecraft and the vertical distance between the two aerospace sensors with the longest vertical distance outside the spacecraft into the temperature gradient calculation formula to calculate the temperature gradient threshold; The channel closing unit controls the connectivity of the data transmission channel based on the difference between the calibration temperature gradient and the temperature gradient threshold; If the calibration temperature gradient is greater than a preset temperature gradient threshold, the channel closing unit opens the data transmission channel; If the calibration temperature gradient is not greater than the preset temperature gradient threshold, the channel closing unit keeps the data transmission channel closed.

4. The multi-channel temperature acquisition and analysis system based on aerospace sensor system according to claim 3 is characterized in that: The calculation formula of the temperature gradient is: ;in Used to represent temperature gradient, It is used to represent the difference between the second temperature data and the first temperature data, that is, , Used to represent the vertical distance between the aerospace sensors corresponding to the second temperature data and the first temperature data.

5. The multi-channel temperature acquisition and analysis system based on aerospace sensor system according to claim 2, characterized in that: In the scenario of temperature monitoring inside a spacecraft, the operation method of the channel closure unit includes: Collect temperature data recorded by various space sensors inside the spacecraft, and divide the temperature data into different data groups according to the installation position of the sensors inside the spacecraft; Performing frequency analysis on each set of temperature data to obtain frequency characteristics of the temperature data set; Compare the frequency characteristics of the temperature data set with the control instructions of the spacecraft's internal temperature control system; The channel closing unit selectively opens the data transmission channel based on the comparison result; If the frequency characteristic of the temperature data set is consistent with the control instruction, the channel closing unit selectively activates the data transmission channel based on the frequency characteristic of the temperature data set; If the frequency characteristic of the temperature data group is inconsistent with the control instruction, the channel closing unit keeps the data transmission channel closed.

6. The multi-channel temperature acquisition and analysis system based on aerospace sensor system according to claim 5, characterized in that: The comparison method between the frequency characteristics of the temperature data group and the control instructions of the spacecraft internal temperature control system includes: Optimize and adjust the control instructions of the temperature control system so that the control instructions form associated instructions that match the temperature fluctuations. The associated instructions include temperature range instructions and temperature change rate instructions. Perform quantitative analysis on the frequency characteristics of the acquired temperature data set and the associated instructions; Construct a matching model between frequency characteristics and associated instructions; The matching model includes a matching degree calculation model between the frequency characteristics of the temperature data set and the temperature range instruction and a matching degree calculation model between the frequency characteristics of the temperature data set and the temperature change rate instruction; The matching model assigns corresponding weights to the matching degree calculation model of the temperature data set frequency characteristics and the temperature range instruction and the matching degree calculation model of the temperature data set frequency characteristics and the temperature change rate instruction according to the mission performed by the spacecraft; Based on the assigned weights, a comparison result between the frequency characteristics of the temperature data set and the correlation instruction is obtained.

7. The multi-channel temperature acquisition and analysis system based on aerospace sensor system according to claim 6, characterized in that: The operating formula of the matching degree calculation model of the temperature data set frequency characteristic and the temperature range instruction includes: ;middle Used to indicate the matching degree between the frequency characteristics of the temperature data set and the temperature range instruction; in is the indicator function, when Falling When the exponential function is within the range, the value of the exponential function is 1. Did not fall When it is within the range, the value of the exponential function is 0; in is the total number of temperature datasets.

8. The multi-channel temperature acquisition and analysis system based on aerospace sensor system according to claim 6, characterized in that: The operating formula of the matching degree calculation model of the temperature data set frequency characteristic and the temperature change rate instruction includes: ;in It is used to indicate the matching degree between the frequency characteristic of the temperature data set and the temperature change rate instruction. The value of is between 0 and 1; in Used to indicate and The absolute distance between the values ​​and the instruction range, The value used to ensure the match is between 0 and 1.

9. The multi-channel temperature acquisition and analysis system based on aerospace sensor system according to claim 1, characterized in that: In the monitoring scenario where the external temperature of the spacecraft affects the internal temperature, the method of cooperating between the temperature difference analysis unit and the channel closing unit includes: The temperature data recorded by the external and internal space sensors of the spacecraft are collected and marked as external temperature data and internal temperature data respectively; Calculate the temperature difference between the external temperature data and the internal temperature data; Setting a temperature difference threshold, which is artificially set based on the material properties of the spacecraft, external environmental factors, and the performance of the spacecraft's internal temperature control system; The temperature difference analysis unit compares the calculated temperature difference value with the set temperature difference threshold; If the temperature difference exceeds the temperature difference threshold, the temperature difference analysis unit triggers the channel closing unit to adjust the collection and transmission strategy of the internal temperature data; If the temperature difference value does not exceed the temperature difference threshold, the channel closing unit maintains the current data collection and transmission strategy unchanged.

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