Aircraft structural strength information physical fusion hierarchical model, system and method

Abstract

The invention discloses an aircraft structure strength information physical fusion hierarchical model based on reflective memory transmission, and the model comprises a ground flutter principle test demonstration subsystem which carries out the flutter analysis and load analysis of an aircraft structure based on flight parameters, and obtains the flutter response and load analysis result of the aircraft structure; the flutter response comprises vibration information and flutter allowance; the aircraft body structure virtual test demonstration subsystem is used for carrying out structure static strength analysis based on a load analysis result which is transmitted by the reflective memory and is from the ground flutter principle test demonstration subsystem to obtain a static strength analysis result of an aircraft structure; the airborne equipment is integrated with the vibration test platform demonstration subsystem, the vibration information transmitted by the reflection memory and from the ground flutter principle test demonstration subsystem is subjected to envelope statistics, a vibration load spectrum is obtained, the vibration load spectrum is used for dynamic intensity response analysis of the structure, and a dynamic response result of the aircraft structure is obtained. The unmanned aerial vehicle provides powerful guarantee for flight safety.

Description

Technical Field

[0001] This invention belongs to the field of strength digital design technology, specifically relating to an aircraft structural strength cyber-physical fusion hierarchical model, system, and method. Background Technology

[0002] Cyber-physical systems (CPS) achieve deep integration of the digital and physical worlds by constructing a two-way mapping between physical and cyberspace, supporting industrial design and testing of products based on digital virtual space. As an integrated, distributed, heterogeneous system, CPS combines physical and computational processes, comprising multiple subsystems with distinct functions. These subsystems coordinate through communication to achieve collaborative operation.

[0003] In traditional cyber-physical systems, data transmission typically relies on writing and reading files from computer hard drives. This method's data write and read rates are heavily dependent on the processing speed of simulation or experimental data acquired on the computer, resulting in significant time latency in the cyber-physical system. Data write and read operations are performed by accessing hard drive files through physical memory, and then the data is shared to the network mainline via network transmission protocols. Figure 1 As shown, this traditional data transmission method cannot meet the increasingly demanding real-time requirements of advanced cyber-physical systems. Especially in scenarios requiring rapid response and efficient data processing, this data transmission method based on hard disk file reading is inefficient. Summary of the Invention

[0004] The purpose of this invention is to provide a cyber-physical fusion hierarchical model, system, and method for aircraft structural strength. This invention enables real-time monitoring and analysis of aircraft structural strength, providing strong protection for flight safety.

[0005] Technical solution: A hierarchical model for information-physical fusion of aircraft structural strength based on reflective memory transmission, comprising: The ground flutter principle demonstration subsystem performs flutter and load analysis on the aircraft structure based on flight parameters to obtain the flutter response and load analysis results of the aircraft structure; the flutter response includes vibration information and flutter margin. The airframe structure virtual test demonstration subsystem performs static strength analysis on the structure based on the load analysis results from the ground flutter principle test demonstration subsystem transmitted via reflected memory, and obtains the static strength analysis results of the aircraft structure. The airborne equipment integrated vibration test platform demonstration subsystem performs envelope statistics on the vibration information transmitted from the ground flutter principle test demonstration subsystem via the reflection memory to obtain the vibration load spectrum. The vibration load spectrum is then used to perform dynamic strength response analysis of the structure to obtain the dynamic response results of the aircraft structure. In the aforementioned aircraft structural strength information-physical fusion hierarchical model, flight parameters are transmitted into the ground flutter principle test demonstration subsystem via reflective memory.

[0006] In the aforementioned aircraft structural strength information-physical fusion hierarchical model, flight parameters include: altitude H, Mach number M, acceleration g, angle of attack, engine low-pressure speed ENG_N1, and engine high-pressure speed ENG_N2.

[0007] In the aforementioned physical fusion hierarchical model of aircraft structural strength information, vibration information includes amplitude, frequency, and acceleration.

[0008] An aircraft structural strength cyber-physical fusion system based on the aforementioned aircraft structural strength cyber-physical fusion hierarchical model includes: The aircraft structural strength response output module receives flutter margin, static strength analysis results and dynamic response results transmitted from the reflection memory, performs real-time fusion processing, and displays the aircraft structural strength response in real time.

[0009] An information fusion method based on the aforementioned aircraft structural strength cyber-physical fusion system includes the following steps: The first step is to build a physical network for an aircraft structural strength information physical fusion system with reflective memory cards; The second step is to preprocess the flight parameters transmitted in real time in the physical network's reflective memory switch and store them in the physical network's reflective memory. The third step is that after the ground flutter principle test demonstration subsystem receives the flight parameters, it performs flutter analysis and load analysis on the aircraft structure to obtain the flutter response and load analysis results. The fourth step involves the ground flutter principle test demonstration subsystem performing real-time load analysis to obtain the load analysis results of the aircraft structure under various flight conditions, and transmitting them to the airframe structure virtual test demonstration subsystem. Simultaneously, the ground flutter principle test demonstration subsystem also transmits the vibration information of the aircraft structure under various flight conditions to the airborne equipment integrated vibration test platform demonstration subsystem. Fifth, after receiving the load analysis results, the virtual test demonstration subsystem for the airframe structure initiates the static strength analysis of the airframe structure, obtains the static strength analysis results, and lists the safety factor and strength margin of each part of the aircraft. The sixth step involves the demonstration subsystem of the airborne equipment integrated vibration test platform performing dynamic intensity response analysis based on vibration information to obtain dynamic response results. The seventh step involves the aircraft structural strength response output module receiving the aircraft structural flutter margin, static strength analysis results, and dynamic response results from the three subsystems, respectively. It then performs real-time information fusion processing and displays the aircraft structural strength response status in real time through the user interface.

[0010] In the aforementioned information fusion method of the aircraft structural strength information-physical fusion system, step five involves the static strength analysis as follows: First, a comprehensive analysis of the static mechanical properties of the airframe structure is performed based on the finite element method to generate a static strength proxy model of the aircraft airframe structure. After receiving the load analysis results, the airframe structure virtual test demonstration subsystem calls the static strength proxy model and uses numerical simulation to calculate the strain distribution and displacement of the airframe structure under different load conditions in real time.

[0011] In the aforementioned information fusion method of the aircraft structural strength cyber-physical fusion system, in step five, the airframe structure virtual test demonstration subsystem can also simulate various extreme working conditions to discover potential structural problems through the virtual environment.

[0012] In the aforementioned information fusion method of the aircraft structural strength cyber-physical fusion system, step six involves the dynamic strength response analysis as follows: The airborne equipment integrated vibration test platform demonstration subsystem performs simulation analysis based on the vibration environment spectrum in advance, and generates a proxy model of the aircraft body structure vibration response based on the simulation results. After receiving the vibration information transmitted by the ground flutter principle test demonstration subsystem, it performs envelope statistical analysis based on the vibration information, extracts key features in the vibration information, and generates a vibration load spectrum. The aircraft body structure vibration response proxy model performs dynamic strength response analysis of the structure based on the vibration load spectrum. Beneficial Effects: Cyber-physical systems increasingly emphasize high real-time performance, and any delay can lead to security risks. This invention proposes a cyber-physical fusion hierarchical model for aircraft structural strength based on reflective memory transmission. This model, through innovative reflective memory technology and a multi-layered collaborative architecture, constructs an efficient and reliable aircraft structural strength safety monitoring system, possessing the following significant technical advantages and practical application value: 1) This model employs reflective memory technology as the core support for data transmission. Reflective memory technology enables direct data reading and writing between nodes through a shared memory mechanism, effectively eliminating intermediate links in traditional message passing mechanisms. This technological innovation significantly improves data transmission efficiency, especially in cyber-physical fusion systems with high real-time requirements, where it can significantly reduce latency and ensure real-time updates and processing of flight parameters. Specifically, the aircraft structural strength cyber-physical fusion system of this invention uses a high-performance reflective memory switch, which can collect and transmit aircraft flight parameters (including altitude H, Mach number M, acceleration g, angle of attack, engine low-pressure speed ENG_N1, engine high-pressure speed ENG_N2, and other key flight information parameters) in real time. The algorithms of the three core subsystems—the ground flutter principle test demonstration subsystem, the airframe structure virtual test demonstration subsystem, and the airborne equipment integrated vibration test platform demonstration subsystem—are embedded into the reflective memory card. This gives the cyber-physical fusion system ultra-low latency characteristics, and the processing and transmission of aircraft structural strength input and output data are directly and synchronously completed by hardware, providing reliable data support for flight safety. Compared to the traditional method of writing and reading data from a hard drive and then transmitting it over a network, this method reduces data transmission latency by several orders of magnitude, achieving microsecond-level data transmission latency. This low-latency characteristic is particularly important for monitoring the structural strength of aircraft, because under complex flight conditions, any delay can lead to flight safety hazards. Through this invention, the aircraft structural strength cyber-physical fusion system can quickly respond to changes in structural response caused by changes in the aircraft's flight status based on real-time collected flight parameters, thereby monitoring aircraft flight safety.

[0013] 2) Multi-parameter and high-bandwidth support capability. The aircraft structural strength cyber-physical fusion system can simultaneously support the concurrent transmission of multiple data streams, meeting the needs of parallel processing of a large number of parameters under complex flight conditions. This multi-parameter and high-bandwidth characteristic enables the aircraft structural strength cyber-physical fusion system to maintain stable operation under high load conditions, providing strong support for real-time monitoring of aircraft structural strength.

[0014] 3) This invention promotes new developments in aircraft structural strength safety. By constructing an efficient and reliable cyber-physical fusion system for aircraft structural strength flight safety monitoring, real-time online monitoring of aircraft structural strength is achieved, enabling timely detection of potential risks. This real-time monitoring capability not only improves flight safety but also significantly reduces testing costs. Traditional aircraft development requires extensive ground and flight testing, while this invention, through real-time monitoring and data analysis, reduces the number and scale of traditional ground tests. This cost saving directly translates into savings in R&D resources and a shorter development cycle, bringing significant economic benefits to the design of aircraft throughout its entire lifecycle.

[0015] 4) Furthermore, this invention has broad application prospects. Through reflective memory technology and a multi-level collaborative subsystem architecture, this model is not only suitable for aircraft structural strength monitoring, but can also be extended to other fields requiring high real-time performance and high reliability. This technological innovation provides new ideas and directions for the development of cyber-physical systems.

[0016] This invention proposes an innovative cyber-physical fusion hierarchical model for aircraft structural strength based on reflective memory transmission. Through its advantages such as ultra-low latency and high bandwidth support, it has significant application value in aircraft flight safety monitoring, reducing strength testing costs, and improving R&D efficiency. This innovation not only promotes new developments in aircraft structural strength safety but also provides strong support for the technological advancement of cyber-physical fusion systems.

[0017] Furthermore, this invention proposes a hierarchical cyber-physical fusion model, system, and method for aircraft structural strength. By innovatively integrating reflective memory technology, multi-level subsystem collaborative technology, and surrogate model algorithms, a hierarchical and functionally complementary cyber-physical fusion system is constructed. This system performs real-time fusion processing of the flutter response, static strength response, and dynamic strength response of aircraft structures—key aspects of aircraft structural design and test monitoring—and displays the results in real time through a user interface. This provides strong support for real-time monitoring and analysis of aircraft structural strength during flight, significantly improving the real-time performance, accuracy, and safety of aircraft structural strength analysis. Specifically, this is reflected in the following aspects: 1) Breakthrough in real-time data response.

[0018] This invention proposes a hierarchical information-physical fusion model for aircraft structural strength that transmits data via reflective memory, achieving hardware-level data synchronization between the reflective memory card and the switch, thereby compressing data latency to 1~10. μs Traditional methods of writing and reading files on a computer hard drive involve reading and writing to the hard drive and then transmitting the data via network protocols, resulting in data latency as high as 10 to 100 milliseconds. ms Reflective memory technology, as the support for data transmission in this system, breaks through the bottleneck of traditional cyber-physical systems relying on hard disk file transmission, increasing the data transmission speed from millisecond-level response to microsecond-level response, and improving the data response speed by more than 10,000 times.

[0019] This breakthrough in real-time data response brings about improvements in real-time response safety control and multi-system collaborative efficiency in key scenarios of the aircraft structural strength cyber-physical fusion hierarchical model. During aircraft flight, when encountering turbulence or maneuvering overload, the aircraft structural strength cyber-physical fusion hierarchical model, system, and method proposed in this invention can achieve real-time response safety control and multi-system collaborative efficiency in critical scenarios. μsThe system completes flutter margin calculation and early warning push within the system. During aircraft test flights, it can also successfully monitor and warn of high overload and abnormal vibration of the aircraft structure, which can buy valuable time for pilots to adjust the aircraft attitude and properly mitigate abnormal load conditions. At the same time, the aircraft structural strength information physical fusion hierarchical model of this invention realizes the coordination of subsystems such as the ground flutter principle test demonstration subsystem, the airframe structure virtual test demonstration subsystem, and the airborne equipment integrated vibration test platform demonstration subsystem through reflective memory. It performs real-time fusion processing of the aircraft structural flutter response, static strength response, and dynamic strength response, which are of most concern to designers, in the three subsystems. The analysis results of the ground flutter subsystem, the airframe static strength subsystem, and the airborne vibration platform are synchronized across nodes in real time through the aircraft structural strength response output module, ensuring that the user interface displays the structural status in real time.

[0020] 2) Enhanced ability to handle heterogeneous multi-parameter data.

[0021] Traditional cyber-physical fusion systems (CPTFS) often encounter bandwidth shortages and latency accumulation issues when handling concurrent transmission of heterogeneous multi-parameter data from aircraft, such as transmitting flight parameters (including altitude H, Mach number M, acceleration g, angle of attack, engine low-pressure speed ENG_N1, and engine high-pressure speed ENG_N) while simultaneously processing flutter margin calculations, acceleration response calculations, displacement and strain value calculations. This invention proposes a hierarchical CPTFS model, system, and method for aircraft structural strength that supports high bandwidth and multi-parameter data coverage under complex flight load conditions, achieving parallel transmission of multi-level subsystems and stable data throughput. This invention can simultaneously process various sensor data (such as altitude H, Mach number M, acceleration g, angle of attack, engine low-pressure speed ENG_N1, and engine high-pressure speed ENG_N) and calculate various types of structural responses (such as acceleration, strain, and deformation response), without packet loss or sudden latency increases during concurrent data updates.

[0022] 3) Reduced physical testing and increased flight safety.

[0023] This invention proposes a cyber-physical fusion hierarchical model, system, and method for aircraft structural strength. By employing cyber-physical fusion-driven virtual testing, it achieves cost reduction and efficiency improvement. Traditional aircraft development relies heavily on extensive ground-based physical tests and flight verification. This invention, however, significantly reduces development costs by fusing virtual testing with real-time aircraft physical data. For example, this system can simulate extreme load conditions. During actual flight testing, the aircraft flies at 100% design load, while the virtual flight model can continue verification in a virtual environment with 150% design load, avoiding the high risks and costs of physical testing.

[0024] This invention proposes a hierarchical model, system, and method for aircraft structural strength based on cyber-physical systems, enabling real-time monitoring and early warning of multiple subsystems across multiple dimensions of the aircraft. By integrating flutter, static strength, and dynamic strength analysis, the system constructs a digital twin of the aircraft structure, significantly improving flight safety. For example, in terms of flutter warning capability, the system can predict critical flutter states 2-3 seconds in advance, with a warning accuracy of 99.8%. During aircraft flutter test flights, when the angle of attack exceeds the limit and the flight Mach number is about to exceed the limit, the system successfully identifies a reduction in flutter margin. When the reduction in flutter margin reaches a safe threshold, an alarm is triggered, allowing the pilot to make a successful judgment and ensure flight control safety by slowing down and increasing altitude. Regarding structural load-bearing capacity, structural crack damage can be identified. The dynamic strength analysis module detects microcracks in the structure through changes in the vibration load spectrum, initiating early warnings and avoiding potential catastrophic structural failures. This invention utilizes an efficient human-computer interaction method, providing a user interface that displays 3D models in a highlighted manner (e.g., dangerous area display), trend curves (e.g., flutter margin changes with altitude), and numerical lists (e.g., safety factors for various parts), allowing for simple and intuitive display of early warning information about the aircraft structure on a screen or real-time push to the ground control center. Attached Figure Description

[0025] Figure 1 illustrates a traditional data transmission method for a cyber-physical fusion system. Figure 2 This is a data transfer method based on reflection memory; Figure 3 This is a system flowchart of the present invention; Figure 4 This is the system flowchart described in Example 3; Figure 5 This is the output result of the proxy model for the whole-machine flutter analysis in Example 3; Figure 6 The output results of the surrogate model for static strength analysis in Example 3; Figure 7 The output results are from the vibration analysis proxy model in Example 3. Detailed Implementation

[0026] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0027] Example 1. A physical fusion hierarchical model for aircraft structural strength information based on reflective memory transmission, the physical structure as follows: Figure 3As shown, this model achieves efficient data read and write operations through reflective memory, and transmits aircraft flight parameters (including altitude) in real time through a reflective memory switch. H ,Mach number M acceleration g The system monitors the real-time response of key flight parameters (such as angle of attack, engine low-pressure speed ENG_N1, and engine high-pressure speed ENG_N2) and structural strength. The aircraft structural strength information-physical fusion hierarchical model integrates a structural strength hierarchical model, comprising three core subsystems: a virtual test demonstration subsystem for airframe structure, a ground flutter principle test demonstration subsystem, and an integrated vibration test platform demonstration subsystem for airborne equipment. During the operation of the aircraft structural strength cyber-physical fusion system, the ground flutter principle test demonstration subsystem first performs flutter and load analysis on the input flight parameters, then transmits the flutter response of the aircraft structure to the network via reflective memory, and simultaneously transmits the load analysis results to the airframe structure virtual test demonstration subsystem and the vibration information of the aircraft structure to the airborne equipment integrated vibration test platform demonstration subsystem. The airframe structure virtual test demonstration subsystem performs static strength analysis on the received load analysis data and transmits the static strength analysis results to the aircraft structured strength response output module via reflective memory. The airborne equipment integrated vibration test platform demonstration subsystem performs envelope statistics on the vibration information, obtains the vibration load spectrum, performs dynamic strength response analysis on the structure, and transmits the dynamic response results to the aircraft structured strength response output module via reflective memory. The aircraft structured strength response output module in the aircraft structural strength cyber-physical fusion system, constructed by this hierarchical model, receives the aircraft structural flutter response, static strength response, and dynamic strength response from the three subsystems in the network, realizes real-time fusion processing of information, and displays the aircraft structural strength response status in real time through the user interface. This invention presents a physical fusion hierarchical model for aircraft structural strength information transmitted via reflective memory, which effectively enables real-time monitoring and analysis of aircraft structural strength, providing strong protection for flight safety. In this embodiment, reflective memory is a technology that enables high-speed data sharing and real-time communication through a reflective memory card. It creates a shared memory area that allows multiple nodes connected to the network to access. When a node writes data to its local reflective memory, the data is rapidly broadcast to other nodes in the network via high-speed fiber optic communication, ensuring that data changes propagate to all nodes with extremely low latency. By embedding the algorithm into the reflective memory card, data processing and transmission are directly and synchronously completed by hardware, reducing the latency introduced by software processing, thereby achieving microsecond-level data transmission latency. Figure 2 As shown, this technique can meet the stringent requirements of real-time systems for high efficiency and low latency.

[0028] The reflective memory technology employed in this invention is a highly efficient data transmission technology with several significant advantages. It boasts fast data transmission speeds and extremely low inter-node latency, typically ranging from hundreds of nanoseconds to microseconds, meeting the stringent requirements of real-time systems for rapid response. Furthermore, the data transmission time of reflective memory is deterministic, further enhancing real-time performance. Reflective memory is simple to use, widely compatible, and can be plugged into various bus motherboards, supporting data exchange between different platforms. It provides a large memory capacity, meeting the needs of large-scale real-time data sharing. This technology, which enables efficient data transmission between interconnected computers via a local area network, offers powerful real-time performance.

[0029] Example 2. A hierarchical model for aircraft structural strength cyber-physical fusion, and the aircraft structural strength cyber-physical fusion system constructed from it, see... Figure 3 ,include: The ground flutter principle demonstration subsystem performs flutter and load analysis on the aircraft structure based on flight parameters to obtain the flutter response and load analysis results of the aircraft structure; the flutter response includes vibration information and flutter margin. The airframe structure virtual test demonstration subsystem performs static strength analysis on the structure based on the load analysis results from the ground flutter principle test demonstration subsystem transmitted via reflected memory, and obtains the static strength analysis results of the aircraft structure. The airborne equipment integrated vibration test platform demonstration subsystem performs envelope statistics on the vibration information transmitted from the ground flutter principle test demonstration subsystem via the reflection memory to obtain the vibration load spectrum. The vibration load spectrum is then used to perform dynamic strength response analysis of the structure to obtain the dynamic response results of the aircraft structure. The aircraft structural strength response output module receives flutter margin, static strength analysis results and dynamic response results transmitted from the reflection memory, performs real-time fusion processing, and displays the aircraft structural strength response in real time.

[0030] The information fusion method of the above system includes the following steps: The first step is to establish a network of aircraft structural strength cyber-physical systems (CPSS) with reflective memory cards. High-performance reflective memory cards are installed and configured on a dedicated CPSS computer. Through a high-bandwidth, low-latency reflective memory switch, the CPSS is connected to the main aircraft information transmission network in real time, establishing a highly reliable data transmission channel. The core objective of this step is to achieve bidirectional interaction between the CPSS and the real-time flight parameters of the aircraft, ensuring efficient signal input and output, and laying the foundation for subsequent data processing. The second step involves the reflective memory switch transmitting a large amount of collected aircraft flight parameters in real time. The aircraft structural strength information-physical fusion system extracts key flight parameters from these parameters, primarily including altitude.H ,Mach number M acceleration g The system processes key flight parameters such as angle of attack, engine low-pressure speed ENG_N1, and engine high-pressure speed ENG_N2, and stores them in designated locations according to preset formats. This process enables efficient acquisition and management of key flight parameters, providing reliable input for subsequent analysis. The third step involves the aircraft structural strength cyber-physical fusion system, which consists of three hierarchical models: a ground-based flutter principle test demonstration subsystem, an airframe structure virtual test demonstration subsystem, and an airborne equipment integrated vibration test platform demonstration subsystem. These three hierarchical models together form a complete hierarchical system for aircraft structural strength. The ground-based flutter principle test demonstration subsystem, upon receiving selected key aircraft flight parameters, performs flutter analysis and load analysis of the aircraft structure. The fourth step involves the ground flutter principle demonstration subsystem transmitting the flutter response of the aircraft structure to the aircraft structural strength response output module in real time via an efficient reflective memory data transmission mechanism. Specifically, after completing the flutter analysis of the aircraft structure, the ground flutter principle demonstration subsystem transmits the relevant flutter response data. Within this subsystem, the flutter analysis results at different flight states are first calculated. Based on the flutter margin at different states within the flight envelope, a flutter proxy model of the aircraft structure is generated. Upon receiving flight parameters, this proxy model performs efficient calculations via reflective memory and transmits the analyzed flutter margin to the aircraft structural strength response output module. The flutter margin directly reflects the flutter performance of the aircraft structure under different flight conditions, providing crucial information for the aircraft's flutter safety assessment. The fifth step involves the ground flutter principle test demonstration subsystem performing real-time load analysis to obtain aerodynamic load distribution data (load analysis results) of the aircraft structure under various flight conditions, and then transmitting this aerodynamic load distribution data to the airframe structure virtual test demonstration subsystem. Simultaneously, the ground flutter principle test demonstration subsystem also transmits the vibration information of the aircraft structure under various flight conditions (including amplitude, frequency, and acceleration) to the airborne equipment integrated vibration test platform demonstration subsystem. This data interoperability and collaboration between the hierarchical subsystems ensures the consistency of input data across the three hierarchical models—the ground flutter principle test demonstration subsystem, the airframe structure virtual test demonstration subsystem, and the airborne equipment integrated vibration test platform demonstration subsystem—providing a reliable input basis for the static strength design and vibration design of the aircraft structure. Step 6: After receiving the load analysis results transmitted by the ground flutter principle test demonstration subsystem, the airframe structure virtual test demonstration subsystem initiates the static strength analysis of the airframe structure. This analysis first conducts a comprehensive analysis of the static performance of the airframe structure based on the finite element method, generating a static strength proxy model of the aircraft airframe structure. After receiving the load analysis results transmitted by the ground flutter principle test demonstration subsystem, the airframe structure virtual test demonstration subsystem calls the pre-set strength proxy model and uses numerical simulation to calculate the strain distribution, displacement, and other conditions of the airframe structure under different load conditions in real time. At the same time, the airframe structure virtual test demonstration subsystem can also simulate a variety of extreme working conditions, helping engineers to discover potential structural problems in a virtual environment, significantly reducing the need for physical testing, thereby improving design efficiency and reliability. The seventh step involves the airframe structure virtual test demonstration subsystem transmitting the static strength analysis results of the aircraft structure to the aircraft structure strength response output module via reflective memory. The analysis results will be presented in a graphical interface, including strain cloud diagrams, displacement cloud diagrams, etc., so that engineers can intuitively understand the load-bearing capacity of the structure. At the same time, the airframe structure virtual test demonstration subsystem will list the safety factor and strength margin of each part in detail, providing real-time static strength monitoring for the flight of the aircraft structure platform. The eighth step involves the airborne equipment integrated vibration test platform demonstration subsystem performing simulation analysis based on the vibration environment spectrum in advance. Based on the simulation results, a proxy model of the aircraft body structure vibration response is generated. After receiving the vibration information (amplitude, frequency, acceleration) transmitted by the ground flutter principle test demonstration subsystem, the airborne equipment integrated vibration test platform performs envelope statistical analysis on these data to extract key features from the vibration information, such as maximum value, average value, and spectral distribution, thereby generating a vibration input load spectrum. The aircraft body structure vibration response proxy model quickly performs dynamic strength response analysis of the structure based on the vibration load spectrum to evaluate the stress and acceleration response of the equipment under these vibration loads, ensuring the stable operation of the structure in complex vibration environments. The ninth step involves the demonstration subsystem of the airborne equipment integrated vibration test platform transmitting the dynamic response results of the aircraft structure to the aircraft structure strength response output module via the reflection memory. The analysis results will be presented in a graphical interface, including the root mean square value of stress and the root mean square value of acceleration, so that engineers can intuitively understand the load-bearing capacity of the structure under vibration environment and provide real-time vibration monitoring for the flight of the aircraft structure platform. In the tenth step, the aircraft structural strength response output module of the aircraft structural strength cyber-physical fusion system receives the flutter response, static strength response, and dynamic strength response of the aircraft structure from the three subsystems in the network. It then performs real-time fusion processing of the information and displays the aircraft structural strength response status in real time through the user interface. In this step, the aircraft structural strength response output module integrates multi-dimensional data such as flutter response, static strength response, and dynamic strength response to comprehensively reflect the strength performance of the aircraft structure under complex load conditions. Through a user-friendly interface, it intuitively presents the strength response of the aircraft structure in the form of graphs, 3D models, and numerical values, including key indicators such as flutter margin, strain distribution, displacement, and root mean square amplitude of vibration stress. These real-time output results support engineers in ensuring the safety and reliability of the aircraft structure under various extreme conditions.

[0031] Example 3. A reflective memory-transmitted aircraft structural strength information-physical fusion system, see... Figure 4 As shown. A physical fusion hierarchical model for aircraft structural strength information transmitted via reflective memory mainly includes a full-aircraft flutter analysis model (ground flutter principle test demonstration subsystem), a static strength analysis model (airframe structure virtual test demonstration subsystem), and a vibration analysis model (airborne equipment integrated vibration test platform demonstration subsystem). Finally, the aircraft structural strength response is displayed in real time through an aircraft structural strength response output module to implement the technology of this invention. A detailed description follows: 1) Establish an aircraft structural strength information-physical fusion system network with reflective memory cards.

[0032] 1.1) To achieve efficient data processing and real-time interaction in the aircraft structural strength cyber-physical fusion system, this system first installs and configures a high-performance reflective memory card on a dedicated computer. This step includes two parts: hardware installation and software installation. Hardware installation involves inserting the reflective memory card into the computer's PCI slot and then connecting it via fiber optic cable. When connecting the fiber optic cable, ensure that the output line is connected to the input line and vice versa. Software installation involves installing the driver for the reflective memory card, which can be done through the official driver website.

[0033] 1.2) After the reflective memory card is deployed, the next step is to use it. The reflective memory card implements data read and write operations through a specific workflow, including three steps: write operation, data propagation, and read operation. Write operation: When a node needs to send data, it writes the data to its local reflective memory area. After the hardware detects the write operation, it immediately initiates data broadcasting, sending the data to other nodes in the network via a high-speed communication link; Data propagation: Modified data is sent to other nodes in the network via a high-speed communication link. The hardware of the receiving node updates its local reflective memory with the received data; Read operation: Other nodes can read the latest data from their local reflective memory at any time, as if the data were stored directly locally. This mechanism allows each computer to have a real-time local backup of the shared memory set.

[0034] 2) The reflective memory switch transmits the collected aircraft flight parameters in real time.

[0035] The aircraft structural strength cyber-physical fusion system extracts key flight parameters from the reflection memory, mainly including: altitude. H ,Mach number M acceleration g The angle of attack, engine low-pressure speed ENG_N1, engine high-pressure speed ENG_N2, and other real-time key flight parameters are processed by the system and stored in designated locations according to preset format specifications, as shown in Table 1.

[0036] Table 1 Flight Parameter Preset Format

[0037] 3) The present invention divides the aircraft structural strength cyber-physical fusion system into three hierarchical models, specifically including: ground flutter principle test demonstration subsystem, airframe structure virtual test demonstration subsystem, and airborne equipment integrated vibration test platform demonstration subsystem. These three hierarchical models together constitute a complete aircraft structural strength hierarchical system.

[0038] 4) The function of the ground flutter principle test demonstration subsystem is to establish a dynamic finite element model of the entire aircraft object, simulate accurate dynamic characteristics, and perform flutter analysis and load analysis of the aircraft structure after receiving the key flight parameters of the aircraft selected in Table 1.

[0039] 4.1) The ground flutter principle test demonstration subsystem transmits the flutter response of the aircraft structure to the aircraft structural strength response output module in real time through an efficient reflective memory data transmission mechanism. Specifically, after the ground flutter principle test demonstration subsystem completes the flutter analysis of the aircraft structure, it will output relevant flutter response data, mainly including key output results such as amplitude, frequency, acceleration, and flutter margin. The ground flutter principle test demonstration subsystem first calculates the flutter analysis results of the aircraft at different flight state points, as shown in Table 2.

[0040] Table 2 Output data format of the ground flutter principle demonstration subsystem

[0041] 4.2) Based on the flutter results at different state points under the flight envelope in Table 2, a flutter proxy model for the aircraft structure is generated. After receiving flight parameters, this proxy model performs efficient calculations via reflected memory and transmits the flutter analysis results to the aircraft structural strength response output module. The flutter analysis results directly reflect the flutter performance of the aircraft structure under different flight conditions. (See...) Figure 5 As shown, this provides an important basis for assessing the flutter safety of aircraft.

[0042] 4.3) The ground flutter principle test demonstration subsystem analyzes the aerodynamic load distribution of the aircraft structure under various flight conditions in real time and transmits this aerodynamic load data to the virtual test demonstration subsystem of the aircraft structure. Simultaneously, the ground flutter principle test demonstration subsystem also analyzes the vibration information of the aircraft structure under various flight conditions in real time, including acceleration time-domain acquisition data, and transmits the vibration information data to the airborne equipment integrated vibration test platform demonstration subsystem.

[0043] 5) After receiving the aerodynamic load analysis data (4.3) transmitted by the ground flutter principle test demonstration subsystem, the airframe structure virtual test demonstration subsystem starts the airframe structure static strength analysis module to perform static strength analysis and real-time display of the aircraft structure.

[0044] 5.1) The virtual test demonstration subsystem for the body structure first conducts a comprehensive analysis of the static performance of the body structure based on the finite element method. It then uses numerical simulation to calculate the deformation and strain distribution of the body structure under different load conditions in real time, as shown in Table 3. At the same time, the virtual test demonstration subsystem for the body structure can also simulate a variety of extreme working conditions, helping engineers to discover potential structural problems in a virtual environment, significantly reducing the need for physical testing, thereby improving design efficiency and reliability.

[0045] Table 3 Output data format of the virtual experiment demonstration subsystem for body structure

[0046] 5.2) Based on the static strength results at different state points under the flight envelope in Table 3, a static strength proxy model for the aircraft airframe structure is generated. After receiving flight parameters, this proxy model performs efficient calculations via reflected memory and transmits the static strength analysis results to the aircraft structured strength response output module. The static strength analysis results directly reflect the static performance of the aircraft structure under different flight conditions. (See...) Figure 6 As shown, the airframe structure virtual test demonstration subsystem transmits the static strength analysis results of the aircraft structure to the aircraft structure strength response output module through the reflection memory. The analysis results will be presented in a graphical interface, including displacement values, strain values, etc., so that engineers can intuitively understand the load-bearing capacity of the structure. At the same time, the airframe structure virtual test demonstration subsystem will list the safety factor and strength margin of each part in detail, providing real-time static strength monitoring for the flight of the aircraft structure platform.

[0047] 6) After receiving the vibration information data (4.3) transmitted by the ground flutter principle test demonstration subsystem, the airborne equipment integrated vibration test platform starts the airframe structure vibration analysis module to perform aircraft structure vibration analysis and real-time display.

[0048] 6.1) After receiving the vibration information (4.3) transmitted by the ground flutter principle test demonstration subsystem, the airborne equipment integrated vibration test platform will perform envelope statistical analysis on these data to extract key features in the vibration information, such as maximum value, average value and spectral distribution, thereby generating a vibration input load spectrum. The airborne equipment integrated vibration test platform will perform simulation analysis based on the vibration input load spectrum to obtain the stress and acceleration response of the aircraft structure under these vibration loads, as shown in Table 4, to ensure the stable operation of the structure in a complex vibration environment.

[0049] Table 4 Output Data Format of Demonstration Subsystem of Airborne Equipment Integrated Vibration Test Platform

[0050] 6.2) Based on the vibration analysis results at different state points under the flight envelope in Table 4, a proxy model for the vibration response of the aircraft airframe structure is generated. After receiving the flight parameters, this proxy model performs efficient calculations through reflected memory and transmits the vibration analysis structure to the aircraft structural strength response output module. See [link to module]. Figure 7 As shown, the vibration analysis results intuitively reflect the load-bearing capacity of the structure under vibration environment, providing real-time vibration monitoring for the flight of aircraft structural platforms.

[0051] 7) The aircraft structural strength response output module of the aircraft structural strength information physical fusion system receives the flutter response, static strength response, and dynamic strength response of the aircraft structure from the three subsystems in the network. It then performs real-time fusion processing of the information and displays the aircraft structural strength response status in real time through the user interface. In this step, the aircraft structural strength response output module integrates multi-dimensional data such as flutter response, static strength response, and dynamic strength response, as shown in Table 5. This comprehensively reflects the strength performance of the aircraft structure under complex load conditions and intuitively presents the strength response status of the aircraft structure, including key indicators such as flutter margin, strain distribution, displacement, and root mean square amplitude of vibration stress. These real-time output results support engineers in ensuring the safety and reliability of the aircraft structure under various extreme conditions.

[0052] Table 5 shows the real-time display of three levels of model data from the aircraft structural strength response output module.

[0053] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A hierarchical model for the physical fusion of aircraft structural strength information based on reflected memory transmission, characterized in that, include: The ground flutter principle test demonstration subsystem performs flutter analysis and load analysis of the aircraft structure based on flight parameters to obtain the flutter response and load analysis results of the aircraft structure. Flutter response includes vibration information and flutter margin; The airframe structure virtual test demonstration subsystem performs static strength analysis on the structure based on the load analysis results from the ground flutter principle test demonstration subsystem transmitted via reflected memory, and obtains the static strength analysis results of the aircraft structure. The airborne equipment integrated vibration test platform demonstration subsystem performs envelope statistics on the vibration information transmitted from the ground flutter principle test demonstration subsystem via the reflection memory to obtain the vibration load spectrum. The vibration load spectrum is then used to perform dynamic strength response analysis of the structure to obtain the dynamic response results of the aircraft structure.

2. The aircraft structural strength information-physical fusion hierarchical model according to claim 1, characterized in that, Flight parameters are transmitted to the ground flutter principle test demonstration subsystem via reflective memory.

3. The aircraft structural strength information-physical fusion hierarchical model according to claim 1, characterized in that, Flight parameters include: altitude H, Mach number M, acceleration g, angle of attack, engine low-pressure speed ENG_N1, and engine high-pressure speed ENG_N2.

4. The aircraft structural strength information-physical fusion hierarchical model according to claim 1, characterized in that, Vibration information includes amplitude, frequency, and acceleration.

5. An aircraft structural strength cyber-physical fusion system constructed based on the aircraft structural strength cyber-physical fusion hierarchical model according to any one of claims 1-4, characterized in that, include: The aircraft structural strength response output module receives flutter margin, static strength analysis results and dynamic response results transmitted from the reflection memory, performs real-time fusion processing, and displays the aircraft structural strength response in real time.

6. An information fusion method based on the aircraft structural strength cyber-physical fusion system of claim 5, characterized in that, Includes the following steps: The first step is to build a physical network for an aircraft structural strength information physical fusion system with reflective memory cards; The second step is to preprocess the flight parameters transmitted in real time in the physical network's reflective memory switch and store them in the physical network's reflective memory. The third step is that after the ground flutter principle test demonstration subsystem receives the flight parameters, it performs flutter analysis and load analysis on the aircraft structure to obtain the flutter response and load analysis results. The fourth step involves the ground flutter principle test demonstration subsystem performing real-time load analysis to obtain the load analysis results of the aircraft structure under various flight conditions, and transmitting them to the airframe structure virtual test demonstration subsystem. Simultaneously, the ground flutter principle test demonstration subsystem also transmits the vibration information of the aircraft structure under various flight conditions to the airborne equipment integrated vibration test platform demonstration subsystem. Fifth, after receiving the load analysis results, the virtual test demonstration subsystem for the airframe structure initiates the static strength analysis of the airframe structure, obtains the static strength analysis results, and lists the safety factor and strength margin of each part of the aircraft. The sixth step involves the demonstration subsystem of the airborne equipment integrated vibration test platform performing dynamic intensity response analysis based on vibration information to obtain dynamic response results. The seventh step involves the aircraft structural strength response output module receiving the aircraft structural flutter margin, static strength analysis results, and dynamic response results from the three subsystems, respectively. It then performs real-time information fusion processing and displays the aircraft structural strength response status in real time through the user interface.

7. The information fusion method of the aircraft structural strength cyber-physical fusion system according to claim 6, characterized in that, In step five, the static strength analysis is as follows: First, a comprehensive analysis of the static mechanical properties of the airframe structure is performed based on the finite element method to generate a static strength proxy model of the aircraft airframe structure; after receiving the load analysis results, the airframe structure virtual test demonstration subsystem calls the static strength proxy model and uses numerical simulation to calculate the strain distribution and displacement of the airframe structure under different load conditions in real time.

8. The information fusion method of the aircraft structural strength cyber-physical fusion system according to claim 7, characterized in that, In step five, the virtual test demonstration subsystem for the body structure can also simulate various extreme working conditions to discover potential structural problems through the virtual environment.

9. The information fusion method of the aircraft structural strength cyber-physical fusion system according to claim 6, characterized in that, In step six, the dynamic intensity response analysis is as follows: The airborne equipment integrated vibration test platform demonstration subsystem performs simulation analysis based on the vibration environment spectrum in advance, and generates a proxy model of the aircraft body structure vibration response based on the simulation results. After receiving the vibration information transmitted by the ground flutter principle test demonstration subsystem, it performs envelope statistical analysis based on the vibration information, extracts key features in the vibration information, and generates a vibration load spectrum. The aircraft body structure vibration response proxy model performs dynamic strength response analysis of the structure based on the vibration load spectrum.

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