Onboard integrated data acquisition and recording system and method

Abstract

This application provides an airborne integrated data acquisition and recording system and method, applicable to the field of aviation flight testing. The system includes: for each data acquisition module, each data acquisition unit acquires target data under the current flight state; each data processing unit determines the cache priority of the target data based on the importance of the data type attributes of the data acquisition module under the current flight state, as well as the data transmission rate and data change entropy of the target data; wherein the importance of the data type attributes of the data acquisition module differs under different flight states; each data output unit sends the target data and its cache priority to the main control module; the main control module receives the target data and corresponding cache priorities sent by multiple data output units; and caches multiple target data in descending order of cache priority. This enables real-time and reliable acquisition and recording of multi-source heterogeneous data in complex flight test missions.

Description

Technical Field

[0001] This application relates to the field of aviation flight test technology, and in particular to an airborne integrated data acquisition and recording system and method. Background Technology

[0002] In flight testing, the airborne data acquisition and recording system is the core equipment for obtaining relevant performance data of the aircraft. With the increasing complexity of flight test missions, the airborne data acquisition and recording system needs to simultaneously collect heterogeneous data from multiple sources, including sensors, audio / video equipment, and avionics buses. These data differ significantly in data structure, sampling frequency, transmission bandwidth, and real-time requirements, forming a complex high-bandwidth data stream.

[0003] However, existing airborne data acquisition and recording systems can usually only acquire a single type of data when dealing with complex flight test missions, or they can barely be compatible with multiple data sources by adding conversion interfaces and frequently replacing specific data acquisition boards. This architecture often adopts a preset fixed bandwidth allocation or a single cyclic acquisition mode. When multiple heterogeneous data sources flood in concurrently, it cannot adaptively coordinate the storage requests of data streams with different characteristics, which can easily lead to instantaneous congestion of the internal bus and buffer overflow, causing packet loss, out-of-order or timing distortion of critical test data. It is difficult to meet the current high-reliability real-time processing and storage requirements of high-bandwidth complex heterogeneous data. Summary of the Invention

[0004] This application provides an airborne integrated data acquisition and recording system and method. By deeply deconstructing the dynamic characteristics of target data in each data acquisition module and coupling the importance of attributes associated with different flight states, it achieves real-time and accurate quantification of the priority of heterogeneous data streams. This overcomes the limitations of traditional solutions that rely on adding conversion interfaces or replacing boards, resulting in low system integration and rigid bandwidth allocation. Through a multi-dimensional feature perception mechanism, it accurately captures transient fluctuations of data from different physical channels using data change entropy, and corrects timing deviations by combining timestamp offsets, thus resolving the contention of limited bus resources when heterogeneous data floods in concurrently. Based on the calculated priority sequence, it performs ordered cache scheduling from largest to smallest, significantly reducing the risk of instantaneous congestion and buffer overflow on the internal bus. This fundamentally eliminates technical bottlenecks such as packet loss, out-of-order delivery, and timing distortion, ensuring that massive heterogeneous data can achieve highly reliable real-time processing and full lifecycle timing consistency under complex flight test mission scenarios and high bandwidth pressure.

[0005] This application provides an airborne integrated data acquisition and recording system, comprising: an airborne integrated data acquisition and recording device, the airborne integrated data acquisition and recording device including multiple data acquisition modules and a main control module, the main control module being electrically or communicatively connected to the multiple data acquisition modules; the multiple data acquisition modules acquiring different types of data; each data acquisition module including a data acquisition unit, a data processing unit, and a data output unit; wherein... The data acquisition unit is used to acquire target data under the current flight status; The data processing unit is used to determine the cache priority of the target data based on the importance of the data type attributes of the data acquisition module in the current flight state, and the data transmission rate and data change entropy of the target data; wherein the importance of the data type attributes of the data acquisition module is different in different flight states; A data output unit is used to send the target data and the cache priority of the target data to the main control module. The main control module is used to receive target data and corresponding cache priorities sent by multiple data output units; and to cache the multiple target data in descending order of cache priority.

[0006] This application also provides an airborne integrated data acquisition and recording method, applied to the aforementioned airborne integrated data acquisition and recording system. The airborne integrated data acquisition and recording system includes: an airborne integrated data acquisition and recording device, which includes multiple data acquisition modules and a main control module. The main control module is electrically or communicatively connected to the multiple data acquisition modules. The multiple data acquisition modules acquire different data types. Each data acquisition module includes a data acquisition unit, a data processing unit, and a data output unit. The method includes: For each of the aforementioned data acquisition modules, target data under the current flight status is acquired through the data acquisition unit; The data processing unit determines the cache priority of the target data based on the importance of the data type attributes of the data acquisition module in the current flight state, as well as the data transmission rate and data change entropy of the target data; wherein, the importance of the data type attributes of the data acquisition module is different in different flight states. The target data and the cache priority of the target data are sent to the main control module through the data output unit; The main control module receives target data and corresponding cache priorities sent by multiple data output units; and caches the target data in descending order of cache priority.

[0007] This application provides an airborne integrated data acquisition and recording system and method. The system includes an airborne integrated data acquisition recorder, which comprises multiple data acquisition modules and a main control module. The main control module is electrically or communicatively connected to the multiple data acquisition modules. The multiple data acquisition modules acquire different data types. Each data acquisition module includes a data acquisition unit, a data processing unit, and a data output unit. The data acquisition unit is used to acquire target data under the current flight state. The data processing unit is used to determine the cache priority of the target data based on the importance of the data type attributes of the data acquisition modules under the current flight state, and the data transmission rate and data change entropy of the target data. The importance of the data type attributes of the data acquisition modules differs under different flight states. The data output unit is used to send the target data and the cache priority of the target data to the main control module. The main control module is used to receive the target data and corresponding cache priorities sent by the multiple data output units. The multiple target data are cached in descending order of cache priority. This airborne integrated data acquisition and recording system achieves real-time and accurate quantification of the priority of heterogeneous data streams by deeply deconstructing the dynamic characteristics of target data in each data acquisition module and coupling the importance of attributes associated with different flight states. This overcomes the limitations of traditional solutions that rely on adding conversion interfaces or replacing boards, resulting in low system integration and rigid bandwidth allocation. Through a multi-dimensional feature perception mechanism, it accurately captures transient fluctuations in data from different physical channels using data change entropy and corrects timing deviations by combining timestamp offsets, thus resolving the competition for limited bus resources when heterogeneous data floods in concurrently. Based on the calculated priority sequence, it performs ordered cache scheduling from largest to smallest, significantly reducing the risk of instantaneous congestion and buffer overflow on the internal bus. This fundamentally eliminates technical bottlenecks such as packet loss, out-of-order delivery, and timing distortion, ensuring that massive heterogeneous data can achieve highly reliable real-time processing and full lifecycle timing consistency under complex flight test mission scenarios and high bandwidth pressure. Attached Figure Description

[0008] To more clearly illustrate the technical solutions in this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0009] Figure 1 This is a schematic diagram of the structure of the airborne integrated data acquisition and recording system provided in the embodiments of this application; Figure 2 This is a schematic diagram of the structure of the data acquisition module provided in an embodiment of this application; Figure 3 This is a schematic diagram of the data offloading and diversion module provided in an embodiment of this application; Figure 4 This is a flowchart illustrating the working process of the data offloading and diversion module provided in this application embodiment; Figure 5 This is a schematic diagram of the configuration loading and status monitoring module provided in an embodiment of this application; Figure 6 This is a schematic diagram of the main control module provided in an embodiment of this application; Figure 7 This is a flowchart illustrating the working process of the data acquisition module provided in this application embodiment; Figure 8 This is a flowchart illustrating the working process of the data output unit provided in the embodiments of this application; Figure 9 This is a flowchart illustrating the working process of the data receiving unit provided in the embodiments of this application; Figure 10 This is a flowchart illustrating the working process of the airborne integrated data acquisition recorder provided in the embodiments of this application; Figure 11 This is a flowchart illustrating the working process of the data acquisition and recording system provided in this application embodiment; Figure 12 This is a flowchart illustrating the airborne integrated data acquisition and recording method provided in the embodiments of this application. Detailed Implementation

[0010] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0011] To better understand the embodiments of this application, the prior art will first be described in detail: Existing airborne data acquisition and recording systems, besides being unable to adaptively coordinate storage requests from different data streams with varying characteristics when multiple heterogeneous data sources flood in concurrently, are prone to instantaneous congestion and buffer overflows on the internal bus, resulting in packet loss, out-of-order delivery, or timing distortion of critical test data. They fail to meet the current high-reliability real-time processing and storage requirements for high-bandwidth, complex, and heterogeneous data, and also suffer from the following technical problems: P1. Because the data is recorded in different dedicated devices or independent storage media, after the flight test mission is completed, ground personnel need to physically unload and export the data from multiple storage modules one by one. This fragmented data flow mode makes the data aggregation operation extremely cumbersome, which seriously restricts the iteration and post-processing analysis efficiency of the flight test mission. P2. Due to the lack of a unified architecture standard, multiple independent data acquisition and recording devices are often required to collect heterogeneous data from various sources such as sensors, audio and video equipment and avionics buses. This results in complex cab wiring, large space occupation and expensive maintenance costs throughout the entire life cycle.

[0012] It should be noted that the airborne integrated data acquisition and recording system provided in this application embodiment is applicable to multi-source heterogeneous data fusion monitoring and high-reliability storage scenarios in complex aviation flight test missions. Specifically, when the test aircraft is performing complex test flight missions such as high-risk and high-dynamic subjects, the aforementioned airborne integrated data acquisition and recording system can simultaneously handle heterogeneous data environments involving multiple channels, large bandwidth spans, synchronous / asynchronous mixing, and complex protocol structures, such as flight parameters, audio and video, and avionics buses.

[0013] Based on the aforementioned complex and heterogeneous data environment, this application precisely adapts to typical scenarios such as highly integrated distributed acquisition, dynamic and complex link competition, high-precision time alignment and spatiotemporal correlation, and large-scale automated post-processing of data through in-depth analysis and resource scheduling of heterogeneous data streams.

[0014] Specifically, in highly integrated distributed acquisition scenarios, the airborne integrated data acquisition and recording system utilizes a "stack-based + modular" design to enable a single device to flexibly access heterogeneous data from the entire aircraft. This solves the physical integration problem for space-constrained aircraft when acquiring multi-source data in parallel, and significantly reduces the complexity of the airborne testing system and the equipment maintenance cost.

[0015] In dynamic and complex link contention scenarios, by real-time sensing of link bandwidth compensation coefficient and data change entropy, and combining the coefficient of variation to dynamically correct the weights of different flight states, the airborne integrated data acquisition and recording system has established a complete priority evaluation mechanism. This ensures that critical control commands and sudden fault signals can be recorded with absolute priority when multiple heterogeneous data sources flood in concurrently, effectively avoiding the risk of sampling frame loss and loss of critical abnormal information caused by bus congestion.

[0016] In high-precision time alignment and spatiotemporal correlation scenarios, the airborne integrated data acquisition and recording system relies on the synchronous time broadcasting mechanism and unified time synchronization unit to achieve precise time synchronization across physical modules. This ensures that various sensor data, video frames and bus messages distributed on different acquisition plug-ins have a strictly consistent time reference, providing a spatiotemporal alignment basis for accident tracing, accurate flight envelope verification and multi-dimensional data fusion analysis in complex subjects.

[0017] In large-scale automated data post-processing scenarios, for the massive unordered raw bit streams generated after the flight test mission, the airborne integrated data acquisition and recording system uses a binary feature recognition model to intelligently split the storage stream and establish logical files. It can automatically identify the protocol type of heterogeneous data and achieve structured storage, which significantly reduces the complexity of manual interpretation at the ground station and greatly shortens the closed-loop processing cycle from unloading to effective analysis of flight test data.

[0018] The airborne integrated data acquisition and recording system (hereinafter referred to as the "acquisition and recording system") provided in the embodiments of this application will be described in detail below. This acquisition and recording system can solve the technical problems in the prior art, as detailed below: Figure 1 This is a schematic diagram of the structure of the airborne integrated data acquisition and recording system provided in the embodiments of this application; Figure 2 This is a schematic diagram of the data acquisition module provided in an embodiment of this application. Figure 1 and Figure 2 As can be seen from the data acquisition and recording system, the system may include an airborne integrated data acquisition and recording unit 10. The airborne integrated data acquisition and recording unit 10 may include n data acquisition modules 101 and a main control module 102, where n is an integer greater than 1. The main control module 102 is electrically or communicatively connected to the n data acquisition modules 101. The n data acquisition modules acquire different types of data. Each data acquisition module 101 may include a data acquisition unit 1011, a data processing unit 1012, and a data output unit 1013. The data acquisition unit 1011 is used to acquire target data under the current flight status; The data processing unit 1012 is used to determine the cache priority of the target data based on the importance of the data type attributes of the data acquisition module 101 in the current flight state, as well as the data transmission rate and data change entropy of the target data; wherein, the importance of the data type attributes of the data acquisition module 101 is different in different flight states. Data output unit 1013 is used to send target data and target data cache priority to main control module 102; The main control module 102 is used to receive the target data and corresponding cache priority sent by each of the multiple data output units 1013; and to cache the multiple target data in descending order of cache priority.

[0019] Optionally, the n data acquisition modules 101 include, but are not limited to: flight parameter data acquisition modules, audio and video data acquisition modules, and bus data acquisition modules.

[0020] Optionally, flight parameter data acquisition modules include, but are not limited to: digital acquisition modules, analog acquisition modules, and Pulse Code Modulation (PCM) stream decoding modules.

[0021] The digital acquisition module is used to acquire discrete switch signals such as landing gear retraction and extension status and door lock; the analog acquisition module is used to acquire continuously changing physical quantities such as oil pressure, air pressure, temperature and displacement; and the PCM stream decoding module is used to acquire telemetry frames and PCM signals.

[0022] It should be noted that the flight parameter data acquired by the flight parameter data acquisition module is usually in the form of slowly changing signals or status bits, and the data volume is relatively small. In specific flight states such as takeoff and landing, the data type attribute of this flight parameter data is usually assigned a higher weight to ensure the absolute reliability of the recording of core flight safety parameters.

[0023] Optionally, the audio and video data acquisition module can be a Digital Visual Interface (DVI) video acquisition module, a High-Definition Multimedia Interface (HDMI) video acquisition module, or a Serial Digital Interface (SDI) video acquisition module.

[0024] The DVI video acquisition module is used to acquire digital video streams and display auxiliary channel data based on the Minimum Transmission Differential Signaling protocol; the HDMI video acquisition module is used to acquire uncompressed high-definition audio and video streams based on the HDMI protocol; and the SDI video acquisition module is used to acquire uncompressed, unencrypted digital video component signals and embedded audio data based on the SDI protocol.

[0025] It should be noted that audio and video data acquisition modules have extremely high data bandwidth consumption characteristics (e.g., high bandwidth, high throughput). By calculating the data transmission rate of the target data in real time, the acquisition and recording system can dynamically adjust the buffer priority of audio and video stream data while ensuring the high real-time data such as bus commands. This balances the storage load of the acquisition and recording system and avoids system congestion caused by sudden surges in traffic.

[0026] Optionally, bus-type data acquisition modules include, but are not limited to: network acquisition modules, RS232 / RS422 / RS485 bus acquisition modules, 1394B bus acquisition modules, and Fibre Channel (FC) bus acquisition modules.

[0027] Among them, the network acquisition module is used to acquire network packets and interactive messages using aviation full-duplex switched Ethernet protocol or user datagram protocol; the RS232 / RS422 / RS485 bus acquisition module is used to acquire low-speed discrete data streams and sensor status words based on asynchronous serial communication protocol; the 1394B bus acquisition module is used to acquire isochronous transmission data packets and control register status of high-performance serial bus protocol; and the FC bus acquisition module is used to acquire FC protocol messages and massive information exchange data across nodes.

[0028] It should be noted that bus-type data acquisition modules involve a variety of complex bus data, ranging from low-speed bus acquisition modules (such as RS232 bus acquisition modules) to ultra-high-speed bus acquisition modules (such as FC bus acquisition modules), carrying critical control commands and navigation data within the avionics system. Because bus data typically has a high information value density, the acquisition and recording system can accurately identify sudden anomalies on the bus by monitoring data change entropy in real time, and can prioritize buffering to ensure high-fidelity reproduction of critical control logic in complex flight test missions.

[0029] It is important to note that for each of the n data acquisition modules 101, each module 101 acquires data of a specific data type. In other words, this acquisition and recording system, through physical isolation of the hardware interfaces and independent design of functional circuits, ensures that each data acquisition module 101 is only responsible for extracting the specific data protocol or signal category it matches. For example, the digital acquisition module is only responsible for acquiring discrete switching signals such as landing gear retraction / extension status and door locking; the analog acquisition module is only responsible for acquiring continuously changing physical quantities such as oil pressure, air pressure, temperature, and displacement; the FC bus acquisition module is only responsible for acquiring FC protocol messages and massive cross-node information exchange data; and the DVI video acquisition module is only responsible for acquiring digital video streams based on the Minimum Transmission Differential Signaling protocol and display auxiliary channel data, etc.

[0030] This "single-module, single-data-type" configuration, through the decoupling of physical links and the isolation of dedicated processing circuits, effectively prevents electromagnetic coupling or crosstalk between high-bandwidth video streams or high-speed pulse signals and weak signals such as precision analog quantities, ensuring signal fidelity at the data acquisition end from the source. Simultaneously, this architecture allows the acquisition and recording system to accurately allocate the initial data type attribute importance based on the inherent characteristics of the data carried by each data acquisition module 101 (such as real-time requirements, bandwidth load, and data value density), thus laying the physical foundation for the subsequent fine-grained heterogeneous data priority scheduling by the main control module 102.

[0031] It is understandable that target data in the current flight state refers to the raw information stream captured in real time by various data acquisition modules during the flight state of a UAV or manned aircraft performing a specific task (such as takeoff, cruise, landing, high-dynamic subject test, etc.).

[0032] Optionally, corresponding to the above n data acquisition modules 101, the target data may include flight parameter data, audio and video stream data, and bus data, etc. These data are multi-source heterogeneous data involving multiple channels and different protocol formats, and are the processing objects for subsequent dynamic scheduling and priority evaluation.

[0033] Optionally, flight parameter data may include digital data, analog data, and PCM stream data, etc.

[0034] Optionally, audio and video data may include: high-definition video stream data acquired via DVI, cabin voice audio data, and image sequences generated by infrared / low-light sensors, etc.

[0035] Optionally, the bus data may include data acquired by buses such as RS232 / RS422 / RS485, ARINC429, 1553B, 1394B, and FC.

[0036] It is understandable that the importance of data type attributes refers to the weighted indicators that reflect the business value of different data sources under different flight conditions.

[0037] Data transmission rate refers to the real-time effective bandwidth or data throughput of the physical link between the data acquisition module 101 and the main control module 102, which is used to quantify the current degree of congestion or physical degradation of the physical link.

[0038] Data change entropy refers to a quantitative indicator obtained by extracting the statistical distribution characteristics of target data within a preset sliding window (such as the absolute value fluctuation of the difference between adjacent sampling points), which is used to reflect the burst characteristics of the signal corresponding to the target data.

[0039] Cache priority refers to the execution order in which the main control module 102 sorts and caches multiple received target data.

[0040] Optionally, the main control module 102 and multiple data acquisition modules 101 are interconnected via a backplane bus. Specifically, each data acquisition module 101 establishes an electrical connection with the main control module 102 via the backplane bus to achieve unified power supply and physical transparent transmission of high-precision synchronous clock signals; or, each data acquisition module 101 establishes a communication connection with the main control module 102 based on a preset high-speed transmission protocol, thereby providing a logical channel for real-time, deterministic interaction of target data and its corresponding cache priority between modules.

[0041] In this embodiment, each data acquisition unit 1011 acquires target data in parallel according to the isolation principle of "single module, single type". Then, the data processing unit 1012 extracts multi-dimensional dynamic features of each target data in real time, including data transmission rate reflecting link status and data change entropy reflecting signal burst characteristics. Subsequently, each data processing unit 1012, in conjunction with the current flight status, retrieves the preset importance of data type attributes and integrates the aforementioned extracted multi-dimensional dynamic features to calculate a comprehensive cache priority for the corresponding target data. After the calculation is completed, each data output unit 1013 synchronously pushes the target data and the corresponding cache priority tag to the backplane bus and sends it to the main control module 102 through the backplane bus. After receiving the concurrent target data streams from multiple data output units 1013, the main control module 102 does not need to perform protocol parsing on complex heterogeneous data and can perform global sorting cache according to the cache priority of each target data from largest to smallest.

[0042] It should be noted that this data acquisition and recording system extracts multi-dimensional dynamic features such as data transmission rate and data change entropy in real time within each data acquisition module 101, and combines this with the importance of data type attributes under the current flight state to construct a precise cache priority evaluation process for multi-source heterogeneous data. The main control module 102 executes global sorting cache only based on cache priority, and achieves adaptive resource scheduling for complex multi-source heterogeneous data without the need for deep protocol parsing. This effectively avoids electromagnetic interference and bus congestion in high-bandwidth concurrent scenarios, and ensures highly reliable real-time recording and time-series consistency of massive heterogeneous data under complex flight test missions.

[0043] In some embodiments, from Figure 1It can also be seen that the data acquisition and recording system further includes: a host computer 20; a data processing unit 1012 electrically or communicatively connected to the host computer 20; the data processing unit 1012 is used to determine the cache priority of the target data based on the importance of the data type attributes of the data acquisition module 101 in the current flight state, and the data transmission rate and data change entropy of the target data, and may include: the data processing unit 1012 specifically used to obtain the importance of the data type attributes of the data acquisition module 101 in the current flight state sent by the host computer 20; use the ratio of the preset reference transmission rate to the data transmission rate as the transmission compensation coefficient; calculate the absolute value of the difference between adjacent sampling points in the first sampling column of the target data, and extract the statistical distribution characteristics of the absolute value of the difference within a preset sliding window as the data change entropy; wherein, the data change entropy increases with the increase of the fluctuation frequency and fluctuation amplitude of the target data; and determine the cache priority of the target data based on the importance of the data type attributes, the transmission compensation coefficient, and the data change entropy.

[0044] The generation time refers to the initial moment when the target data is generated at the sensor under test, avionics bus, or video source.

[0045] The acquisition time refers to the moment when the data acquisition unit 1011 actually receives the target data and completes the physical layer parsing of the target data.

[0046] The preset baseline transmission rate refers to the rated design bandwidth or maximum throughput of the physical channel between the data acquisition module 101 and the main control module 102 under ideal conditions, and is used to measure the deviation of the actual transmission performance.

[0047] The first sampling column of the target data refers to a set of original target data samples with a chronological order that are continuously acquired by the data acquisition unit 1011 within a preset time window. It is the basic sequence for calculating the data change entropy.

[0048] Adjacent sampling points refer to two sampling points that are immediately adjacent on the timestamp sequence in the first sampling column.

[0049] Statistical distribution characteristics refer to the mathematical calculation results of the probability distribution, variance, mean, or information entropy increment of the absolute value sequence of differences between adjacent sampling points within a preset sliding window.

[0050] Fluctuation frequency refers to the number of times the target data undergoes numerical jumps per unit time or the density of signal cycles.

[0051] Fluctuation amplitude refers to the absolute deviation or the degree of deviation from the reference value between adjacent sampling points.

[0052] In this embodiment of the application, for each data acquisition module 101, firstly, the data processing unit 1012 obtains the pre-configured importance of the data type attributes of the data acquisition module 101 in the current flight state through the communication connection with the host computer 20.

[0053] Secondly, to cope with the complex and ever-changing airborne acquisition environment, the data processing unit 1012 performs parallel multi-dimensional dynamic feature extraction on the target data acquired in real time by the data acquisition module 101. Specifically, the data processing unit 1012 monitors the current data transmission rate in real time and compares it with a preset benchmark transmission rate, calculating the ratio of the two as a transmission compensation coefficient. When the actual data transmission rate is much lower than the benchmark transmission rate, the transmission compensation coefficient increases, and the data processing unit 1012 identifies the risk of congestion or degradation in the current physical link, thereby increasing the buffer priority of the affected target data to ensure that the core signal is not lost. For the first sampling column of the target data, the data processing unit 1012 analyzes the absolute value of the difference between adjacent sampling points in the first sampling column, and accurately calculates the data change entropy by extracting the statistical distribution characteristics (such as variance or information entropy increment) of the difference sequence within a preset sliding window. It should be noted that the acquisition time sequence of the transmission compensation coefficient and the data change entropy is not limited.

[0054] Finally, the data processing unit 1012 performs a nonlinear fusion operation on the importance of the aforementioned data type attributes and the aforementioned multidimensional dynamic features to ultimately determine the cache priority of the target data. Based on this, the data processing unit 1012 can determine the cache priority of the target data acquired by each of the n data acquisition modules 101.

[0055] It should be noted that by deeply integrating the importance of static data type attributes pre-configured on the host computer 20 with the aforementioned multi-dimensional dynamic features extracted in real time, a multi-dimensional priority evaluation system that takes into account both the business value and link status during the flight mission phase is constructed. This enables the data acquisition and recording system to adaptively identify and prioritize the caching of key data packets with high timeliness requirements and high information density. From an algorithmic perspective, this eliminates the risk of frame loss and abnormal information loss during sampling of multi-source heterogeneous data in a concurrent competition environment, significantly improving the fidelity and recording reliability of airborne test data.

[0056] In some embodiments, the data processing unit 1012 is specifically used to obtain the importance of data type attributes of the data acquisition module 101 sent by the host computer 20 in the current flight state, including: the data processing unit 1012 is specifically used to obtain the initial importance of data type attributes of the data acquisition module 101 sent by the host computer 20 in the current flight state; and to obtain the second sampling sequence of data collected by the data acquisition unit 1011 in the previous adjacent flight state; to use the ratio of the standard deviation to the arithmetic mean of the second sampling sequence as the coefficient of variation of the target data; and to correct and compensate the initial importance of data type attributes according to the coefficient of variation to obtain the importance of data type attributes.

[0057] Among them, the importance of the initial data type attribute refers to the static weight benchmark value pre-assigned by the host computer 20 to each data acquisition module 101 in a specific flight state according to the preset flight mission book or test outline, which is used to reflect the prior attention of different data sources in the current flight state.

[0058] The preceding adjacent flight state refers to the previous complete execution phase that is immediately adjacent to the current flight state on the timeline (for example, if the current phase is "cruise phase", then the preceding adjacent phase is "takeoff phase").

[0059] The second sampling sequence refers to the set of historical target data samples acquired by the data acquisition unit 1011 in the previous adjacent flight state, which is used to characterize the fluctuation characteristics of a specific data source.

[0060] In this embodiment, after the host computer 20 obtains the importance of the initial data type attribute of the data acquisition module 101 in the current flight state, it can send the importance of the initial data type attribute to the data processing unit 1012. The data processing unit 1012 uses the received importance of the initial data type attribute as a weighting benchmark. At the same time, it retrieves the second sampling sequence captured in the previous adjacent flight state and performs statistical analysis on the second sampling sequence. Specifically, it calculates the standard deviation and arithmetic mean of the second sampling sequence and then obtains the ratio of the two to get the coefficient of variation, which reflects the dispersion and activity characteristics of the data collected in the previous adjacent flight state. Then, it uses the coefficient of variation to correct and compensate the importance of the initial data type attribute. Specifically, if the coefficient of variation of a certain type of target data (such as axial acceleration or engine vibration parameters in high dynamic subjects) in the previous adjacent flight state is large, it indicates that the target data has drastic numerical fluctuations, continuous active characteristics, or potential abnormal trends. At this time, the data processing unit 1012 will increase the importance of the data type attribute of the target data in the current flight state. If the coefficient of variation is small, it indicates that the target data is in a stable state, with minimal numerical fluctuations or is in a static state. In this case, the data processing unit 1012 keeps the initial data type attribute importance of the target data unchanged or lowers the data type attribute importance of the target data.

[0061] It should be noted that this step quantifies the dispersion and activity characteristics of the data collected in the previous adjacent flight state through the data processing unit 1012, and performs positive compensation or negative correction on the importance of the initial data type attributes, effectively making up for the lag of the preset static weights of the host computer 20. In addition, it effectively solves the problem that key continuous signals may be suppressed due to sudden changes in the mission focus during the transition between different flight states, further optimizes the allocation accuracy of cache priority, and ensures that the airborne integrated data acquisition recorder 10 can always focus limited cache resources on the most informational data dimensions during the evolution of multi-stage complex test flight missions, significantly improving the intelligence level of complex multi-source heterogeneous data acquisition.

[0062] In some embodiments, the host computer 20 is also used to respond to the weight allocation operation input by the user, and for each flight state, set the importance of the data type attributes corresponding to each of the multiple data acquisition modules 101 according to the business attributes of the data collected by each of the multiple data acquisition modules 101.

[0063] The user-input weight allocation operation refers to the process by which technicians or flight test engineers manually input or adjust the weight scores of each data acquisition module 101 under different flight states through the visual configuration interface of the host computer 20, based on the flight mission book or test outline for a specific flight state.

[0064] The business attributes of collected data refer to the logical functions and safety value classifications that the target data carries in flight missions.

[0065] In this embodiment, the host computer 20 receives the weight scores entered by the user through a visual interface. For each specific flight state, based on the business attributes of the data collected by each data acquisition module 101, the corresponding data type attribute importance is pre-set. For example, in carrier-based aircraft landing tests or autonomous alignment tests, since the digital acquisition module is responsible for acquiring digital status data such as landing gear retraction and extension status and landing hook working position, which has extremely high safety value attributes, the user sets the data type attribute importance of the digital acquisition module to the highest level (e.g., weight value 0.95) through the host computer 20. Since the audio and video data acquisition module is mainly used to acquire external wing monitoring images or non-core area images, the user sets the data type attribute importance of the audio and video data acquisition module to a lower level (e.g., weight value 0.4) while ensuring bus data transmission. These preset data type attribute importance levels are distributed to each data processing unit 1012 through the backplane bus.

[0066] It should be noted that the visualization interface of the host computer 20 enables users to flexibly configure weights according to the attributes of the test flight subjects, transforming human experience into the business value benchmarks preset by each data acquisition module 101. This achieves targeted resource allocation for specific test flight tasks, ensuring that core business data with high security value obtains absolute bandwidth priority in complex concurrent environments, and greatly improving the task adaptability and critical information protection capabilities of the data acquisition and recording system under different test flight tasks.

[0067] In some embodiments, the data processing unit 1012 is further configured to label the target data with channel number, data type and acquisition time, and encapsulate the labeled target data using the target data packet protocol.

[0068] The channel number is a unique identifier assigned by the acquisition and recording system to the physical interface or logical link of each data acquisition module 101. It is used to identify the physical source of the target data in a multi-channel concurrent acquisition environment, so as to ensure that the target data can be accurately traced back to its source when played back at the back end.

[0069] Data type refers to a classification label used to characterize the original physical attributes or protocol type of the target data. For example, the label value "0x01" represents analog data, and "0x05" represents high-definition video stream data.

[0070] The target data packet protocol refers to the unified encapsulation format agreed upon between each data acquisition module 101 and the main control module 102. Optionally, this target data packet protocol is the Inter-Range Instrumentation Group (IRIG)-106 standard packet format. Optionally, the target data packet protocol defines the structure of the packet header, packet trailer, checksum, and metadata area, which can ensure that multi-source heterogeneous data has a standardized encapsulation shell during the transmission of data on the backplane bus.

[0071] In this embodiment, the data processing unit 1012 labels the target data acquired by the data acquisition unit 1011 with a unique channel number, the corresponding data type, and the precise acquisition time to obtain the metadata corresponding to the target data. Then, the data processing unit 1012 uses the metadata and the cache priority calculated in real time as a feature set to be encapsulated. Subsequently, the data processing unit 1012 uses a unified target data packet protocol to accurately map the feature set to a preset field in the protocol header, and logically combines it with the target data carrying the original information. Finally, a cyclic redundancy check code is added to generate a standardized protocol data packet for the target data.

[0072] It should be noted that by introducing the IRIG-106 standard package format to standardize and encapsulate multi-source heterogeneous data, and deeply coupling data such as channel number, data type, and acquisition time with dynamic priority tags, a standardized spatiotemporal correlation benchmark between multi-source heterogeneous data is constructed. This not only achieves high normalization of multi-source heterogeneous data during backplane bus transmission, but also ensures that other devices (such as host computer 20) can accurately trace the source of the multi-source heterogeneous data. From the architectural level, this supports the efficient parsing of complex flight test data and the consistent management of the entire life cycle.

[0073] In some embodiments, Figure 3 This is a schematic diagram of the structure of the data offloading and diversion module provided in the embodiments of this application. Figure 1 and Figure 3As can be seen from the diagram, the data acquisition and recording system may further include: a data offloading and diversion module 40 and a data offloading device. The data offloading and diversion module 40 is electrically or communicatively connected to the airborne integrated data acquisition and recording unit 10 through the data offloading device. The data offloading and diversion module 40 may include a protocol parsing unit 402 and a file creation unit 403. The protocol parsing unit 402 is used to take the binary sequence of the target data as input data for each target data, extract the structural features and statistical distribution features of the binary sequence through the data type identification module, and generate a type label corresponding to the target data based on the structural features and statistical distribution features. The type label is used to characterize the data type of the target data in the target data packet protocol. The structural features include at least periodic delimiters, field alignment patterns, sequence dependency degree, and the degree of repetition of fixed offsets. The statistical distribution features include at least information entropy, bit conversion density, value range distribution and mean / variance, and autocorrelation coefficient. The file creation unit 403 is used to create corresponding logical storage files for target data with the same data type based on the identified data type, and write the target data into the corresponding logical storage files.

[0074] Among them, the data offloading device refers to the hardware interface device that realizes the physical connection and data transfer between the airborne integrated data acquisition recorder 10 and the ground data processing system, such as high-speed Ethernet, fiber channel or dedicated card reader interface, etc.

[0075] The binary sequence of target data refers to the raw information stream read from the airborne integrated data acquisition recorder 10 without any protocol stripping. This binary sequence contains at least the encapsulated protocol header and the payload of the target data.

[0076] The data type identification module refers to the intelligent algorithm component built into the protocol parsing unit 402. By performing deep pattern analysis on the binary sequence, it can automatically determine the data type of the target data without human intervention.

[0077] Periodic delimiters are specific bit patterns that appear at fixed intervals in a binary sequence and are used to determine the boundaries of data frames.

[0078] Field alignment mode refers to the arrangement pattern of data fields in a binary sequence at the byte or bit level.

[0079] Sequence dependency refers to the numerical or logical correlation between the current binary sequence of data blocks and their adjacent data blocks, and is used to identify streaming data with continuous characteristics.

[0080] The repetition of a fixed offset refers to the frequency with which the same bit pattern appears at a specific position in a binary sequence.

[0081] Information entropy is an indicator that quantifies the uncertainty or randomness of information in a binary sequence.

[0082] Bit transition density refers to the frequency of switching between "0" and "1" in a binary sequence, and is used to reflect the activity of physical signals at the binary level.

[0083] Value range distribution and mean / variance refer to the statistical description of the numerical range and fluctuation of sampled data of binary sequences, used to distinguish between slowly changing analog signals and high-frequency fluctuating vibration signals.

[0084] The autocorrelation coefficient measures the degree of correlation between binary sequences at different times and is used to identify acquired signals with strong periodic characteristics.

[0085] Logical storage files refer to independent files created on the storage medium of the data offloading and diversion module 40 according to the identified data types, realizing the sorting and storage of massive heterogeneous data at the ground end.

[0086] Optionally, the data offloading and diversion module 40 may further include a data reading unit 401 and a data writing unit 404.

[0087] Specifically, the data reading unit 401 is used to read the recorded data in the data recording module 103 and put it into a temporary buffer; the data writing unit 404 is used to write the data in the temporary buffer into the data file with the corresponding name according to the data type.

[0088] In this embodiment, the data reading unit 401 establishes a physical link with the airborne integrated data acquisition recorder 10 through the data offloading device, and sequentially reads the binary sequence of the target data that has not been stripped of the protocol from the data recording module. To ensure the continuity of the parsing process, the data reading unit 401 stores the read binary sequence into an internal temporary buffer in real time, providing a stable input stream for subsequent deep protocol analysis.

[0089] Subsequently, the protocol parsing unit 402 retrieves the binary sequence from the temporary buffer and inputs it into the built-in data type identification module. This module uses a two-dimensional analysis method combining "microstructure + macrostatistics" to extract features from the binary sequence. At the microstructure level, the module searches for periodic delimiters in the binary sequence to lock frame boundaries and analyzes structural features such as field alignment patterns and the degree of repetition of fixed offsets. At the macrostructure level, the module simultaneously calculates information entropy, bit conversion density, value range distribution, mean / variance, and autocorrelation coefficients. By fusing and comparing the extracted structural features and statistical distribution features, the module automatically determines the protocol category of the current bitstream and generates the corresponding type label.

[0090] Finally, the file creation unit 403 dynamically creates the corresponding logical storage file in the ground storage medium based on the type tag parsed by the protocol parsing unit 402. The data writing unit 404 extracts the identified target data blocks from the temporary buffer in real time, sorts them according to the type tag, and writes them into the corresponding logical storage file.

[0091] It should be noted that by constructing an adaptive protocol identification mechanism based on a two-dimensional pattern analysis of "microstructure + macro statistics", the data offloading and diversion module 40 achieves deep feature extraction and automated protocol discrimination of massive and messy raw binary data streams under extreme conditions without manual intervention and without relying on airborne index files. This ensures accurate sorting and efficient structured storage of multi-source heterogeneous data on the ground, significantly improving the efficiency and robustness of post-processing analysis of complex flight test mission data. In other words, the data offloading and diversion module 40 can solve the above-mentioned technical problem P1.

[0092] To more intuitively understand the working mechanism of the data offloading and diversion module 40, Figure 4 This is a flowchart illustrating the working process of the data offloading and diversion module provided in this application embodiment. Figure 4 It can be seen from this: First, the data reading unit establishes a physical link through the data offloading device, sequentially reading the binary sequence of the target data (without protocol stripping) from the data recording module and placing it into an internal temporary buffer. Then, the protocol parsing unit retrieves the binary sequence from the temporary buffer, performs deep parsing according to the target data packet protocol, and automatically obtains the data type of the target data using a built-in data type identification module. Next, the data offloading and diversion module enters the decision-making stage. Specifically, the file creation unit determines whether the current data type is new based on the identification result: if so, a new data file is created in the ground storage medium and named strictly according to the data type name. After confirming or creating the corresponding file, the data writing unit extracts the identified target data blocks from the temporary buffer in real time and writes them into the corresponding named data files according to their data type, achieving "sorting" storage of data. Finally, the data offloading and diversion module continuously checks whether the target data stored in the data recording module has been read completely: if not, it loops back to the reading step to read the next binary sequence for parsing; until all original information streams are processed, completing the entire offloading and diversion process.

[0093] In some embodiments, combined with Figure 1The airborne integrated data acquisition recorder 10 may further include: a data recording module 103, which is electrically or communicatively connected to the main control module 102; wherein, the data recording module 103 is used to record the packaged target data so that the data offloading and diversion module 40 can read the target data through the data offloading device.

[0094] The data recording module 103 can be represented as a data recording disk in hardware form. Optionally, the data recording disk typically uses solid-state storage media (such as a solid-state drive, SSD), which has the characteristics of high overvoltage resistance, wide temperature operation and high-speed continuous read and write, and can meet the bandwidth requirements of concurrent writing of high-definition audio and video streams and high-speed bus data.

[0095] In the embodiments of this application, the data recording module 103 receives in real time the protocol data packets output by the main control module 102, which are encapsulated by the data processing unit 1012 and carry cache priority. During the recording process, the data recording module 103 utilizes its non-volatile storage characteristics to ensure the physical safety of the data in complex airborne environments (such as severe vibration or unexpected power outages). After the flight mission ends, the data recording module 103 switches to unloading mode. At this time, the data unloading device is connected to the airborne integrated data acquisition recorder 10 through a physical interface. The data reading unit 401 of the data unloading diversion module 40 reads the binary sequence of the target data that has not been stripped of the protocol directly from the data recording module 103 according to the timing relationship, providing the most basic data support for subsequent automated sorting and analysis on the ground.

[0096] It should be noted that the data recording module 103, by adopting solid-state storage media with industrial-grade durability and in conjunction with the priority scheduling mechanism of the main control module 102, ensures that the protocol data packets of multi-source heterogeneous data can be reliably solidified in a "what is recorded is what is obtained" manner during complex flight test missions. This not only ensures the integrity of the original binary sequence at the physical level, but also provides a solid data benchmark for the subsequent automated parsing and accurate sorting of index-free files by the ground-side data offloading and diversion module 40 by retaining complete protocol packet header metadata.

[0097] Optionally, combined Figure 1 The airborne integrated data acquisition recorder 10 may also include a power supply module 104, which provides a stable normal operating voltage for the data recording module 103, the main control module 102, each data acquisition module 101 and the backplane bus communication link.

[0098] Optionally, the airborne integrated data acquisition recorder 10 adopts a stacked structure, with each data acquisition module 101 stacked vertically or horizontally via a standard chassis backplane interface. Users can flexibly select one or more data acquisition modules 101 with different functions (such as digital acquisition modules, analog acquisition modules, or audio / video acquisition modules) to combine according to the actual flight test mission's acquisition requirements.

[0099] It should be noted that this stacked structure, combined with the "single module, single type" design concept, not only improves the integration of the data acquisition and recording system in physical space, but also effectively suppresses electromagnetic interference between modules through independent power supply of the power modules. Furthermore, this hardware configuration is deeply compatible with the aforementioned "manual guidance + mechanism self-adaptation" two-layer evaluation system, enabling the data acquisition and recording system to maintain the flexibility of the physical link while ensuring high reliability and determinism in logical scheduling of data recording in large-scale, multi-channel heterogeneous data environments. This greatly expands the applicability of the data acquisition and recording system in various manned / unmanned aircraft flight test missions.

[0100] In some embodiments, combined with Figure 1 The data acquisition and recording system may further include: a configuration loading and status monitoring module 30, which is electrically and communicatively connected to the airborne integrated data acquisition recorder 10 and the host computer 20, respectively; wherein, the configuration loading and status monitoring module 30 is used to receive the card slot number and module type of each of the multiple data acquisition modules 101 sent by the airborne integrated data acquisition recorder 10, as well as the total number of data acquisition modules 101; to receive user configuration information sent by the host computer 20, which is generated by the host computer 20 in response to the user's configuration operation; and to perform data type acquisition configuration and system time source configuration for the airborne integrated data acquisition recorder 10 based on the card slot number and module type of each of the multiple data acquisition modules 101, the total number of data acquisition modules 101, and the user configuration information.

[0101] Among them, the slot number refers to the physical location number of each data acquisition module 101 on the back panel of the airborne integrated data acquisition recorder 10 chassis.

[0102] The module type refers to the hardware function category to which each data acquisition module 101 belongs, such as digital signal acquisition function, analog signal acquisition function, or audio and video acquisition function.

[0103] The total number of data acquisition modules 101 refers to the sum of all data acquisition modules 101 physically present in the current airborne integrated data acquisition recorder 10. This number is used for hardware self-testing and global resource allocation during the initialization phase of the data acquisition and recording system.

[0104] User configuration information refers to the set of instructions generated by the host computer 20 after responding to the user's input weight allocation operation, which includes all acquisition task parameters and system time source parameters.

[0105] Optionally, Figure 5 This is a schematic diagram of the configuration loading and status monitoring module provided in the embodiments of this application. Figure 5 As can be seen from the above, the configuration loading and status monitoring module 30 may include a status monitoring unit 301, a user configuration unit 302, a data acquisition configuration unit 303, and a time source configuration unit 304.

[0106] The status monitoring unit 301 is used to monitor and receive physical status information such as the slot number, module type and total number of data acquisition modules 101 sent by the airborne integrated data acquisition recorder 10 in real time, and send the physical status information as a physical index to the acquisition configuration unit 303.

[0107] User configuration unit 302 is used to read system user configuration information from the visual interface of host computer 20 to obtain user configuration parameters and system time source configuration information of each data acquisition module 101, and to send them to acquisition configuration unit 303 and time source configuration unit 304 respectively by adopting a traffic splitting strategy.

[0108] The acquisition configuration unit 303 is used to compare the physical status information provided by the status monitoring unit 301 with the logical configuration requirements (i.e., user configuration parameters) sent by the user configuration unit 302, generate the final hardware acquisition configuration information, and send it to the airborne integrated data acquisition recorder 10.

[0109] The time source configuration unit 304 is used to generate system time source configuration flag information based on the system time source configuration information sent by the user configuration unit 302, and send it to the airborne integrated data acquisition recorder 10.

[0110] In the embodiments of this application, combined with Figure 5 The status monitoring unit 301, through communication with the airborne integrated data acquisition recorder 10, monitors and acquires physical status information such as the card slot number, module type, and total number of all physically present data acquisition modules 101 on the chassis backplane, constructs a physical topology view of the underlying acquisition and recording system, and sends this physical status information to the acquisition configuration unit 303.

[0111] Subsequently, the user configuration unit 302 reads the user configuration information containing the user weight allocation operation results from the visualization interface of the host computer 20, obtains the user configuration parameters of each data acquisition module and the system time source configuration information, and sends them to the acquisition configuration unit 303 and the time source configuration unit 304 respectively.

[0112] Next, the acquisition configuration unit 303 performs a "physical-logical" mapping operation, comparing the physical status information of each data acquisition module 101 fed back by the status monitoring unit 301, such as the card slot number, module type, and total number of data acquisition modules 101, with the user configuration parameters distributed by the user configuration unit 302. For example, when the user configuration information requires a high weight to be assigned to a specific video stream, the acquisition configuration unit 303 will lock the audio and video acquisition module on the corresponding card slot number, generate the final hardware acquisition configuration information, and send it to the airborne integrated data acquisition recorder 10 for acquisition task configuration.

[0113] Finally, the time source configuration unit 304 generates system time source configuration flag information based on the system time source configuration information received from the user configuration unit 302 and sends it to the airborne integrated data acquisition recorder 10 for system time configuration.

[0114] It should be noted that the underlying physical topology view is constructed in real time by the status monitoring unit 301, and the "physical-logical" mapping operation is performed by the acquisition configuration unit 303. The user configuration information obtained by the host computer 20 is automatically compared with the physical status such as the card slot number and module type of the in-situ data acquisition module 101 and aligned with the task. Combined with the unified time reference generated by the time source configuration unit 304, the deep decoupling and flexible matching of hardware resources and flight test mission requirements are realized. From the architecture level, it supports the rapid reconstruction, accurate identification and time unification of the multi-source heterogeneous acquisition system, which significantly improves the efficiency of complex flight test mission deployment and the robustness of system operation.

[0115] In other words, the configuration loading and status monitoring module 30 achieves deep decoupling between airborne hardware resources and flight test mission logic, enabling the data acquisition and recording system to have the ability of "plug and play" for heterogeneous data acquisition modules (i.e., n data acquisition modules 101) and "one-click reconstruction" of acquisition tasks. It fundamentally solves the defects of hardware redundancy, complex wiring and poor task adaptability in the existing technology from the architectural level, and significantly reduces the full life cycle support cost of the data acquisition and recording system, that is, it can solve the above-mentioned technical problem P2.

[0116] In some embodiments, Figure 6 This is a schematic diagram of the main control module provided in the embodiments of this application. Figure 6As can be seen, the main control module 102 may include a time synchronization unit 1023; wherein, the time synchronization unit 1023 is used to obtain the system time source configuration flag information during the configuration loading and status monitoring module 30's system time source configuration process; according to the system time source configuration flag information, it accesses and receives external IRIG-B code or IEEE1588 time synchronization to complete the internal time synchronization of the main control module 102; after time synchronization, it sends system synchronization time messages and PPS second pulse signals to multiple data acquisition modules 101 through the backplane bus respectively.

[0117] Among them, IRIG-B code refers to a serial time standard format specifically used in airborne and avionics environments.

[0118] The IEEE 1588 Network Time Protocol signal refers to a network synchronization standard based on a precise time protocol.

[0119] It is important to note that the system synchronization time message is sent via broadcast. The system synchronization time message is encapsulated in Transaction Layer Packet (TLP) format, and the TLP definition for the system synchronization time message is shown in Table 1.

[0120] Table 1: TLP Definitions for System Synchronization Time Messages The Fmt field is set to binary value 011, indicating that the TLP header size is 4 double words with data; the Type field is set to binary value 10011, indicating a request broadcast message with message type MsgD; the Message Code field is set to binary value 01111111, indicating Vendor_Defined Type 1; the Vendor ID field is set to hexadecimal value 005h, indicating a custom message; the SyncTimeData field is 4 data words, each occupying 2 bytes. When the system time is in IEEE1588 time format, the SyncTimeData definition is shown in Table 2; when the system time is in IRIG-B code time format, the SyncTimeData definition is shown in Table 3.

[0121] Table 2: Definition of SyncTimeData in IEEE 1588 Time Format Second represents the total number of seconds since 1970, expressed in hexadecimal numbers.

[0122] Table 3: SyncTimeData Definition for IRIG-B Time Format (Type=0) Among them, Day Of Year is in Binary-Coded Decimal (BCD) form, representing 000~365 days; hours is in BCD form, representing BCD00~23 hours; minutes is in BCD form, representing 00~59 minutes; and Seconds is in BCD form, representing 00~59 seconds.

[0123] In this embodiment, firstly, during the initialization configuration of the airborne integrated data acquisition recorder 10 by the configuration loading and status monitoring module 30, the time synchronization unit 1023 captures the system time source configuration flag information issued by the time source configuration unit 304 in real time. Subsequently, the time synchronization unit 1023 performs protocol identification and parsing on the system time source configuration flag information. If it is identified as an external analog / digital synchronization source, it demodulates and extracts the IRIG-B code with high-precision serial characteristics and uses it as the internal alignment time reference. If it is identified as a network synchronization source, it obtains the IEEE 1588 time through the Precision Time Protocol (PTP) stack built into the time synchronization unit 1023 and uses it as the internal alignment time reference. Finally, the time synchronization unit 1023 encapsulates the aligned time reference into a system synchronization time message and broadcasts it synchronously to each data acquisition module 101 through the backplane bus along with the PPS second pulse signal.

[0124] It should be noted that the time synchronization unit 1023 achieves adaptive compatibility of the acquisition and recording system with multiple timing protocols under complex flight test missions by uniformly parsing and transparently forwarding the system time source configuration flag information. This ensures that the multi-source heterogeneous data has high-precision time stamp consistency at the source of generation, and provides a reliable judgment benchmark for the main control module 102 to perform time-based cache priority scheduling.

[0125] Optionally, combined Figure 2 The data acquisition module 101 may also include: a system time receiving unit 1014 and an acquisition configuration receiving unit 1015.

[0126] The system time receiving unit 1014 is used to receive the system synchronization time message and PPS second pulse signal distributed by the main control module 102 in real time through the backplane bus; after obtaining the whole second system synchronization time, it adds the nanosecond time within the second calculated by the current local crystal oscillator to form the acquisition timestamp, and provides the acquisition timestamp to the data processing unit 1012.

[0127] The data acquisition configuration receiving unit 1015 is used to receive and parse the data acquisition configuration information sent from the main control module 102, clarify the data acquisition task requirements of the current flight status (including channel opening status, sampling frequency and data type attributes, etc.), thereby activating and guiding the entire data acquisition module to execute the data acquisition task according to the preset strategy.

[0128] To more intuitively understand the working mechanism of the data acquisition module 101, Figure 7 This is a flowchart illustrating the working process of the data acquisition module provided in this application embodiment. Figure 7 It can be seen from this: First, the acquisition configuration receiving unit receives and parses the acquisition configuration information sent from the main control module via the backplane bus, clarifying the importance of the data type attributes corresponding to the current flight status. Then, the system time receiving unit receives the system synchronization time message and PPS second pulse signal distributed by the main control module in real time via the backplane bus. It obtains the whole-second system synchronization time through parsing and resets the internal nanosecond counter using the PPS signal as a trigger edge. High-frequency accumulation using a local crystal oscillator yields the nanosecond offset within a second, generating an acquisition timestamp with nanosecond-level resolution, which is provided to the data processing unit. Next, the data acquisition unit acquires the raw information streams (i.e., target data) of various data types in parallel through multiple channels. The data processing unit synchronously extracts multi-dimensional dynamic features (i.e., data transmission rate and data change entropy) from the target data and fuses these features with the importance of the data type attributes in the current flight status to determine the cache priority of the target data. Subsequently, the data processing unit, according to the target data packet protocol, labels the target data with a unique channel number, data type, and acquisition time, maps the cache priority label to a preset field in the protocol header, and encapsulates it together with the target data payload and cyclic redundancy check code into a standardized protocol data packet. Finally, the data output unit sends the encapsulated protocol data packet to the main control module, so that the main control module can perform adaptive scheduling based on the priority tag in the header of the protocol data packet.

[0129] It should be noted that by constructing a deep processing link of "high-precision time synchronization - multi-dimensional feature extraction - dynamic priority evaluation" on the data acquisition side, different flight state service attributes are deeply coupled with signal transient fluctuations and real-time link status. The transparent transmission of cache priority is achieved through standardized data packet protocol headers, enabling the acquisition and recording system to automatically make optimal resource scheduling decisions based on mission value and physical status. This fundamentally solves the bus conflict and frame loss risk when high-bandwidth multi-source heterogeneous data are concurrent, and significantly improves the determinism, real-time performance and consistency of data recording in complex flight test missions across all time and space dimensions.

[0130] Optionally, the data output unit 1013 further includes multiple data output buffers and a status register corresponding to each of the multiple data output buffers. The multiple data output buffers are used to temporarily store standardized protocol data packets with cache priority tags, encapsulated by the data processing unit 1012. The status register is used to characterize the operating status of the corresponding data output buffer in real time, storing information including status flags, the offset address of the data output buffer, and the length of the current protocol data packet.

[0131] Optionally, the status register also stores the cache priority of the target data calculated in real time by the data processing unit 1012.

[0132] It should be noted that the number of data output buffers is determined by the Field Programmable Gate Array (FPGA) chip resources used in the data acquisition module 101 and the preset storage depth, while the size of a single buffer is dynamically matched according to the instantaneous acquisition rate of the service attributes carried by the data acquisition module 101.

[0133] To more intuitively understand the working mechanism of the data output unit 1013, Figure 8 This is a flowchart illustrating the working process of the data output unit provided in the embodiments of this application. Figure 8 It can be seen from this: The data output unit receives standardized protocol data packets output by the data processing unit in real time. First, the data output unit reads the status flag bit in the status register corresponding to the current data output buffer. If the status flag bit is 0, it indicates that the data output buffer is idle or that the data within it has been read by the main control module. In this case, the data output unit immediately performs a write operation. If the status flag bit is not 0, the data output unit moves down to the next data output buffer and re-determines the status. After locking an idle data output buffer, the data output unit sequentially stores the protocol data packets into it. Subsequently, the data output unit synchronously writes the offset address of the data output buffer, the length of the protocol data packet, and the corresponding buffer priority of the protocol data packet into the corresponding status register, and modifies the status flag bit to 1 to send a "data ready" signal to the backplane bus, guiding the main control module to access the data output buffer to obtain the target data. Finally, the data output unit uses modulo operation logic to calculate the pointer to the next data output buffer. The calculation formula is: offset address of the next data output buffer = (offset address of the current data output buffer + BUFFER_SIZE) % (BUFFER_SIZE) N); where BUFFER_SIZE represents the byte capacity of a single data output buffer block, and N represents the total number of data output buffers (i.e., the number of status registers corresponding to a single data acquisition module 101). Simultaneously, to ensure that the control logic and data storage proceed synchronously, the data output unit automatically updates the pointer of the next status register. The calculation formula is: offset address of the next status register = (offset address of the current status register + L) % (N × L); where L represents the byte size of the status register. At this point, the output preparation work for the current cycle is completed, and the next round of loop traversal begins.

[0134] It should be noted that by establishing a hardware handshake mechanism based on status flags and a dual circular addressing logic based on modulo operations, a lock-free data interaction model was constructed. This ensures that massive heterogeneous data can achieve deterministic sequential transmission and cyclical utilization of storage space with extremely low communication overhead, significantly improving the real-time output performance and memory scheduling efficiency of the acquisition and recording system.

[0135] Optionally, combined Figure 5 The main control module 102 may include a board identification unit 1021, a data acquisition and configuration receiving and sending unit 1022, a data receiving unit 1024, a high-speed circular buffer 1025, and a data storage unit 1026.

[0136] The board identification unit 1021 is used to read each data acquisition module 101 inserted into the airborne integrated data acquisition recorder 10 via the backplane bus. Optionally, the board identification unit 1021 is specifically used to read the physical status information of each data acquisition module 101, such as the card slot number and module type.

[0137] The acquisition configuration receiving and sending unit 1022 is used to receive the acquisition configuration message sent by the acquisition configuration unit 303 and the system time source configuration flag information sent by the time source configuration unit 304, send the acquisition configuration message to the corresponding data acquisition module 101 through the backplane bus, and send the system time source configuration flag information to the time synchronization unit 1023.

[0138] The data receiving unit 1024 is used to receive protocol data packets sent by the data output units 1013 of all data acquisition modules 101 via the backplane bus, and send them to the high-speed circular buffer 1025.

[0139] The high-speed circular buffer 1025 is used to temporarily store all protocol data packets sent by each data acquisition module 101, which are sorted according to the cache priority.

[0140] The data storage unit 1026 is used to read all protocol data packets from the high-speed circular buffer 1025 and coordinate the data recording module 103 to complete the non-volatile storage and solidification.

[0141] Optionally, the data receiving unit 1024 includes a data acquisition status monitoring subunit and a Direct Memory Access (DMA) data transfer subunit. Specifically, the data acquisition status monitoring subunit is used to read the status registers corresponding to the data output buffers of all data acquisition modules 101 via the backplane bus. Optionally, the data acquisition status monitoring subunit can also synchronously extract the cache priority of the current protocol data packet stored in the status register and send the cache priority to the DMA data transfer subunit.

[0142] The DMA data transfer subunit is specifically used to receive the value of the status register sent by the acquisition status monitoring subunit, read the protocol data packets of all data output buffers through the backplane bus according to the value of the status register, and store the protocol data packets into the high-speed circular buffer according to the buffer priority from large to small.

[0143] To more intuitively understand the working mechanism of the main control module 102, the following example illustrates the specific working process of the main control module 102: After the main control module 102 is started, the board identification unit 1021 first monitors the physical slot of the airborne integrated data acquisition recorder 10 inserted through the backplane bus, reads the physical status information such as the card slot number, module type and total number of each data acquisition module 101, and sends the physical status information to the configuration loading and status monitoring module 30 to complete the initial construction of the hardware topology.

[0144] Next, the acquisition configuration receiving and sending unit 1022 receives the acquisition configuration message and system time source configuration flag information sent from the configuration loading and status monitoring module 30. Subsequently, the acquisition configuration receiving and sending unit 1022 performs a dual-path parallel distribution task: First, it sends the received acquisition configuration message to the corresponding data acquisition module 101 through the backplane bus to activate the acquisition strategy of each data acquisition module; Second, it sends the received system time source configuration flag information to the time synchronization unit 1023.

[0145] Subsequently, the time synchronization unit 1023 performs protocol identification and parsing on the system's time source configuration flag information, and connects to external IRIG-B or IEEE1588 time synchronization. After completing time synchronization, the system synchronization time message and second pulse (PPS) signal are synchronously broadcast to all data acquisition modules 101 via the backplane bus, ensuring that the data of the entire acquisition and recording system has a unified high-precision time tag at the source of generation.

[0146] Then, the data receiving unit 1024 uses a combination of active monitoring and high-speed transfer to receive protocol data packets sent by the data output units 1013 in each data acquisition module 101 in real time, and stores the protocol data packets in the high-speed circular buffer 1025. Specifically, the data receiving unit 1024 reads the status flag bits and cache priorities in the status registers of each data acquisition module 101 in real time through the acquisition status monitoring subunit. Once a "data ready" signal is detected (i.e., the status flag bit is 1), the DMA data transfer subunit immediately pulls the protocol data packets from the data acquisition module 101 and stores them in the high-speed circular buffer 1025 according to the order of cache priority from large to small, realizing a seamless connection from distributed acquisition to centralized aggregation.

[0147] Finally, the data storage unit 1026 sequentially reads the protocol data packet from the high-speed circular buffer 1025, and then the data storage unit 1026 coordinates the data recording module 103 to complete the non-volatile storage and solidification of the protocol data packet.

[0148] It should be noted that the main control module 102 constructs a closed-loop processing architecture that includes automatic hardware topology identification, system-wide time synchronization broadcasting, and active monitoring and transfer of multi-source heterogeneous data. Combined with cache priority-based caching and ordered solidification logic, it achieves centralized and efficient scheduling of distributed acquisition resources, ensuring the storage timing consistency of multi-source heterogeneous data and the high-fidelity recording of key data under complex flight test conditions at the system level.

[0149] To more intuitively understand the working mechanism of the data receiving unit 1024, Figure 9 This is a flowchart illustrating the working process of the data receiving unit provided in the embodiments of this application. Figure 9 It can be seen from this: First, the acquisition status monitoring subunit internally maps M×N status register mapping tables, where M represents the total number of in-place data acquisition modules and N represents the number of registers corresponding to a single data acquisition module. After the data receiving unit 1024 starts, it performs a cyclic scanning task through the acquisition status monitoring subunit to read the value of the current status register (nth status register) of the current data acquisition module (m-th data acquisition module). The acquisition status monitoring subunit starts its traversal search from the data acquisition module numbered m=0 and the n=0th status register. During the traversal, the acquisition status monitoring subunit reads the "status flag bit" of the current status register. If the status flag bit is 1, it determines that the data acquisition module has a "data ready" signal and immediately extracts the offset address of the data output buffer, the length of the protocol data packet, and the buffer priority corresponding to the protocol data packet recorded in the status register. If the status flag bit is 0, it means that there is no ready data in the data output buffer, and the acquisition status monitoring subunit automatically jumps to the next data acquisition module for horizontal traversal by performing a modulo operation m=(m+1)%M.

[0150] Subsequently, upon detecting the data ready signal, the DMA data transfer subunit intervenes and performs high-speed data fetching. Before initiating the transfer, the DMA data transfer subunit first checks the empty flag of the high-speed circular buffer. If the empty flag is 1, it indicates that the buffer space is sufficient. At this time, the DMA data transfer subunit reads the corresponding protocol data packet from the data output buffer of the data acquisition module via the backplane bus using DMA, based on the offset address of the extracted data output buffer and the length of the protocol data packet, and efficiently stores it into the corresponding subspace of the high-speed circular buffer according to the buffer priority from largest to smallest. If the empty flag is 0, it indicates that the buffer space is insufficient. At this time, the DMA data transfer subunit moves down to the next storage area of ​​the high-speed circular buffer and re-evaluates the situation.

[0151] Finally, after completing a data fetch, to achieve a closed-loop link, the DMA data transfer subunit writes a clear signal to the corresponding status register via the backplane bus (i.e., resets the status flag to 0) to release the data output buffer for the data acquisition module to write to again. After completing the processing of the current status register or skipping an idle status register, the acquisition status monitoring subunit updates the pointer of the status register using a dual modulo operation logic. The calculation formula is: offset address of the next status register = (offset address of the current status register + L)%(N×L), and simultaneously executes m=(m+1)%M to jump to the next data acquisition module, realizing traversal monitoring and dynamic data extraction of all data acquisition modules.

[0152] It should be noted that by establishing a hardware awareness mechanism based on M×N status register mapping tables and a cache priority-driven DMA adaptive scheduling strategy, the on-demand allocation and high-value priority of distributed acquisition resources in the centralized aggregation process are realized. This eliminates the risk of bus congestion caused by the concurrency of multiple heterogeneous data from the bottom layer, and ensures deterministic transmission and spatiotemporal consistency recording of massive heterogeneous data under extreme bandwidth load.

[0153] To more intuitively understand the working mechanism of the airborne integrated data acquisition recorder 10, Figure 10 This is a flowchart illustrating the working process of the airborne integrated data acquisition and recording device provided in the embodiments of this application. Figure 10 It can be seen from this: First, the airborne integrated data acquisition recorder obtains the physical status information of all in-situ data acquisition modules, including slot number, module type, and total quantity, through the main control module, and sends this physical status information to the configuration loading and status monitoring module. Subsequently, the airborne integrated data acquisition recorder receives data acquisition configuration information and system time source configuration flag information distributed by the configuration loading and status monitoring module.

[0154] Next, the main control module adaptively connects to the external IRIG-B code time synchronization signal or the IEEE 1588 network time protocol signal according to the system time source configuration flag information to complete the internal time synchronization. After synchronization is completed, the main control module broadcasts the system synchronization time message and the PPS second pulse signal to all data acquisition modules.

[0155] Subsequently, each data acquisition module completes the acquisition of various types of data according to the data acquisition configuration information and system synchronization time, and sends the acquired data back to the main control module.

[0156] Finally, the main control module receives protocol data packets sent by all data acquisition modules through the backplane bus, and records the protocol data packets in descending order of cache priority onto the non-volatile data recording disk (i.e., the data recording module), thereby achieving high-fidelity solidified storage of complex multi-source heterogeneous data.

[0157] To more intuitively understand the working mechanism of this data acquisition and recording system, Figure 11 This is a flowchart illustrating the working process of the data acquisition and recording system provided in this application embodiment. Figure 11 It can be seen from this: First, the airborne integrated data acquisition recorder identifies and obtains physical status information such as the card slot number, module type, and total quantity of all data acquisition modules through the backplane bus, and sends this physical status information to the configuration loading and status monitoring module.

[0158] Next, the configuration loading and status monitoring module receives user configuration information from the host computer and, in conjunction with the aforementioned physical status information, completes the data acquisition configuration information and system time source configuration flag information for the airborne integrated data acquisition recorder.

[0159] Subsequently, the airborne integrated data acquisition recorder activates each data acquisition module based on the received data acquisition configuration information and system time source configuration flag information, completing the parallel acquisition and non-volatile storage and solidification of multiple heterogeneous data.

[0160] Finally, in the post-processing stage, the data offloading and diversion module establishes a physical link through the data offloading device, offloading and diverting the raw binary sequence stored on the data recording module of the airborne integrated data acquisition recorder to the host computer, and using an adaptive protocol identification mechanism to achieve accurate sorting and efficient post-processing analysis of multi-source heterogeneous data.

[0161] Understandably, this data acquisition and recording system achieves deep decoupling and efficient collaboration between airborne heterogeneous hardware resources and complex flight test mission requirements by constructing a full lifecycle data processing link from "automatic identification of physical topology and dynamic configuration of mission requirements" to "parallel acquisition and orderly storage with priority tags" and then to "automatic sorting after the event". While ensuring the determinism and temporal consistency of data recording in a high-bandwidth concurrent environment, it greatly improves the efficiency of heterogeneous data flow from front-end acquisition to back-end data analysis.

[0162] It should be noted that the airborne integrated data acquisition and recording method provided in this application embodiment is applied to Figure 1 , Figure 2 , Figure 3 , Figure 5 and Figure 6 Any of the airborne integrated data acquisition and recording systems shown. The following uses this acquisition and recording system as an example to describe in detail the airborne integrated data acquisition and recording method provided in this application embodiment: Figure 12 This is a flowchart illustrating the airborne integrated data acquisition and recording method provided in an embodiment of this application. Figure 12 As shown, the method includes the following steps 1201-1204.

[0163] Step 1201: For each data acquisition module, acquire the target data under the current flight status through the data acquisition unit.

[0164] Step 1202: The data processing unit determines the cache priority of the target data based on the importance of the data type attributes of the data acquisition module in the current flight state, as well as the data transmission rate and data change entropy of the target data; the importance of the data type attributes of the data acquisition module is different in different flight states.

[0165] Optionally, the data processing unit determines the cache priority of the target data based on the importance of the data type attributes of the data acquisition module in the current flight state, as well as the data transmission rate and data change entropy of the target data. This can include: obtaining the importance of the data type attributes of the data acquisition module in the current flight state sent by the host computer through the data processing unit; using the ratio of a preset baseline transmission rate to the data transmission rate as a transmission compensation coefficient; calculating the absolute value of the difference between adjacent sampling points in the first sampling column of the target data, and extracting the statistical distribution characteristics of the absolute value of the difference within a preset sliding window as the data change entropy; wherein, the data change entropy increases with the increase of the fluctuation frequency and fluctuation amplitude of the target data; and determining the cache priority of the target data based on the importance of the data type attributes, the transmission compensation coefficient, and the data change entropy.

[0166] Optionally, obtaining the importance of data type attributes of the data acquisition module sent by the host computer in the current flight state through the data processing unit may include: obtaining the initial importance of data type attributes of the data acquisition module sent by the host computer in the current flight state through the data processing unit; obtaining the second sampling sequence of data collected by the data acquisition unit in the previous adjacent flight state; using the ratio of the standard deviation to the arithmetic mean of the second sampling sequence as the coefficient of variation of the target data; and correcting and compensating the initial importance of data type attributes based on the coefficient of variation to obtain the importance of data type attributes.

[0167] Optionally, by responding to the user's input weight allocation operation through the host computer, the importance of the data type attributes of each of the multiple data acquisition modules is set according to the business attributes of the data collected by each of the multiple data acquisition modules for each flight state.

[0168] Optionally, the configuration loading and status monitoring module receives the card slot number and module type of each of the multiple data acquisition modules sent by the airborne integrated data acquisition recorder, as well as the total number of data acquisition modules; receives user configuration information sent by the host computer, which is generated by the host computer in response to the user's configuration operation; and performs data type acquisition configuration and system time source configuration for the airborne integrated data acquisition recorder based on the card slot number and module type of each of the multiple data acquisition modules, the total number of data acquisition modules, and the user configuration information.

[0169] Optionally, during the system time source configuration process in the configuration loading and status monitoring module, the time synchronization unit obtains the system time source configuration flag information; based on the system time source configuration flag information, it accesses and receives external IRIG-B code or IEEE1588 time synchronization to complete the internal time synchronization of the main control module; after time synchronization, it sends system synchronization time messages and PPS second pulse signals to multiple data acquisition modules through the backplane bus.

[0170] Step 1203: Send the target data and the cache priority of the target data to the main control module through the data output unit.

[0171] Optionally, before step 703, the method may further include: labeling the target data with channel number, data type and acquisition time of the target data by the data processing unit, and encapsulating the labeled target data using the target data packet protocol.

[0172] Step 1204: Receive the target data and corresponding cache priority sent by each of the multiple data output units through the main control module; cache the multiple target data in descending order of cache priority.

[0173] Optionally, after step 1204, the method may further include: recording the encapsulated target data through the data recording module so that the data offloading and diversion module can read the target data through the data offloading device.

[0174] Optionally, after step 1204, the method may further include: using the protocol parsing unit of the data offloading and diversion module, for each target data, taking the binary sequence of the target data as input data, extracting the structural features and statistical distribution features of the binary sequence through the data type identification module, and generating a type label corresponding to the target data based on the structural features and statistical distribution features. The type label is used to characterize the data type of the target data in the target data packet protocol. The structural features include at least periodic delimiters, field alignment patterns, sequence dependency degree, and the degree of repetition of fixed offsets. The statistical distribution features include at least information entropy, bit conversion density, value range distribution and mean / variance, and autocorrelation coefficient. Using the file creation unit of the data offloading and diversion module, creating corresponding logical storage files for target data with the same data type based on the identified data type, and writing the target data into the corresponding logical storage files.

[0175] In this embodiment, the technical solution described in steps 1201-1204 above achieves real-time and accurate quantification of the priority of heterogeneous data streams by deeply deconstructing the dynamic characteristics of target data in each data acquisition module and coupling the importance of attributes associated with different flight states. This overcomes the limitations of traditional solutions that rely on adding conversion interfaces or replacing boards, resulting in low system integration and rigid bandwidth allocation. Through a multi-dimensional feature perception mechanism, the transient fluctuations of data from different physical channels are accurately captured using data change entropy, and timing deviations are corrected by combining timestamp offsets. This solves the problem of competition for limited bus resources when heterogeneous data floods in concurrently. Based on the calculated priority sequence, ordered cache scheduling from large to small is performed, which significantly reduces the risk of instantaneous congestion and buffer overflow on the internal bus. This fundamentally eliminates technical bottlenecks such as packet loss, out-of-order delivery, and timing distortion, ensuring that massive heterogeneous data can achieve highly reliable real-time processing and full lifecycle timing consistency under complex flight test mission scenarios and high bandwidth pressure.

[0176] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0177] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

Claims

1. An airborne integrated data acquisition and recording system, characterized in that, include: An airborne integrated data acquisition recorder (IGR) includes multiple data acquisition modules and a main control module. The main control module is electrically or communicatively connected to the multiple data acquisition modules. The multiple data acquisition modules acquire different types of data. Each data acquisition module includes a data acquisition unit, a data processing unit, and a data output unit. The data acquisition unit is used to acquire target data under the current flight status; The data processing unit is used to determine the cache priority of the target data based on the importance of the data type attributes of the data acquisition module in the current flight state, and the data transmission rate and data change entropy of the target data; wherein the importance of the data type attributes of the data acquisition module is different in different flight states; A data output unit is used to send the target data and the cache priority of the target data to the main control module. The main control module is used to receive target data and corresponding cache priorities sent by multiple data output units; and to cache the multiple target data in descending order of cache priority.

2. The airborne integrated data acquisition and recording system according to claim 1, characterized in that, Also includes: A host computer; the data processing unit is electrically or communicatively connected to the host computer; the data processing unit is used to determine the cache priority of the target data based on the importance of the data type attributes of the data acquisition module in the current flight state, and the data transmission rate and data change entropy of the target data, including: The data processing unit is specifically used to obtain the importance of the data type attribute of the data acquisition module in the current flight state, as sent by the host computer. The ratio of the preset base transmission rate to the data transmission rate is used as the transmission compensation coefficient. Calculate the absolute value of the difference between adjacent sampling points in the first sampling column of the target data, and extract the statistical distribution characteristics of the absolute value of the difference within a preset sliding window as the data change entropy; wherein, the data change entropy increases with the increase of the fluctuation frequency and fluctuation amplitude of the target data; The cache priority of the target data is determined based on the importance of the data type attribute, the transmission compensation coefficient, and the data change entropy.

3. The airborne integrated data acquisition and recording system according to claim 2, characterized in that, The data processing unit is specifically used to obtain the importance of the data type attributes of the data acquisition module in the current flight state, as sent by the host computer, including: The data processing unit is specifically used to obtain the importance of the initial data type attribute of the data acquisition module in the current flight state sent by the host computer; and to obtain the second sampling sequence of the data acquired by the data acquisition unit in the previous adjacent flight state; The ratio of the standard deviation to the arithmetic mean of the second sampling sequence is used as the coefficient of variation of the target data; The importance of the initial data type attribute is corrected and compensated based on the coefficient of variation to obtain the importance of the data type attribute.

4. The airborne integrated data acquisition and recording system according to any one of claims 1-3, characterized in that, The data processing unit is also used to label the target data with channel number, data type and acquisition time, and to encapsulate the labeled target data using the target data packet protocol.

5. The airborne integrated data acquisition and recording system according to claim 4, characterized in that, It also includes a data offloading and diversion module and a data offloading device. The data offloading and diversion module is electrically or communicatively connected to the airborne integrated data acquisition and recording unit through the data offloading device. The data offloading and diversion module includes a protocol parsing unit and a file creation unit. The protocol parsing unit is used to take the binary sequence of the target data as input data, extract the structural features and statistical distribution features of the binary sequence through the data type identification module, and generate a type label corresponding to the target data based on the structural features and statistical distribution features. The type label is used to characterize the data type of the target data in the target data packet protocol. The structural features include at least periodic delimiters, field alignment patterns, sequence dependency degree, and repetition degree of fixed offset. The statistical distribution features include at least information entropy, bit conversion density, value range distribution and mean / variance, and autocorrelation coefficient. The file creation unit is used to create a corresponding logical storage file for target data with the same data type according to the identified data type, and write the target data into the corresponding logical storage file.

6. The airborne integrated data acquisition and recording system according to claim 2, characterized in that, The host computer is also used to respond to the weight allocation operation input by the user, and for each flight state, set the importance of the data type attributes corresponding to each of the multiple data acquisition modules according to the business attributes of the data collected by each of the multiple data acquisition modules.

7. The airborne integrated data acquisition and recording system according to any one of claims 1-3, characterized in that, It also includes a configuration loading and status monitoring module, which is electrically and communicatively connected to the airborne integrated data acquisition recorder and the host computer, respectively; wherein, The configuration loading and status monitoring module is used to receive the card slot number and module type of each of the multiple data acquisition modules sent by the airborne integrated data acquisition recorder, as well as the total number of data acquisition modules. Receive user configuration information sent by the host computer, wherein the user configuration information is generated by the host computer in response to the user's configuration operation; Based on the slot number and module type of each of the multiple data acquisition modules, the total number of the data acquisition modules, and the user configuration information, the airborne integrated data acquisition recorder is configured with data type acquisition and system time source.

8. The airborne integrated data acquisition and recording system according to claim 7, characterized in that, The main control module includes a time synchronization unit; wherein... The time synchronization unit is used to obtain system time source configuration flag information during the configuration loading and status monitoring module's system time source configuration process. According to the system time source configuration flag information, it accesses and receives external IRIG-B code or IEEE1588 time synchronization to complete the internal time synchronization of the main control module. After time synchronization, the system synchronization time message and PPS second pulse signal are sent to multiple data acquisition modules via the backplane bus.

9. The airborne integrated data acquisition and recording system according to claim 5, characterized in that, It also includes a data recording module, which is electrically or communicatively connected to the main control module; wherein, The data recording module is used to record the packaged target data so that the data offloading and diversion module can read the target data through the data offloading device.

10. An airborne integrated data acquisition and recording method, characterized in that, Applied to the airborne integrated data acquisition and recording system as described in any one of claims 1-9, the airborne integrated data acquisition and recording system comprises: an airborne integrated data acquisition and recording device, the airborne integrated data acquisition and recording device comprising multiple data acquisition modules and a main control module, the main control module being electrically or communicatively connected to the multiple data acquisition modules; the multiple data acquisition modules acquiring different data types; each data acquisition module comprising a data acquisition unit, a data processing unit, and a data output unit; the method comprising: For each of the aforementioned data acquisition modules, target data under the current flight status is acquired through the data acquisition unit; The data processing unit determines the cache priority of the target data based on the importance of the data type attributes of the data acquisition module in the current flight state, as well as the data transmission rate and data change entropy of the target data; wherein, the importance of the data type attributes of the data acquisition module is different in different flight states. The target data and the cache priority of the target data are sent to the main control module through the data output unit; The main control module receives target data and corresponding cache priorities sent by multiple data output units; and caches the target data in descending order of cache priority.

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