A health management system, a health management method, and an electric aircraft

Abstract

This invention relates to the field of health management technology, and discloses a health management system, a health management method, and an electric aircraft. The system includes: an airborne system, which is divided into preset layers according to the functional characteristics of the controllers deployed on the airborne terminal, for hierarchical data collection and health assessment; and a ground system, which is wirelessly connected to the airborne system to receive the health assessment results from the airborne system and perform a comprehensive health assessment. This invention utilizes the controllers on the airborne terminal to deploy an airborne health management system with different layers, and is complemented by a ground-based health management system. This avoids the need for additional data collection and analysis systems on the airborne terminal, saving costs and reducing the weight of the airborne terminal. Furthermore, the complex comprehensive health assessment performed by the ground system ensures the accuracy and reliability of the health assessment.

Description

Technical Field

[0001] This invention relates to the field of health management technology, specifically to a health management system, method, and electric aircraft. Background Technology

[0002] The main purpose of aircraft health management is to improve flight safety, enhance aircraft reliability and availability, extend aircraft lifespan, reduce maintenance costs throughout the life cycle, and provide more efficient maintenance management through data analysis and predictive maintenance.

[0003] In aviation, a separate data acquisition and analysis system is typically used to monitor the parameters of electric aircraft and analyze their health status. This approach not only incurs significant equipment costs but also adds considerable weight. Summary of the Invention

[0004] In view of this, the present invention provides a health management system, a health management method, and an electric aircraft to solve the problems of high cost and increased aircraft weight of existing health management systems.

[0005] In a first aspect, the present invention provides a health management system, the system comprising:

[0006] The airborne system is divided into preset layers based on the functional characteristics of the controllers deployed on the airborne terminal, which is used to perform hierarchical data collection and health assessment on the airborne terminal.

[0007] The ground system connects to the airborne system to receive health assessment results from the airborne system and to conduct a comprehensive health assessment.

[0008] The health management system provided in this invention divides the recording system into preset layers based on the functional characteristics of the controllers deployed on the airborne terminal. It performs hierarchical data collection and health assessment on the airborne terminal, and a ground system connected to the airborne system receives the health assessment results and performs a comprehensive health assessment. By utilizing the controllers on the airborne terminal to deploy an airborne health management system with different layers, and in conjunction with a ground-based health management system, this invention avoids the need for additional data collection and analysis systems on the airborne terminal, saving costs and reducing the weight of the airborne terminal. Furthermore, the complex comprehensive health assessment performed by the ground system ensures the accuracy and reliability of the health assessment.

[0009] In one optional implementation, the airborne system includes: a component-level subsystem, a region-level subsystem, and a system-wide subsystem. The component-level subsystem includes components interconnected via input / output interfaces and wiring harnesses. The components include: component controllers, actuators, and sensors. The component controller is used to acquire the operating status and operating parameters of the components, perform component-level health assessments based on the operating status and operating parameters, determine the first fault level of the components, and generate a first-cycle health status message.

[0010] This invention acquires the working status and parameters of itself, actuators, and sensors through a component controller, enabling component-level data acquisition and providing basic operational data for subsequent health assessments. This allows the current health status of the airborne system to be determined based on the operating conditions of the components.

[0011] In one optional implementation, the regional subsystem includes: a regional controller; the regional controller pre-deploys an inference model and is connected to at least one component controller, for performing a regional-level health assessment based on the first-cycle health status message uploaded by the component controller, obtaining a second fault level and redundancy of a preset region, and generating a second-cycle health status message.

[0012] This invention acquires basic operational data collected by component-level controllers with strong functional correlation through a regional controller. It can fully consider the correlation information between various components and perform preliminary comprehensive analysis and reasoning on the airborne faults according to the region. This is equivalent to integrating and processing component-level fault information, thereby improving the reliability of health assessment results.

[0013] In one optional implementation, the system-level subsystem includes: a system controller; the system controller, connected to the component controller and the area controller, is used to perform a system-level health assessment based on the first periodic health status message uploaded by the component controller and the second periodic health status message uploaded by the area controller, determine the overall health status, and generate a third periodic health status message.

[0014] This invention acquires periodic health status messages from component-level and region-level subsystems through the overall controller, enabling comprehensive analysis of the vehicle's operational status at the highest level for onboard fault diagnosis and health management, further improving the reliability of health assessment results. Furthermore, data transmission between controllers at different levels on the airborne end via periodic health status messages allows for the full utilization of network resources, fully utilizing various operational and fault information. Moreover, no connection needs to be established between levels, and messages can be sent periodically, resulting in high reliability and flexibility.

[0015] In one optional implementation, the ground system pre-deploys a fault prediction model and a health database, which are connected to the overall controller. This model is used to perform a comprehensive health assessment based on the first-cycle health status messages, the second-cycle health status messages, and the third-cycle health status messages uploaded by the controllers at each level, and to generate alarm signals and / or warning signals based on the comprehensive health assessment results.

[0016] This invention acquires periodic health status messages generated at various levels of the airborne terminal through a ground system. A complex health assessment algorithm onboard the ground system performs a final comprehensive analysis, generating alarm information based on the analysis results. This alerts operators to promptly perform maintenance on the airborne terminal, preventing further escalation of faults. Simultaneously, based on a fault prediction model, it provides early warnings of impending faults, reminding operators to perform maintenance on the airborne terminal in advance, thus preventing failures from occurring. Therefore, through alarms and early warnings, this invention provides more efficient maintenance management for the airborne terminal, improving its security, reliability, and availability, extending its service life, and reducing maintenance costs throughout its lifecycle.

[0017] In one optional implementation, a system-wide health assessment is performed based on the first-cycle health status report uploaded by the component controller and the second-cycle health status report uploaded by the area controller to determine the overall system health level. This includes: obtaining pre-determined weights for components and preset areas; determining the health level score of components based on the first fault level in the first-cycle health status report, and determining the health level score of preset areas based on the second fault level and redundancy in the second-cycle health status report; and performing a weighted summation based on the weights and health level scores to obtain the overall system health level.

[0018] This invention calculates the overall health status of the machine based on the weights and health scores of different components or regions. It can combine multiple indicators from various systems for overall analysis, comprehensively reflecting the current health status of the airborne terminal, providing operators with accurate fault information, so that operators can take appropriate measures based on the health status, thereby improving the safety and availability of the airborne terminal.

[0019] In one alternative implementation, the ground system further includes a human-machine interface for displaying comprehensive health assessment results, alarm signals, and / or warning signals.

[0020] This invention provides a human-machine interface that can intuitively display comprehensive health assessment results, alarm signals, and early warning signals to operators, enabling them to quickly understand and grasp the current operating status of the onboard unit and take necessary measures for maintenance or repair.

[0021] In one alternative implementation, the regional subsystem further includes switching the regional controller based on a second fault level and redundancy.

[0022] This invention switches the controllers at the regional subsystem level according to redundancy, enabling the system to switch to a non-faulty control system to control the airborne terminal when a fault occurs. This avoids situations where the airborne terminal cannot operate normally due to faults, thereby improving the operational reliability and availability of the airborne terminal.

[0023] Secondly, the present invention provides a health management method, which performs a health assessment on an airborne device based on a health management system based on the first aspect above or any corresponding embodiment thereof.

[0024] Since the health management method is based on the aforementioned health management system and has the same effect, it will not be elaborated further here.

[0025] Thirdly, the present invention provides an electric aircraft, including an airborne system in the health management system of the first aspect or any corresponding embodiment described above.

[0026] Since electric aircraft include the airborne systems in the aforementioned health management system and have the same effects as the health management system, they will not be elaborated upon here. Attached Figure Description

[0027] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0028] Figure 1 This is a structural block diagram of a health management system according to an embodiment of the present invention;

[0029] Figure 2 This is a structural block diagram of the health management system according to an embodiment of the present invention;

[0030] Figure 3 This is a schematic diagram of the internal components of a health management system according to an embodiment of the present invention;

[0031] Figure 4 This is a flowchart illustrating a health management system according to an embodiment of the present invention;

[0032] Figure 5 This is a flowchart illustrating a health management method according to an embodiment of the present invention.

[0033] Explanation of reference numerals in the attached figures: 100-Airborne system; 101-Component-level subsystem; 102-Regional-level subsystem; 103-Complete-system-level subsystem; 200-Ground system. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, 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, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] This invention provides a health management system that utilizes an airborne controller to deploy the airborne system and integrates it with a ground-based system to reduce health assessment costs and airborne weight.

[0036] According to embodiments of the present invention, a health management system embodiment is provided. It should be noted that, as used below, the terms "module" or "system" can refer to a combination of software and / or hardware that performs a predetermined function. Although the apparatus described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0037] This embodiment provides a health management system that can perform health management on the aforementioned airborne terminal. Figure 1 This is a structural block diagram of a health management system according to an embodiment of the present invention, such as... Figure 1 As shown, the health management system includes:

[0038] Airborne system 100, based on the functional characteristics of the controllers deployed on the airborne terminal, divides the airborne system into preset layers for hierarchical data collection and health assessment of the airborne terminal.

[0039] Ground system 200, connected to airborne system 100, is used to receive health assessment results from airborne system 100 and to perform comprehensive health assessment.

[0040] Specifically, in this embodiment of the invention, taking an electric aircraft as an example, in order to perform functional control on the electric aircraft, specific components that perform corresponding functions are pre-deployed inside the electric aircraft, including component controllers, actuators, and sensors. These components are connected through input / output (I / O) interfaces and wiring harnesses to form a component-level control system, such as electric drive, electronic control, thermal management, and navigation systems. In this component-level system, the controller generates control commands for the actuators. After the control commands are sent to the actuators, the actuators execute the corresponding actions according to the control commands. For example, an electric drive consists of key components such as a motor, controller, battery, and inverter. This controller is a component controller, and the motor is the actuator. The component controller controls the motor, converting electrical energy from the battery into mechanical energy to drive the motor to rotate and generate propulsion. Sensors are used to measure the working status and data of components. For example, photoelectric sensors are used to measure the speed of an electric motor. Finally, the component controller collects the working status and parameters of each component, including the working status and parameters of the component controller itself, as well as the working status and parameters of the sensors and actuators. This enables component-level data acquisition, providing basic operational data for subsequent health assessments and determining the current health status of the airborne system based on the operating conditions of the components.

[0041] In some alternative implementations, in order to achieve comprehensive control of various components, area controllers are pre-deployed on the electric aircraft. The area controllers are connected to component controllers with strong functional dependencies, thereby forming different area-level control systems from highly functional components. These include the electric aircraft's power system, flight control system, autopilot system, and communication system. Taking the power system as an example, it includes component-level electric drive and electronic control systems. Through the cooperation between the various component-level control systems, the electric aircraft is powered to support its takeoff, flight, and landing.

[0042] In some alternative implementations, in order to achieve comprehensive control of the electric aircraft, a whole-aircraft controller is pre-deployed on the electric aircraft and connected to various area controllers. It can also be directly connected to component controllers to form a whole-aircraft control system, which is used to uniformly manage various area-level control systems and some component controllers to ensure the normal operation of the electric aircraft.

[0043] In some optional implementations, embodiments of the present invention are based on existing component-level control systems, regional-level control systems, and overall control systems for electric aircraft. An airborne system 100 is deployed at the airborne end for data acquisition and health assessment. Based on the functional characteristics of the controllers in each level of the control system, the airborne system is divided into three levels: component-level subsystem 101, regional-level subsystem 102, and overall-level subsystem 103, such as... Figure 2 As shown. Each level contains some basic health management functions, but each has its own focus and division of labor. For example, all three levels of subsystems need to implement basic health management sub-functions, mainly including data acquisition, data transmission interface, data processing, data standardization, fault detection, online diagnosis and other basic functions. In addition to implementing the above basic functions, the whole-system subsystem 103 and the regional subsystem 102 also need to focus on implementing comprehensive fault handling, fault isolation analysis, redundancy management, alarm prompts, health reports, decision support and other functions.

[0044] In some alternative implementations, the component-level subsystem 101 includes component controllers, actuators, and sensors interconnected via input / output interfaces and wiring harnesses, for example... Figure 3 The component controllers, actuators, and sensors in the control systems for components such as electric drives, electronic controls, thermal management, navigation, or instrumentation, as shown, primarily perform the following functions: data acquisition, i.e., collecting and processing parameters from connected sensors and actuators; reporting operating status parameters and operating mode information; and using sensors, diagnostic detection, and models to perform fault detection on themselves and their connected components, supporting fault isolation. Component-level subsystems support data interfaces with the fault diagnosis and health management functions of regional-level subsystems. Each component controller generates a Periodic Health Status Message (PHSM) based on the collected information and submits it directly to the intermediate-layer regional controller.

[0045] In some optional implementations, the regional subsystem 102 in this embodiment of the invention includes a regional controller connected to component controllers with strong functional dependencies, such as... Figure 3The diagram shows various component control systems, including power systems, flight control systems, autopilot systems, communication systems, low-voltage electrical systems, and display control systems. These systems perform regional-level health assessments based on periodic health status reports uploaded by the component controllers, obtaining the fault level and redundancy for each region and generating corresponding periodic health status reports. The region controller primarily functions as a signal processing, information fusion, and region inference engine, serving as a real-time processing unit for continuously monitoring the operational status of the corresponding component-level control systems of the electric aircraft. The region controller acts as the interface unit connecting the overall aircraft-level health management system and the component-level subsystems. The main functions of the region-level subsystems are as follows: confirming fault reports, filtering false alarms, and evaluating intermittent faults; utilizing cross-component-level control system correlation information and employing inference models to achieve enhanced fault detection and isolation; predicting impending hardware faults (with limited prediction cases); supporting the generation, synthesis, and management of alarm information; and managing, judging, and switching redundancy. The inference model is deployed within the region controller after model verification and parameter optimization on a component test bench, a standard technique in this field and will not be elaborated upon further. Redundancy management, judgment, and switching mean that the area controller on an electric aircraft can switch the current control components. For example, if the flight control system has 3 redundancy levels, and the currently operating flight control system fails, the flight controller can switch control to another flight control system. This is a common technique in the field and will not be elaborated further here. Figure 4 As shown, enhanced fault diagnosis, confirmation, isolation, and reporting include: receiving fault reports and status information from all associated sub-component-level control systems / components; performing feature extraction, analysis, and multi-source information fusion to achieve regional-level fault diagnosis, fault confirmation (filtering false alarms and evaluating intermittent faults), and precise fault location (locating faults within the component-level control system); classifying confirmed faults by severity; and promptly making selective reports to the overall controller. Feature extraction, analysis, and multi-source information fusion involve selecting relevant data for a specific type of fault, extracting data and features, thereby confirming the cause of the fault and reducing the risk of failure. For example, for speed fluctuations, data such as throttle, motor voltage, motor current, and their rate of change can be extracted; this is just an example and not a limitation.

[0046] In some optional implementations, the system-level subsystem 103 includes: a system controller, connected to component controllers and area controllers, used to perform system-level health assessments based on periodic health status messages uploaded by component controllers and area controllers, determine the overall system health level, and generate corresponding periodic health status messages. The system-level subsystem integrates intelligent information fusion, management, and transmission capabilities to manage and control data fed back from various area controllers or component controllers distributed throughout the system. It processes fault diagnosis and health management data through an onboard fault reasoning and monitoring model, achieving the highest level of integrated functions for onboard fault diagnosis and health management, and serving as the interface between the onboard system for onboard fault diagnosis and health management and the ground system for ground-based fault diagnosis and health management. The main functions performed by the system-level subsystem are as follows: performing cross-regional and cross-component fault data integration; online monitoring of system-level faults and partial fault prediction; managing the processing priority of onboard system fault diagnosis and health management; and managing the information dissemination and transmission of onboard system fault diagnosis and health management. This invention achieves fault diagnosis and health management on the airborne end through the cooperation of controllers at various levels.

[0047] In some optional embodiments, the embodiment of the present invention also deploys a ground system 200 that is compatible with the airborne system 100. Among them, the ground system 200 can be deployed in the cloud. The reason it is called the ground system is to distinguish it from the airborne system carried on the airborne side. The ground system 200 communicates with the whole-aircraft-level subsystem 103 of the airborne system 100 through wireless communication technology and receives the periodic health status message uploaded by the whole-aircraft controller. The periodic health status message uploaded at this time includes the periodic health status messages generated at each level. The ground system 200 conducts a comprehensive health assessment again based on all the periodic health status messages to achieve monitoring of the whole-aircraft fault status, status monitoring alarm, whole-aircraft health status assessment, fault prediction of key and important components, diagnosis data management, life prediction of time-life components, maintenance assistance decision-making, etc., and deploys a maintenance database, a diagnosis database, a fault case database, etc., providing important support for the life cycle management in the subsequent operation and use of electric aircraft. Specifically, the ground system transmits data with the whole-aircraft controller through the communication air-ground data communication interface, and can obtain various health management-related information uploaded by the electric aircraft in real time, including but not limited to the following information: flight control status, flight attitude (pitch angle, roll angle, heading angle), flight heading, flight speed, flight position, high-voltage power-on and power-off status, power battery power, output actual total power, minimum voltage, maximum current, minimum single-cell voltage, maximum temperature of the power battery, minimum temperature of the power battery, power battery charging status, DCDC (direct current - direct current converter) working status, DCDC output voltage, DCDC output current, motor speed, electronic control temperature, motor temperature, electric drive high-voltage voltage, PHSM of each part level / area / whole-aircraft controller, etc. The ground system 200 stores and analyzes the uploaded health management-related information in real time, and monitors the working range of the signal value in real time to achieve the functions of instant alarm and early warning; based on the capabilities of the ground system 200, the operation status and historical status of the electric aircraft can be queried in real time; based on the health assessment model of the data platform, according to the operation status information, fault information and PHSM information of each level uploaded by the electric aircraft, the health status of the whole aircraft can be evaluated; based on the existing historical data and the real-time uploaded data, the fault prediction model can be used to predict the faults of key and important components in real time, give early warnings, and give suggestions for maintenance inspections in advance; for the confirmed faults, using the powerful data storage and computing capabilities of the ground system 200, according to the information in the maintenance database, diagnosis database, fault case database, professional knowledge database, etc., inference-generated maintenance assistance suggestions are generated. The ground system 200 is provided with a human-computer interaction interface for intuitively displaying the above various health assessment results, alarm signals and early warning signals to the operator, enabling the operator to quickly understand and master the current operation situation of the airborne side, so as to take necessary measures for maintenance or repair.This invention generates alarm information based on the analysis results, notifying operators to perform timely maintenance on the airborne terminal to prevent further escalation of the fault. At the same time, based on the fault prediction model, it provides early warning of impending faults, reminding operators to perform maintenance on the airborne terminal in advance to prevent the fault from occurring. Therefore, through alarms and early warnings, it can provide more efficient maintenance management for the airborne terminal, improve the safety, reliability and availability of the airborne terminal, extend the service life of the airborne terminal, and reduce maintenance costs throughout its life cycle.

[0048] In some optional implementations, each level controller issues a periodic Health Status Message (PHSM) based on its own characteristics. A message is a data unit exchanged and transmitted in the network, containing complete data and control information to be sent from the source to the destination. Messages vary greatly in length, are unlimited and variable, ensuring data integrity and accuracy. Furthermore, messages can be transmitted at different network layers, adapting to different network environments and needs, fully utilizing network resources. No connection needs to be established between levels, and messages can be sent periodically, offering high reliability and flexibility. During transmission, messages can be decomposed into multiple data packets, which are then encapsulated into frames for transmission, making it applicable to a wide range of scenarios. The information included in the PHSM of this embodiment is as follows: node fault level, low-voltage power supply status, CAN interface communication status, Ethernet communication status, network management, external storage space utilization, node loss status, fault code status signal, Counter (message counter), and Checksum (checksum) signal. These are merely examples and not intended to be limiting. The Counter is a 4-bit message counter located in the CAN message data segment. Its main function is to ensure that no frames are lost during message transmission. Each time a message is sent, the counter value increases by 1, accumulating from 0 to 15 in a continuous loop. If the receiver detects a discontinuous counter or incorrect beginning and end values, it assumes frame loss has occurred and reports the corresponding fault code 1. Checksum is a simple and efficient data verification method. The sending end obtains a Checksum value using a defined calculation method and adds it to the CAN message data segment before sending it. Upon receiving the message, the receiving end recalculates the Checksum value using the same method and compares it with the received Checksum value. If they match, the data is correct; otherwise, the data is considered incorrect. Periodic health status messages can take various forms and can be sent through different bus types. The information contained can be increased or decreased according to actual needs. For controllers with multiple buses, the messages sent by each controller must be sent on at least two channels.

[0049] In some optional implementations, as can be seen from the functional descriptions of the subsystems at each level above, the present invention divides fault levels in the component-level subsystem 101 and the area-level subsystem 102. Each controller determines the fault level based on its own hardware working status and the functions it undertakes in the whole machine. Generally, there are 5 levels: normal, warning, level 1 general fault, level 2, level 3 general functional fault, level 4 and level 5 severe fault. This is only an example and is not limited thereto.

[0050] In some optional implementations, in the system-level subsystem 103, the overall system health level is determined through comprehensive analysis. The determination process includes: obtaining pre-determined weights Pi of components and preset areas; determining the health level score Phi of components or areas based on periodic health status messages; considering the redundancy of areas when determining the health level score of areas; the sum of the weights of each component or area is 1; and the maximum score for the health level score is 100 points, based on different hardware failures and functional failures. Therefore, the weights and health level scores are weighted and summed to obtain the overall system health level, i.e.:

[0051] Overall machine health status = ∑(Pi*Phi)

[0052] Specifically, if the calculated overall aircraft health level is less than 70, it indicates a serious malfunction in the electric aircraft, potentially posing a crash risk. A health level between 70 and 80 indicates a malfunction requiring immediate landing for repairs to prevent danger. A health level between 80 and 90 indicates a minor malfunction requiring prompt repair. A health level between 90 and 100 indicates normal operation of the electric aircraft without significant safety impact. Therefore, this invention combines multiple indicators from various systems for comprehensive analysis, reflecting the current airborne health level and providing operators with accurate fault information. This allows operators to take appropriate measures based on the health level, improving the safety and availability of the airborne system.

[0053] In some optional implementations, the division of regional subsystems can be skipped between different levels of subsystems in the embodiments of the present invention. Data can be directly reported from the component-level controller to the vehicle-level controller. The health management of the vehicle-level subsystem can be monitored and allocated simultaneously at the airborne end and the ground end. Based on the characteristics of the airborne system, which has strong real-time performance but limited computing power, and the server, which has poor real-time performance but strong computing power, flexible configuration can be made based on the complementary characteristics of the two.

[0054] In some optional implementations, the component-level, region-level, and whole-machine-level aspects of this invention can be combined according to the actual functional allocation. This can support direct progression from the component-level to the whole-machine-level, or it can omit the component-level and proceed directly from the region-level to the whole-machine-level, depending on the actual operational situation. Based on the three-level hierarchical concept, the health management assessment algorithm used in the health management system can perform machine learning inference and classification based on existing cases or data in the field to assess the impact of faults. Furthermore, an expert system can be introduced during ground service assessment. Through comprehensive processing by experts or a knowledge base, the health status of the whole machine or components can be determined. This is merely an example and not a limitation.

[0055] In some optional implementations, embodiments of the present invention utilize existing controller modules located in different parts of the fuselage and performing different functions, as well as existing sensors and actuators in electric aircraft, to aggregate data to the whole-aircraft area gateway module through various bus transmission methods. The data is then processed, packaged, and uploaded to the cloud via a wireless communication link. Simultaneously, it supports fault monitoring, fault prediction, and whole-aircraft health assessment on electric aircraft.

[0056] The health management system provided in this invention divides the recording system into preset layers based on the functional characteristics of the controllers deployed on the airborne terminal. It performs hierarchical data collection and health assessment on the airborne terminal, and a ground system connected to the airborne system receives the health assessment results and performs a comprehensive health assessment. By utilizing the controllers on the airborne terminal to deploy an airborne health management system with different layers, and in conjunction with a ground-based health management system, this invention avoids the need for additional data collection and analysis systems on the airborne terminal, saving costs and reducing the weight of the airborne terminal. Furthermore, the complex comprehensive health assessment performed by the ground system ensures the accuracy and reliability of the health assessment.

[0057] According to an embodiment of the present invention, a health management method embodiment is provided. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0058] This embodiment provides a health management method based on the above. Figure 2 The health management system shown performs health assessments on the onboard device. Figure 5 This is a flowchart of a health management method according to an embodiment of the present invention, such as... Figure 5 As shown, the process includes the following steps:

[0059] In step S501, after the airborne terminal is powered on, the component-level subsystem, the regional-level subsystem, and the overall subsystem complete system initialization.

[0060] In step S502, each component controller collects its working status and parameters, and sends out the first cycle health status message.

[0061] In step S503, the area controller performs an area-level health assessment based on the first-cycle health status message, determines the health management status of each area, obtains the second fault level and redundancy of each area, and sends out the second-cycle health status message.

[0062] In step S504, the system controller performs a system-level health assessment based on the first and second cycle health status messages to determine the overall health status and generates a third cycle health status message.

[0063] In step S505, the ground system performs a comprehensive health assessment based on the first cycle health status message, the second cycle health status message, and the third cycle health status message, and generates alarm signals and / or warning signals based on the comprehensive health assessment results.

[0064] Specifically, in the embodiments of the present invention, each step of the method is performed based on the above-described embodiments and preferred implementations of the health management system, and has the same effect as the health management system. Details that have already been described will not be repeated here.

[0065] This invention also provides an electric aircraft, including the above-described... Figure 1 , Figure 2 or Figure 3 The airborne system in the health management system shown executes the above... Figure 5 The health management methods described here have the same effect as the health management system, and will not be elaborated further here.

[0066] In addition, the above Figure 1 , Figure 2 or Figure 3 The health management system shown is also applicable to electronic and electrical architectures of different carriers and bus types, such as multi-rotor or fixed-wing electric aircraft, automobiles or other electromechanical equipment, etc., without limitation. The specific setup is determined according to the actual situation of the carrier or electronic and electrical architecture, and the data collected related to health management is also determined according to the operation of the carrier or electronic and electrical architecture.

[0067] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A health management system, characterized in that, The system includes: The airborne system is divided into preset layers according to the functional characteristics of the controllers deployed on the airborne terminal, which is used to perform hierarchical data collection and health assessment on the airborne terminal. A ground system, connected to the airborne system, is used to receive the health assessment results of the airborne system and perform a comprehensive health assessment; The airborne system includes: component-level subsystems, region-level subsystems, and system-level subsystems, wherein... The component-level subsystem includes components interconnected via input / output interfaces and wiring harnesses, and the components include component controllers, actuators, and sensors. The component controller is used to acquire the working status and working parameters of the component, perform component-level health assessment based on the working status and working parameters, determine the first fault level of the component, and generate a first-cycle health status message.

2. The system according to claim 1, characterized in that, The regional subsystem includes: a regional controller; The regional controller pre-deploys an inference model and connects to at least one of the component controllers. It performs a regional-level health assessment based on the first-cycle health status message uploaded by the component controller, obtains the second fault level and redundancy of the preset region, and generates a second-cycle health status message.

3. The system according to claim 2, characterized in that, The system-level subsystem includes: a system controller; The overall controller, connected to the component controller and the area controller, is used to perform an overall health assessment based on the first periodic health status message uploaded by the component controller and the second periodic health status message uploaded by the area controller, determine the overall health level, and generate a third periodic health status message.

4. The system according to claim 3, characterized in that, The ground system pre-deploys a fault prediction model and a health database, which are connected to the main controller. The system is used to perform a comprehensive health assessment based on the first-cycle health status message, the second-cycle health status message and the third-cycle health status message uploaded by the main controller, and to generate alarm signals and / or warning signals based on the comprehensive health assessment results.

5. The system according to claim 3, characterized in that, The step of performing a system-wide health assessment based on the first periodic health status message uploaded by the component controller and the second periodic health status message uploaded by the area controller to determine the overall system health status includes: Obtain the predetermined weights of the components and the preset regions; The health score of the component is determined based on the first fault level in the first periodic health status message, and the health score of the preset area is determined based on the second fault level and the redundancy in the second periodic health status message. The overall health status of the machine is obtained by weighted summation based on the weights and the health score.

6. The system according to claim 4, characterized in that, The ground system also includes a human-machine interface for displaying the comprehensive health assessment results, the alarm signals, and / or the early warning signals.

7. The system according to claim 2, characterized in that, The regional subsystem further includes: switching the regional controller according to the second fault level and the redundancy.

8. A health management method, characterized in that, The health management system based on any one of claims 1 to 5 performs a health assessment on the airborne terminal.

9. An electric aircraft, characterized in that, include: The airborne system in the health management system according to any one of claims 1 to 5.

Images