Aero-engine health management integrated platform based on multi-core processor

Abstract

The application discloses an aero-engine health management integrated platform based on a multi-core processor, adopts a multi-core processor to build multiple virtual machines, and integrates an oil metal chip monitoring device, a blade tip clearance measuring device and an engine monitoring device into the aero-engine health management integrated platform based on the multi-core processor, and comprises a hardware layer, a core operating system layer, a partition operating system layer and an application layer. The hardware layer comprises real peripherals and virtual hardware drivers of the peripherals for integrating hardware devices of the devices and a multi-core SOC for providing computing resources, the core operating system layer is used for managing and distributing computing resources and hardware signal resources provided by the hardware layer, the partition operating system layer is used for operating and managing virtual partitions according to security level requirements of each application in the application layer, and the application layer is used for integrating function modules of the oil metal chip monitoring device, the blade tip clearance measuring device and the engine monitoring device based on multiple virtual partitions provided by the partition operating system layer.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine health management, and more specifically to an integrated platform for aircraft engine health management based on a multi-core processor. Background Technology

[0002] The primary function of a commercial aircraft engine health management system is to collect and store operating parameters related to the engine's airflow, fuel / lubricating oil, vibration, control, and overall health management system. This provides data for fault diagnosis and troubleshooting, and verifies and progressively improves functions such as fault detection, fault isolation, fault diagnosis, lifespan management, condition-based maintenance, and data storage. An engine health management system typically includes monitoring sensors, an engine monitoring unit (EMU), a lubricating oil metal scrap monitoring device (DMB), a blade tip clearance measuring device (CBT), and cables connecting these sensors.

[0003] Among them, the EMU (Engine Monitoring Unit) is a key component of the aircraft engine health management system. It can collect and store signals from engine sensors, and process and analyze data sent by the engine electronic controller (EEC) to calculate the engine's real-time vibration level, monitor engine operating status, predict potential faults, generate fault diagnosis reports and maintenance recommendations, and transmit engine health information to the aircraft (AC), EEC or other ground equipment.

[0004] DMB (Device Module for Metal Scrap in Lubricating Oil) is used to detect metal particles in aircraft engine lubricating oil in real time, distinguishing between ferromagnetic and non-ferromagnetic particles and determining their size. The presence of metal particles in lubricating oil is closely related to the state of wear. By statistically analyzing the types, sizes, and generation rates of metal particles in the lubricating oil of bearings and gears, the degree of mechanical wear can be determined, thereby preventing accidents caused by severe wear.

[0005] CBT (blade tip clearance measuring device) is used to measure the clearance between the blade tip and the casing and monitor the change of blade tip clearance in real time. Its main functions are: (1) to provide data basis for engine design optimization; (2) to monitor the rotor shaft center trajectory and blade disk imbalance by using multiple sensors distributed at different positions; (3) to provide early warning to prevent major accidents caused by friction damage between the blade and the casing and to ensure system safety.

[0006] Currently, commercial aircraft engine health management systems employ a separate design for the DMB, CBT, and EMU, each with its own independent processor and cabling. The use of multiple processor modules and complex onboard cabling results in a high failure rate, high power consumption, large weight, large size, and complex wiring, failing to meet the growing demands for high safety, low power consumption, integration, and weight reduction in aircraft engines. Furthermore, each processor module currently performs only a relatively single function, and some multi-core processors disable unused cores for airworthiness purposes, still using a single core for processing. Beyond fulfilling their single function, the surplus computing power, storage, and I / O resources of each processor remain unused, leading to very low hardware resource utilization and inefficient onboard computer hardware. Therefore, with the integration of increasingly new onboard software functions, the hardware and software architecture of aircraft engine health management systems must evolve towards multi-core, multi-partition architectures, urgently requiring a new architecture to meet the challenges of commercial aircraft engine airworthiness certification. Summary of the Invention

[0007] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.

[0008] The purpose of this invention is to solve the above-mentioned problems and provide an integrated platform and method for the health management of aero-engines based on a multi-core processor. This platform can automatically perform requirement quality analysis based on objective standards, thereby ensuring the consistency of requirement quality analysis results and improving analysis efficiency.

[0009] The technical solution of this invention is as follows:

[0010] This invention provides an integrated platform for aero-engine health management based on a multi-core processor. It utilizes a multi-core processor to construct multiple virtual machines, integrating a lubricating oil and metal shavings monitoring device, a blade tip clearance measurement device, and an engine monitoring device into the platform. The platform comprises: a hardware layer, a core operating system layer, a partitioned operating system layer, and an application layer.

[0011] The hardware layer includes real peripherals for integrating various device hardware devices and their virtual hardware drivers, as well as multi-core SoCs that provide computing resources. Through the hardware layer, corresponding computing resources and hardware signal resources are provided to the next layer, the core operating system layer.

[0012] The core operating system layer is used to manage and allocate the computing resources and hardware signal resources provided by the hardware layer, thereby constructing multiple virtual partitions;

[0013] The partitioning operating system layer manages and operates each virtual partition according to the security level requirements of each application in the application layer, thereby deploying applications with different security levels to different virtual partitions;

[0014] The application layer is used to integrate the functional modules of the lubricating oil metal shavings monitoring device, blade tip clearance measurement device, and engine monitoring device based on multiple virtual partitions provided by the partitioned operating system layer, so as to achieve unified health monitoring and management on the same platform.

[0015] According to an embodiment of the multi-core processor-based aero-engine health management integration platform of the present invention, the multi-core processor-based aero-engine health management integration platform adopts a heterogeneous multi-core SOC as a multi-core processor deployed on the hardware layer, and provides multiple flexibly allocated computing cores for the aero-engine health management integration platform through the heterogeneous multi-core SOC.

[0016] According to an embodiment of the multi-core processor-based integrated platform for aero-engine health management of the present invention, the multi-core processor-based integrated platform for aero-engine health management deploys a sensor signal acquisition system at the hardware layer. The deployed sensor signal acquisition system collects hardware signal resources of various hardware devices, thereby monitoring the hardware devices of the lubricating oil metal shavings monitoring device, the blade tip clearance measuring device, and the engine monitoring device.

[0017] According to an embodiment of the multi-core processor-based integrated platform for aero-engine health management of the present invention, the sensor signal acquisition system includes multiple conditioning units, which are connected to the sensors of each hardware device to acquire the sensor signals of the corresponding sensors. The conditioning unit includes a signal conditioning circuit and an A / D analog signal acquisition circuit, which acquire and process the sensor signals of each hardware device to obtain the corresponding hardware signal resources.

[0018] According to an embodiment of the aero-engine health management integration platform based on a multi-core processor of the present invention, the virtual hardware driver of the hardware layer is further provided with a signal processing algorithm link library, which processes the sensor signals of each hardware device by calling the pre-stored signal processing algorithms in the signal processing algorithm link library.

[0019] According to an embodiment of the multi-core processor-based aero-engine health management integration platform of the present invention, after the multi-core processor-based aero-engine health management integration platform connects to the sensors of each hardware device through a sensor signal acquisition system, it abstracts each sensor into a virtual hardware driver in the form of a device tree through the core operating system layer, and then allocates the virtual hardware driver to different virtual partitions through the core operating system layer.

[0020] According to an embodiment of the multi-core processor-based aero-engine health management integration platform of the present invention, the multi-core processor-based aero-engine health management integration platform deploys a virtualized operating system software at the core operating system layer. The deployed virtualized operating system software constructs multiple virtual partitions, thereby binding applications of different safety levels and their corresponding computing cores in the lubricating oil metal chip monitoring device, blade tip clearance measurement device and engine monitoring device to the corresponding virtual machines through the constructed virtual partitions.

[0021] According to an embodiment of the multi-core processor-based integrated platform for aero-engine health management of the present invention, the multi-core processor-based integrated platform binds applications of different safety levels and their corresponding computing cores in the lubricating oil metal chip monitoring device, blade tip clearance measurement device and engine monitoring device to the corresponding virtual partitions. Then, it provides the required virtual hardware drivers for each virtual partition through virtualization operating system software, so that applications on different virtual partitions can obtain the corresponding hardware signal resources.

[0022] According to an embodiment of the multi-core processor-based aero-engine health management integration platform of the present invention, virtualized inter-domain communication technology is used between virtual machines to exchange information, thereby enabling data transmission between applications integrated on the same aero-engine health management integration platform.

[0023] According to an embodiment of the multi-core processor-based integrated platform for aircraft engine health management of the present invention, the partitioned operating system adopts partitioned communication technology based on the ARINC653 standard for inter-partition communication.

[0024] Compared with existing technologies, this invention offers the following advantages: For integrated management of aero-engine health, this invention employs a multi-core processor to construct multiple virtual machines. These virtual machines integrate the lubricating oil and metal shavings monitoring device, the blade tip clearance measurement device, and the engine monitoring device into a single aero-engine health management integration platform, enabling centralized health monitoring and management. This invention allows for the integration of functional modules with different safety levels from the lubricating oil and metal shavings monitoring device, the blade tip clearance measurement device, and the engine monitoring device onto a single aero-engine health management integration platform, thereby monitoring and managing the health status of these devices. Furthermore, this invention uses a high-performance multi-core processor as the processor for the integration platform, reducing redundant deployment of computing resources. When surplus computing resources are available, they can also be used for data acquisition and processing in the DMB and CBT, eliminating the need for signal processing modules and communication cables in the original DMB and CBT. This meets the growing demands for high safety, low power consumption, integration, and weight reduction in aero-engine health management. Attached Figure Description

[0025] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0026] Figure 1 This is a platform architecture diagram illustrating an embodiment of the integrated platform for aircraft engine health management based on a multi-core processor according to the present invention.

[0027] Figure 2 This is a schematic diagram illustrating the operation of an embodiment of the lubricating oil metal shavings monitoring device of the present invention.

[0028] Figure 3 This is a schematic diagram illustrating the operation of an embodiment of the blade tip clearance measuring device of the present invention. Detailed Implementation

[0029] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are merely some examples or embodiments of this application. For those skilled in the art, these drawings can be applied to other similar scenarios without creative effort. Unless obvious from the context or otherwise specified, the same reference numerals in the drawings represent the same structures or operations.

[0030] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0031] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of this application. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following drawings denote similar items; therefore, once an item is defined in one drawing, it need not be further discussed in subsequent drawings.

[0032] In detailing the embodiments of the present invention, for ease of explanation, the cross-sectional views illustrating the device structure will be partially enlarged and not to scale. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of the present invention. In actual fabrication, the three-dimensional spatial dimensions of length, width, and depth should be included.

[0033] In the description of this application, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is usually based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this application and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this application; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0034] This document discloses an embodiment of an integrated platform for aircraft engine health management based on a multi-core processor (hereinafter referred to as the aircraft engine health management integrated platform). Figure 1 This is a platform architecture diagram illustrating an embodiment of the multi-core processor-based integrated platform for aircraft engine health management according to the present invention. Figure 1As shown in this embodiment, the integrated platform for aero-engine health management is characterized by employing a multi-core processor to construct multiple virtual machines. These virtual machines integrate the lubricating oil and metal shavings monitoring device, the blade tip clearance measurement device, and the engine monitoring device into the same integrated platform. The platform comprises a hardware layer, a core operating system layer (CoreOS layer), a partition operating system layer (Partition OS layer), and an application layer. The hardware layer includes virtual hardware drivers and a multi-core processor providing computing resources for integrating the hardware devices. It provides corresponding computing and hardware signal resources to the upper-level core operating system layer. The core operating system layer manages and allocates the computing and hardware signal resources provided by the hardware layer, thereby constructing multiple virtual partitions. The partition operating system layer manages and operates each virtual partition according to the security level requirements of each application in the application layer, thus binding applications with different security levels to different virtual partitions. The application layer integrates the lubricating oil and metal shavings monitoring device, the blade tip clearance measurement device, and the engine monitoring device based on the multiple virtual partitions provided by the partition operating system layer, achieving unified health monitoring and management on the same platform.

[0035] Specifically, in this embodiment, the aero-engine health management integration platform uses a heterogeneous multi-core SOC as a multi-core processor deployed at the hardware layer, providing multiple flexibly allocable computing cores for the aero-engine health management integration platform through the heterogeneous multi-core SOC.

[0036] In one implementation, the ZYNQ UltraScale+ is used as a heterogeneous multi-core SoC. This SoC integrates a Cortex-A5 3MP Core quad-core processor, memory units, communication interface units, etc., to provide corresponding computing resources for each virtual partition.

[0037] In this embodiment, in order to integrate the EMU (Engine Monitoring Unit), DMB (Oil and Metal Shavings Monitoring Unit), and CBT (Clip Tip Clearance Measurement Unit) into the same aero-engine health management integrated platform, a sensor signal acquisition system is deployed at the hardware layer. The deployed sensor signal acquisition system collects the hardware signal resources of each hardware device, thereby monitoring the hardware devices of the oil and metal shavings monitoring unit, the blade tip clearance measurement unit, and the engine monitoring unit.

[0038] Specifically, the EMU (Engine Monitoring Unit) adopts a dual-processor (dual ZYNQ7000 processor) architecture. One processor acts as the main processor, which implements functions such as health trend prediction and maintenance decision generation with lower design safety requirements. The other processor acts as the auxiliary processor, which implements functions such as engine vibration over-limit alarm and lubricating oil level low alarm with higher design safety requirements.

[0039] The DMB (Device Module for Metal Shavings Monitoring) mainly consists of a metal shavings sensor probe, a signal processing algorithm, and a signal processing module (containing a DSP processor for data processing). The sensor probe is installed on the engine's main return oil line and connected to the signal processing module via a dedicated cable. The signal processing module demodulates and performs A / D conversion on the analog signal detected by the sensor probe, and finally transmits it via a communication cable to... Figure 1 The digital signal shown is provided to the EMU in the form of RS422.

[0040] The CBT (Blade Tip Clearance Measurement Device) mainly consists of two capacitive clearance sensors (with cables and sensor probes integrated) and a signal processing unit (containing a ZYNQ7000 processor for data algorithm processing). During measurement, the sensors are mounted on the engine casing wall. The probe core forms a capacitance with the blade tip. When the blade tip sweeps across the sensor, the capacitance increases rapidly, and when it moves away, the capacitance decreases rapidly. The signal processing unit then converts this capacitance signal into a voltage signal. Through signal conditioning, acquisition, and digital processing, the blade tip clearance value is obtained, and finally... Figure 2 The signal is provided to the EMU via a communication cable in the form of a digital signal (RS422).

[0041] Therefore, in this embodiment, to acquire the hardware signal resources of each hardware device—EMU (Engine Monitoring Unit), DMB (Lubricating Oil Metal Shavings Detector), and CBT (Clip Tip Clearance Detector)—multiple conditioning units are set up in the sensor signal acquisition system. These conditioning units are connected to the sensors of each hardware device to acquire the corresponding sensor signals. Each conditioning unit includes a signal conditioning circuit and an A / D analog signal acquisition circuit. These circuits acquire and process the sensor signals from each hardware device to obtain the corresponding hardware signal resources. Furthermore, in this embodiment, in addition to the EMU's own sensors (such as vibration and speed sensors), the signal conditioning circuits and A / D analog signal acquisition circuits of the DMB and CBT can also be directly integrated inside the EMU.

[0042] Furthermore, in this embodiment, the virtual hardware driver in the hardware layer also includes a signal processing algorithm link library, which calls the pre-stored signal processing algorithms in the signal processing algorithm link library to process the sensor signals of each hardware device.

[0043] In this embodiment, a virtualized operating system software is deployed at the core operating system layer. This software constructs multiple virtual partitions, which then bind applications of different security levels and their corresponding computing cores from the lubricating oil metal shavings monitoring device, blade tip clearance measuring device, and engine monitoring device to their respective virtual machines. Furthermore, in this embodiment, after the sensor signal acquisition system connects to the sensors of each hardware device, the virtualized operating system software at the core operating system layer abstracts each sensor into a virtual hardware driver (AD+DMA) in the form of a device tree. This virtual hardware driver is then allocated to different virtual partitions through the core operating system layer.

[0044] In one implementation, Hypervisor is used as the virtualization operating software. The Hypervisor virtualization operating software binds applications of different safety levels, including the lubricating oil metal shavings monitoring device, the blade tip clearance measuring device, and the engine monitoring device, along with their corresponding computing cores, to corresponding virtual partitions. The virtualization operating system software then provides the necessary virtual hardware drivers to each virtual partition, allowing applications on different virtual partitions to obtain the corresponding hardware signal resources. This enables the deployment of applications of different safety levels in different virtual partitions and their binding to designated computing cores. The ARINC653 standard partition scheduling technology provided by Hypervisor ensures the isolation and synchronization of applications of different safety levels in terms of runtime and space.

[0045] Specifically, in this embodiment, when the Hypervisor virtualization operating system software performs virtual partition binding, it configures the core operating system layer Hypervisor in HV_SAFETY mode. For high-security applications, it configures the VSB of the partition operating system layer in GOS_SAFETY mode, establishes an IBLLGOS virtual partition operating system, and configures its attribute to PROFILE_GOS_SAFETY. For low-security applications, it configures the VSB of the partition operating system layer in ordinary GOS mode, establishes a VIP virtual partition operating system, and configures its attribute to NO_PROFILE. For high-security applications, an IBLLAPP application is established; for low-security applications, a DKMAPP application is established. IBLL is a Certified, independently compiled, linked, and loaded method. Therefore, through the above engineering configuration method, independent development, compilation, linking, and loading of operating software, application software, and third-party algorithms (such as DMS and CBT conditioning algorithms) can be achieved, greatly improving the convenience and efficiency of system hardware and software integration.

[0046] In this embodiment, virtualized inter-module communication technology is used for information exchange between virtual machines, enabling data transmission between applications integrated on the same aero-engine health management platform. By replacing the original RS422 communication with hard-wired cables with virtualized inter-module communication technology, not only is the integrity and consistency of the data exchanged between modules guaranteed, but the complex aviation cables between modules are also eliminated, reducing the system's complexity, size, and weight. Furthermore, only ports and channels are established from high to low security level between high-security and low-security-level systems, ensuring that data can only be transmitted from high-security-level to low-security-level systems and prohibiting reverse data transmission, further guaranteeing the system's airworthiness and safety.

[0047] The prior description of this disclosure is provided to enable any person skilled in the art to make or use this disclosure. Various modifications to this disclosure will be apparent to those skilled in the art, and the general principles defined herein may be applied to other variations without departing from the spirit or scope of this disclosure. Therefore, this disclosure is not intended to be limited to the examples and designs described herein, but should be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0048] Those skilled in the art will further appreciate that the various illustrative logic blocks, modules, circuits, and algorithm steps described in conjunction with the embodiments disclosed herein can be implemented as electronic hardware, computer software, or a combination of both. To clearly illustrate this interchangeability between hardware and software, the various illustrative components, blocks, modules, circuits, and steps are described above in a generalized manner in terms of their functionality. Whether such functionality is implemented as hardware or software depends on the specific application and the design constraints imposed on the overall system. Those skilled in the art may implement the described functionality in different ways for each specific application, but such implementation decisions should not be construed as departing from the scope of the invention.

[0049] The various illustrative logic blocks, modules, and circuits described in conjunction with the embodiments disclosed herein can be implemented or performed using a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components, or any combination thereof designed to perform the functions described herein. The general-purpose processor may be a microprocessor, but in alternatives, it may be any conventional processor, controller, microcontroller, or state machine. The processor may also be implemented as a combination of computing devices, such as a combination of a DSP and a microprocessor, multiple microprocessors, one or more microprocessors cooperating with a DSP core, or any other such configuration.

[0050] The steps of the methods or algorithms described in conjunction with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of both. The software module may reside in RAM memory, flash memory, ROM memory, EPROM memory, EEPROM memory, registers, hard disk, removable disk, CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor such that the processor can read and write information to / from the storage medium. In an alternative, the storage medium may be integrated into the processor. The processor and storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and storage medium may reside as discrete components in the user terminal.

[0051] In one or more exemplary embodiments, the described functionality may be implemented in hardware, software, firmware, or any combination thereof. If implemented in software as a computer program product, the functionality may be stored or transmitted as one or more instructions or code on or through a computer-readable medium. A computer-readable medium includes both computer storage media and communication media, encompassing any medium that facilitates the transfer of a computer program from one location to another. A storage medium may be any available medium accessible to a computer. By way of example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disc storage, disk storage or other magnetic storage devices, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and is accessible to a computer. Any connection is also legitimately referred to as a computer-readable medium. For example, if the software is transmitted from a website, server, or other remote source using coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwave, then the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwave are included in the definition of a medium. As used in this article, disk and disc include compact discs (CDs), laser discs, optical discs, digital multi-purpose discs (DVDs), floppy disks, and Blu-ray discs. Disks typically reproduce data magnetically, while discs reproduce data optically using lasers. Combinations of these should also be included within the scope of computer-readable media.

Claims

1. An integrated platform for aircraft engine health management based on a multi-core processor, characterized in that, Multiple virtual machines are constructed using a multi-core processor. These virtual machines integrate a lubricating oil and metal shavings monitoring device, a blade tip clearance measurement device, and an engine monitoring device into the multi-core processor-based aero-engine health management integrated platform. The platform comprises: a hardware layer, a core operating system layer, a partitioned operating system layer, and an application layer. The hardware layer includes real peripherals for integrating various device hardware devices and their virtual hardware drivers, as well as multi-core SoCs that provide computing resources. Through the hardware layer, corresponding computing resources and hardware signal resources are provided to the next layer, the core operating system layer. The core operating system layer is used to manage and allocate the computing resources and hardware signal resources provided by the hardware layer, thereby constructing multiple virtual partitions; The partitioning operating system layer manages and operates each virtual partition according to the security level requirements of each application in the application layer, thereby deploying applications with different security levels to different virtual partitions; The application layer is used to integrate the functional modules of the lubricating oil metal shavings monitoring device, blade tip clearance measurement device, and engine monitoring device based on multiple virtual partitions provided by the partitioned operating system layer, so as to achieve unified health monitoring and management on the same platform.

2. The integrated platform for aircraft engine health management based on a multi-core processor according to claim 1, characterized in that, The aero-engine health management integration platform based on a multi-core processor adopts a heterogeneous multi-core SOC as a multi-core processor deployed at the hardware layer, providing multiple flexibly allocable computing cores for the aero-engine health management integration platform through the heterogeneous multi-core SOC.

3. The integrated platform for aircraft engine health management based on a multi-core processor according to claim 2, characterized in that, The integrated platform for aero-engine health management based on a multi-core processor has a sensor signal acquisition system deployed at the hardware layer. The sensor signal acquisition system is used to collect hardware signal resources from various hardware devices, thereby monitoring the hardware devices of the lubricating oil metal shavings monitoring device, the blade tip clearance measuring device, and the engine monitoring device.

4. The integrated platform for aircraft engine health management based on a multi-core processor according to claim 3, characterized in that, The sensor signal acquisition system includes multiple conditioning units, which are connected to the sensors of each hardware device to acquire the sensor signals of the corresponding sensors. The conditioning unit includes a signal conditioning circuit and an A / D analog signal acquisition circuit. The signal conditioning circuit and the A / D analog signal acquisition circuit are used to acquire and process the sensor signals of each hardware device to obtain the corresponding hardware signal resources.

5. The integrated platform for aircraft engine health management based on a multi-core processor according to claim 4, characterized in that, The virtual hardware driver in the hardware layer also includes a signal processing algorithm link library, which uses pre-stored signal processing algorithms in the link library to process the sensor signals acquired from various hardware devices.

6. The integrated platform for aircraft engine health management based on a multi-core processor according to claim 4, characterized in that, The multi-core processor-based aero-engine health management integration platform connects to the sensors of various hardware devices through the sensor signal acquisition system. Then, through the core operating system layer, it abstracts each sensor into a virtual hardware driver in the form of a device tree, and then allocates the virtual hardware driver to different virtual partitions through the core operating system layer.

7. The integrated platform for aircraft engine health management based on a multi-core processor according to claim 2, characterized in that, The multi-core processor-based aero-engine health management integration platform deploys a virtualized operating system software at the core operating system layer. Through the deployed virtualized operating system software, multiple virtual partitions are constructed, thereby binding applications of different safety levels and their corresponding computing cores in the lubricating oil metal chip monitoring device, blade tip clearance measurement device, and engine monitoring device to the corresponding virtual machines.

8. The integrated platform for aircraft engine health management based on a multi-core processor according to claim 6, characterized in that, The multi-core processor-based aero-engine health management integration platform binds applications with different safety levels and corresponding computing cores in the lubricating oil metal chip monitoring device, blade tip clearance measurement device, and engine monitoring device to corresponding virtual partitions. Then, it provides the necessary virtual hardware drivers for each virtual partition through virtualized operating system software, so that applications on different virtual partitions can obtain the corresponding hardware signal resources.

9. The integrated platform for aircraft engine health management based on a multi-core processor according to claim 1, characterized in that, Virtualized inter-domain communication technology is used between virtual machines to exchange information, enabling data transmission between applications integrated on the same aero-engine health management platform.

10. The integrated platform for aircraft engine health management based on a multi-core processor according to claim 4, characterized in that, The partitioned operating system uses partitioned communication technology based on the ARINC653 standard for inter-partition communication.

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