Health management system, health management method and electric aircraft

Abstract

The invention relates to the technical field of health management, and discloses a health management system, a health management method and an electric aircraft, and the system comprises an airborne system which is divided into preset hierarchies according to the functional characteristics of a controller of an airborne end, and is used for carrying out the hierarchical data collection and health evaluation of the airborne end; and the ground system is wirelessly connected with the airborne system and is used for receiving the health assessment result of the airborne system and carrying out comprehensive health assessment. According to the invention, the controller of the airborne end is utilized to deploy the airborne end health management system comprising different levels, and the ground end health management system is matched, so that the airborne end can be prevented from being additionally provided with a data acquisition and data analysis processing system, the cost is saved, and the weight of the airborne end is reduced; and meanwhile, the accuracy and reliability of health assessment can be ensured by performing complex comprehensive health assessment by a ground system.

Description

Technical Field

[0001] The present invention relates to the technical field of health management, and in particular to a health management system, method and electric aircraft. Background Art

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

[0003] In aviation, an additional data collection and data analysis processing system is generally used to monitor the parameters of electric aircraft and analyze the health management status of electric aircraft. Such a solution will not only bring high equipment costs, but also add a lot of extra 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 the existing health management system.

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

[0006] Airborne systems, which are divided into preset levels according to the functional characteristics of the controllers deployed on the airborne end, are used for hierarchical data collection and health assessment of the airborne end;

[0007] The ground system is connected to the airborne system, and is used to receive the health assessment results of the airborne system and perform a comprehensive health assessment.

[0008] The health management system provided by the embodiment of the present invention divides the recording system into preset levels according to the functional characteristics of the controller deployed on the airborne end, performs hierarchical data collection and health assessment on the airborne end, and the ground system connected to the airborne system receives the health assessment results of the recording system and performs a comprehensive health assessment. The present invention uses the controller of the airborne end to deploy an airborne health management system including different levels, and matches the ground health management system, which can avoid the need for additional data collection and data analysis and processing systems on the airborne end, save costs, and reduce the weight of the airborne end. At the same time, the complex comprehensive health assessment performed by the ground system can ensure the accuracy and reliability of the health assessment.

[0009] In an optional embodiment, the airborne system includes: a component-level subsystem, a regional-level subsystem and a whole-machine-level subsystem, wherein the component-level subsystem includes: components interconnected through input and output interfaces and wiring harnesses, the components including: a component controller, an actuator and a sensor; a component controller, for obtaining the working status and working parameters of the component, performing a component-level health assessment based on the working status and working parameters, determining the first fault level of the component, and generating a first-cycle health status message.

[0010] The present invention obtains the working status and working parameters of itself, the actuator and the sensor through the component controller, can realize component-level data collection, and provide basic operating data of the airborne end for subsequent health assessment, so as to determine the current health status of the airborne end according to the operating status of the component.

[0011] In an optional embodiment, the regional-level subsystem includes: a regional controller; the regional controller pre-deploys an inference model and is connected to at least one component controller, and is used to perform a regional-level health assessment based on a first-cycle health status message uploaded by the component controller, obtain a second fault level and redundancy of a preset area, and generate a second-cycle health status message.

[0012] The present invention obtains basic operating data collected by part-level controllers with strong functional correlation through regional controllers, can fully consider the correlation information between various components, and perform preliminary comprehensive analysis and reasoning on the faults of the airborne end according to the region, which is equivalent to integrating and processing the fault information at the component level, thereby improving the reliability of the health assessment results.

[0013] In an optional embodiment, the whole machine level subsystem includes: a whole machine controller; a whole machine controller connected to the component controller and the regional controller, and used to perform a whole machine level health assessment based on the first cycle health status message uploaded by the component controller and the second cycle health status message uploaded by the regional controller, determine the health level of the whole machine, and generate a third cycle health status message.

[0014] The present invention obtains periodic health status messages of component-level subsystems and regional-level subsystems through the whole machine controller, and can perform the highest level of comprehensive analysis of the operating status of the whole vehicle in terms of onboard fault diagnosis and health management, further improving the reliability of the health assessment results. In addition, the data transmission between the various levels of controllers on the airborne end is carried out through periodic health status messages, which can transmit various operating information and fault information, etc., can make full use of network resources, and there is no need to establish a connection between the various levels, and messages can be sent periodically, with high reliability and flexibility.

[0015] In an optional embodiment, the ground system pre-deploys a fault prediction model and a health database, which are connected to the whole machine controller, for performing a comprehensive health assessment based on the first cycle health status messages, second cycle health status messages, and third cycle health status messages uploaded by controllers at each level, and generating an alarm signal and / or early warning signal based on the comprehensive health assessment results.

[0016] The present invention obtains the periodic health status messages generated by each level of the airborne terminal through the ground system, and can perform a final comprehensive analysis by the complex health assessment algorithm carried by the ground system, generate alarm information based on the analysis results, and notify the operator to repair the airborne terminal in time to avoid further expansion of the fault; at the same time, based on the fault prediction model, early warning is given to the impending fault, reminding the operator to maintain the airborne terminal in advance to avoid the occurrence of the fault. Therefore, the present invention can provide more efficient maintenance management for the airborne terminal through alarms and warnings, improve the safety, reliability and availability of the airborne terminal, extend the service life of the airborne terminal, and reduce the maintenance cost within the life cycle.

[0017] In an optional embodiment, a whole-machine health assessment is performed based on the first-cycle health status message uploaded by the component controller and the second-cycle health status message uploaded by the area controller to determine the health of the whole machine, including: obtaining weights of predetermined components and preset areas; determining the health score of the component based on the first fault level in the first-cycle health status message, and determining the health score of the preset area based on the second fault level and redundancy in the second-cycle health status message; and performing weighted summation based on the weight and health score to obtain the health of the whole machine.

[0018] The present invention calculates the health of the entire machine according to the weights and health scores of different components or areas, and can combine multiple indicators of each system for overall analysis, comprehensively reflect the current health of the airborne terminal, and provide operators with accurate fault conditions, so that the operator can take appropriate measures according to the health level and improve the safety and availability of the airborne terminal.

[0019] In an optional embodiment, the ground system further includes: a human-computer interaction interface for displaying comprehensive health assessment results, alarm signals and / or early warning signals.

[0020] The present invention can intuitively display comprehensive health assessment results, alarm signals and early warning signals to operators by providing a human-computer interaction interface, so that operators can quickly understand and grasp the current operating conditions of the airborne terminal and take necessary measures for maintenance or repair.

[0021] In an optional implementation, the regional subsystem further includes: switching the regional controller according to the second fault level and redundancy.

[0022] The present invention switches the controller according to redundancy in the regional subsystem, and can switch to a control system that has not failed to control the airborne end when a failure occurs, thereby avoiding the situation where the airborne end cannot operate normally due to the failure, and improving the operational reliability and availability of the airborne end.

[0023] In a second aspect, the present invention provides a health management method, which performs a health assessment on an onboard terminal based on the health management system of the first aspect or any corresponding embodiment thereof.

[0024] Because the health management method is executed based on the above-mentioned health management system and has the same effect as the health management system, it will not be repeated here.

[0025] In a third aspect, the present invention provides an electric aircraft, comprising an onboard system in a health management system according to the first aspect or any corresponding embodiment thereof.

[0026] Because the electric aircraft includes the onboard system in the above-mentioned health management system, which has the same effect as the health management system, it will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

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

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

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

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

[0032] Figure 5 4 is a flowchart of a health management method according to an embodiment of the present invention.

[0033] Explanation of reference numerals: 100 - airborne system; 101 - component-level subsystem; 102 - regional-level subsystem; 103 - whole-machine-level subsystem; 200 - ground system. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0035] The embodiment of the present invention is applicable to the application scenario of health management of the airborne terminal, taking an electric aircraft as an airborne terminal as an example. The embodiment of the present invention provides a health management system, which deploys the airborne system by using the controller of the airborne terminal and combines the ground system to achieve the effect of saving health assessment costs and reducing the weight of the airborne terminal.

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

[0037] In this embodiment, a health management system is provided, which can perform health management on the above-mentioned airborne terminal. Figure 1 is a structural block diagram of a health management system according to an embodiment of the present invention. Figure 1 As shown, the health management system includes:

[0038] The airborne system 100 divides the airborne system into preset levels according to the functional characteristics of the controller deployed on the airborne terminal, and is used for hierarchical data collection and health assessment of the airborne terminal;

[0039] The ground system 200 is connected to the airborne system 100 and is used to receive the health assessment result of the airborne system 100 and perform a comprehensive health assessment.

[0040] Specifically, in the embodiment of the present 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. Each component is connected through an input / output (I / O) interface and a harness to form a component-level control system, such as electric drive, electric control, thermal management, navigation, etc. Among them, the controller in the component-level system is used to generate control commands for the actuator. After the control commands are sent to the actuator, the actuator performs corresponding actions according to the control commands. For example, the electric drive is composed of key components such as an electric motor, a controller, a battery, and an inverter. This controller is a component controller, and the electric motor is an actuator. The electric motor is controlled by the component controller to convert the electrical energy in the battery into mechanical energy, drive the motor to rotate, and generate a driving force. Sensors are used to measure the working status and working data of components. For example, photoelectric sensors are used to measure the speed of electric motors. Ultimately, the component controller collects the working status and working parameters of each component, including the working status and working parameters of the component controller itself, as well as the working status and working parameters of sensors and actuators. This enables component-level data collection, provides basic airborne operating data for subsequent health assessments, and determines the current airborne health status based on the operating status of the component.

[0041] In some optional embodiments, in order to comprehensively control various components, a regional controller is pre-deployed on the electric aircraft, and the regional controller is connected to the component controllers with strong functional correlation, so that different regional-level control systems are composed of components with strong functionality, such as the power system, flight control system, automatic driving system, communication system, etc. of the electric aircraft. Taking the power system as an example, it includes component-level electric drive, electronic control and other systems, and the mutual cooperation between the component-level control systems provides power for the electric aircraft to support the take-off, flight and landing of the electric aircraft.

[0042] In some optional embodiments, in order to comprehensively control the electric aircraft, a whole-machine controller is pre-deployed on the electric aircraft and connected to each regional controller. It can also be directly connected to the component controller to form a whole-machine control system for unified management of each regional-level control system and some component controllers to ensure the normal operation of the electric aircraft.

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

[0044] In some optional embodiments, the component-level subsystem 101 includes: component controllers, actuators, and sensors interconnected via input and output interfaces and wiring harnesses, such as Figure 3 The component controllers, actuators and sensors in the control systems of electric drive, electric control, thermal management, navigation or instrumentation shown in the figure mainly perform the following functions: data acquisition, i.e., the acquisition and processing of the parameters of the connected sensors and actuators; reporting of working state parameters and working mode information; and fault detection of the components and their connected components with the help of sensors, diagnostic detection, models, etc., and support for fault isolation. The component-level subsystem supports the data interface of the fault diagnosis and health management functions of the regional-level subsystem. Each component controller generates a periodic health status message (PHSM) based on the collected information and directly submits it to the regional controller in the middle layer.

[0045] In some optional implementations, the regional subsystem 102 in the embodiment of the present invention includes a regional controller connected to component controllers with strong functional relevance, such as Figure 3The power system, flight control system, autopilot system, communication system, low-voltage electrical system or display control system composed of different component control systems shown in the figure are used to perform regional health assessment according to the periodic health status message uploaded by the component controller, obtain the corresponding fault level and redundancy of each region, and generate the corresponding periodic health status message. The regional controller mainly has the functions of signal processing, information fusion and regional inference engine, and is a real-time processing unit that continuously monitors the operating status of the corresponding component-level control system of the electric aircraft. The regional controller is an interface unit connecting the whole-machine-level health management system and the component-level subsystem. The main functions of the regional-level subsystem are as follows: confirm fault reports, filter false alarms and evaluate intermittent faults; use the correlation information across the component-level control system and use the reasoning model to achieve enhanced fault detection and isolation; predict impending hardware failures (limited prediction cases); support the generation, integration and management of alarm information; redundancy management, judgment and switching. Among them, the reasoning model is deployed in the regional controller, which is deployed in the regional controller after model verification and parameter optimization on the component bench. It is a conventional technical means in this field and will not be repeated here. Redundancy management, judgment and switching means that the regional controller on the electric aircraft can switch the current control components. For example, if the flight control system has 3 redundancy, if the currently running flight control system fails, the flight control can switch the control to another set of flight control for control. This is also a conventional technical means in this field and will not be described in detail 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, achieving regional-level fault diagnosis, fault confirmation (filtering false alarms and evaluating intermittent faults) and accurate fault location (locating inside the component-level control system), classifying confirmed faults according to severity, and making selective reports to the whole machine controller in a timely manner. Among them, feature extraction, analysis and multi-source information fusion are for a certain type of fault, selecting relevant data for data extraction and feature extraction, so as to confirm the cause of the fault and reduce the risk of fault. For example, for speed fluctuations, data such as throttle, motor voltage, motor current and its rate of change can be extracted, which is only an example and is not limited to this.

[0046] In some optional implementations, the whole machine level subsystem 103 includes: a whole machine controller, connected to the component controller and the regional controller, for performing whole machine level health assessment according to the periodic health status message uploaded by the component controller and the periodic health status message uploaded by the regional controller, determining the health level of the whole machine, and generating corresponding periodic health status messages. The whole machine level subsystem combines intelligent information fusion, management, and transmission capabilities, manages and controls the data distributed in the regional controllers or component controllers of the whole machine, processes the fault diagnosis and health management data through the onboard fault reasoning and monitoring model, realizes the highest level of comprehensive functions of onboard fault diagnosis and health management, and serves as an interface between the onboard system of onboard fault diagnosis and health management and the ground system of ground fault diagnosis and health management. The main functions performed by the whole machine level subsystem are as follows: perform cross-regional and cross-component fault data integration; whole machine level fault online monitoring and partial fault prediction; manage the processing priority of onboard system fault diagnosis and health management; manage the information release and transmission of onboard system fault diagnosis and health management. The present invention realizes fault diagnosis and health management of the onboard terminal through the mutual cooperation of controllers at various levels.

[0047] In some optional implementations, the embodiment of the present invention also deploys a ground system 200 that matches the airborne system 100, wherein the ground system 200 can be deployed in the cloud. The ground system 200 is called a ground system in order to distinguish it from the airborne system carried by the airborne end. The ground system 200 communicates with the whole-machine subsystem 103 of the airborne system 100 through wireless communication technology, and receives the periodic health status message uploaded by the whole-machine controller. At this time, the uploaded periodic health status message includes the periodic health status message generated by each level. The ground system 200 performs a comprehensive health assessment again based on all periodic health status messages, realizes whole-machine fault status monitoring, status monitoring alarm, whole-machine health status assessment, key and important component fault prediction, diagnostic data management, life prediction of time-life parts, maintenance auxiliary decision-making, etc., and is deployed with maintenance databases, diagnostic databases, fault case libraries, etc., to provide important support for the life cycle management of subsequent electric aircraft operations. Specifically, the ground system transmits data with the whole machine controller through the air-to-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 off status, power battery power, actual total output power, minimum voltage, maximum current, minimum single cell voltage, maximum power battery temperature, minimum power battery temperature, power battery charging status, DCDC (direct current-to-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 machine 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 realize the functions of instant alarm and early warning. Based on the capabilities of the ground system 200, the operating status and historical status of the electric aircraft can be queried in real time. Based on the health assessment model of the data platform, the health status of the whole aircraft can be evaluated according to the operating status information, fault information and PHSM information of each level uploaded by the electric aircraft. Based on the existing historical data and the real-time uploaded data, the fault prediction model can be used to predict the failure of key parts in real time, give early warning, and make maintenance inspection suggestions in advance. For confirmed faults, the powerful data storage and computing capabilities of the ground system 200 are used to infer and generate maintenance auxiliary suggestions based on the maintenance database, diagnosis database, fault case library, professional knowledge library and other information. The ground system 200 is provided with a human-machine interaction interface to intuitively display the above-mentioned various health assessment results, alarm signals and early warning signals to the operator, so that the operator can quickly understand and grasp the current operation status of the airborne terminal, and take necessary measures for maintenance or repair.The present invention generates alarm information according to the analysis results, notifies the operating personnel to repair the airborne terminal in time, etc., to avoid further expansion of the fault; at the same time, based on the fault prediction model, it gives early warning of impending faults, reminds the operating personnel to maintain the airborne terminal in advance, etc., to avoid the occurrence of faults. Therefore, through alarms and warnings, more efficient maintenance management can be provided for the airborne terminal, the safety, reliability and availability of the airborne terminal can be improved, the service life of the airborne terminal can be extended, and the maintenance cost within the life cycle can be reduced.

[0048] In some optional implementations, each level controller sends a periodic health status message PHSM according to its own characteristics, wherein the message is a data unit exchanged and transmitted in the network, and the message contains complete data information and control information to be sent from the source end to the destination end, etc., and its length is very inconsistent, and the length is unlimited and variable, which can ensure the integrity and accuracy of the data, and the message can be transmitted in different network layers, adapting to different network environments and requirements, making full use of network resources, and there is no need to establish a connection between the layers, and the message can be sent periodically, with high reliability and flexibility. During the transmission process, the message can be decomposed into multiple data packets, which are then encapsulated into frames for transmission, and the application scenarios are wide. The information contained in the PHSM of the embodiment of the present invention is as follows: node fault level, low voltage power supply status, CAN interface communication status, Ethernet communication status, network management, external storage space usage, node loss status, fault code status signal, Counter (message counter) and Checksum (checksum) signal, which are only used as examples and are not limited to this. Among them, Counter is a 4-bit message counter, which is located in the data segment of the CAN message. Its main function is to ensure that there is no frame loss during the message transmission process. Every time a message is sent, the value of the counter will increase by 1, and it will continue to cycle from 0 to 15. If the receiver finds that the counter is discontinuous or the first and last values ​​are incorrect, it will be considered that a frame loss has occurred and report the corresponding fault code 1. Checksum is a simple and efficient data verification method. The sender obtains a Checksum value through a prescribed calculation method and adds it to the data segment of the CAN message and sends it out. After receiving the message, the receiver recalculates the Checksum value using the same calculation method and compares it with the received Checksum value. If the two are consistent, it means that the data is correct; otherwise, it is considered that the data is wrong. The periodic health status message can take a variety of forms and can be sent through different bus types. The information contained can be increased or decreased according to actual needs. The messages sent by each controller need to be sent on at least two channels for the controller of the multi-channel bus.

[0049] In some optional implementations, it can be seen from the functional descriptions of the above-mentioned subsystems at each level that the embodiments of the present invention divide the fault levels in the component-level subsystem 101 and the area-level subsystem 102, and each controller defines the fault level according to its own hardware working status and the functions it performs on the whole machine. The fault levels are generally divided into five levels: normal, warning, level 1 general fault, level 2, level 3 general functional fault, level 4 and level 5 serious fault. This is for example only and is not limited to this.

[0050] In some optional implementations, in the whole machine subsystem 103, the embodiment of the present invention determines the health of the whole machine through comprehensive analysis, and the determination process includes: obtaining the weights Pi of predetermined components and preset areas, and determining the health score Phi of the components or areas according to the periodic health status message. When determining the health score of the area, the redundancy of the area must also be considered. The sum of the weights of each component or area is 1. The health score is summarized according to different hardware failures and functional failures, and the full score is 100 points. Therefore, the weight and health score are weighted and summed to obtain the health of the whole machine, that is:

[0051] Machine health = ∑(Pi*Phi)

[0052] Among them, if the calculated whole machine health is less than 70, it means that the electric aircraft currently has a serious fault and may have a crash risk; if the whole machine health is between 70-80, it means that the electric aircraft is at fault at this time and needs to land nearby for maintenance to prevent danger; if the whole machine health is between 80-90, it means that the electric aircraft has a general fault at this time and needs to be repaired as soon as possible; if the whole machine health is between 90-100, it means that the electric aircraft can operate normally without major safety impact. Therefore, the embodiment of the present invention can combine multiple indicators of each system for overall analysis, comprehensively reflect the health of the current airborne terminal, and provide operators with accurate fault conditions, so that operators can take appropriate measures according to the health level to improve the safety and availability of the airborne terminal.

[0053] In some optional implementations, the division of regional subsystems can be skipped between the various levels of subsystems in the embodiments of the present invention, and the component-level controller can directly report the data to the vehicle-level controller. The health management of the whole-machine-level subsystem can be monitored and distributed separately on the airborne end and the ground end at the same time. It can be flexibly configured based on the complementary characteristics of the two, according to the characteristics of strong airborne real-time performance and limited computing power, but poor real-time performance and strong computing power of the server.

[0054] In some optional implementations, the component level, regional level, and whole machine level in the embodiments of the present invention can be combined according to the actual function distribution situation, and can support direct component level to whole machine level, or remove the component level and directly go from regional level to whole machine level, and flexibly handle according to the actual operation situation. Based on the concept of three-level stratification, the health management evaluation algorithm used in the health management system can be based on machine learning reasoning classification based on existing cases or data in the field to evaluate the impact of faults. In addition, an expert system can be introduced in the ground service judgment at the same time, and the health status of the whole machine or parts can be judged through comprehensive processing of experts or knowledge bases. This is only an example and is not limited to this.

[0055] In some optional implementations, the embodiments of the present invention utilize existing controller modules that are arranged in different places on the fuselage to perform different functions and existing sensors and actuator equipment of the electric aircraft, and aggregate them to the whole-machine regional gateway module through a variety of bus transmission methods, and then upload the processed data to the cloud through a wireless communication link; at the same time, it supports fault monitoring, fault prediction and whole-machine health assessment on the electric aircraft.

[0056] The health management system provided by the embodiment of the present invention divides the recording system into preset levels according to the functional characteristics of the controller deployed on the airborne end, performs hierarchical data collection and health assessment on the airborne end, and the ground system connected to the airborne system receives the health assessment results of the recording system and performs a comprehensive health assessment. The present invention uses the controller of the airborne end to deploy an airborne health management system including different levels, and matches the ground health management system, which can avoid the need for additional data collection and data analysis and processing systems on the airborne end, save costs, and reduce the weight of the airborne end. At the same time, the complex comprehensive health assessment performed by the ground system can ensure 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 of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0058] In this embodiment, a health management method is provided. Figure 2 The health management system shown performs health assessment on the airborne terminal. Figure 5 is a flow chart of a health management method according to an embodiment of the present invention. Figure 5 As shown, the process includes the following steps:

[0059] Step S501: After the airborne end is powered on, the component-level subsystem, the regional-level subsystem and the whole-machine-level subsystem complete system initialization.

[0060] Step S502: Each component controller collects working status and working parameters, and sends out a first cycle health status message.

[0061] Step S503, the regional controller performs a regional health assessment based on the first cycle health status message, determines the health management status of each region, obtains the second fault level and redundancy of each region, and sends a second cycle health status message.

[0062] Step S504: the whole machine controller performs a whole machine level health assessment according to the first cycle health status message and the second cycle health status message, determines the health level of the whole machine, and generates a third cycle health status message.

[0063] 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 an alarm signal and / or a warning signal based on the comprehensive health assessment result.

[0064] Specifically, in the embodiment of the present invention, each step of the method is performed based on the above-mentioned health management system embodiment and preferred implementation mode, and has the same effect as the health management system, and will not be repeated here for what has been explained.

[0065] The embodiment of the present invention further provides an electric aircraft, comprising the above Figure 1 , Figure 2 or Figure 3 The onboard system in the health management system shown in the figure performs the above Figure 5 The health management method has the same effect as the health management system and will not be repeated 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 with different carriers and different bus types, such as multi-rotor or fixed-wing electric aircraft, automobiles or other electromechanical equipment, etc., which are not limited here. The specific construction situation is determined according to the actual situation of the carrier or the electronic and electrical architecture, and the collected data related to health management is also determined according to the operation of the carrier or the electronic and electrical architecture.

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

Claims

1. A health management system, characterized in that: The system comprises: An airborne system, which divides the airborne system into preset levels according to the functional characteristics of the controller deployed by the airborne terminal, for performing hierarchical data collection and health assessment on the airborne terminal; The ground system is connected to the airborne system and is used to receive the health assessment result of the airborne system and perform a comprehensive health assessment.

2. The system according to claim 1, characterized in that The airborne system includes: component-level subsystem, regional-level subsystem and whole-machine-level subsystem, wherein: The component-level subsystem includes: components interconnected through input and output interfaces and wiring harnesses, the components including: component controllers, actuators, and sensors; The component controller is used to obtain the working status and working parameters of the component, perform component-level health assessment according to the working status and the working parameters, determine the first fault level of the component, and generate a first periodic health status message.

3. The system according to claim 2, characterized in that The regional subsystem includes: a regional controller; The regional controller pre-deploys an inference model and is connected to at least one of the component controllers to perform a regional health assessment based on the first periodic health status message uploaded by the component controller, obtain a second fault level and redundancy of a preset area, and generate a second periodic health status message.

4. The system according to claim 3, characterized in that The whole machine level subsystem includes: a whole machine controller; The whole machine controller is connected to the component controller and the regional controller, and is used to perform a whole machine-level health assessment based on the first cycle health status message uploaded by the component controller and the second cycle health status message uploaded by the regional controller, determine the health level of the whole machine, and generate a third cycle health status message.

5. The system according to claim 4, characterized in that The ground system pre-deploys a fault prediction model and a health database, which are connected to the whole machine controller, and 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 whole machine controller, and generate an alarm signal and / or an early warning signal based on the comprehensive health assessment result.

6. The system according to claim 4, characterized in that The performing a whole-machine-level health assessment according to the first-cycle health status message uploaded by the component controller and the second-cycle health status message uploaded by the zone controller to determine the health level of the whole machine includes: Obtaining predetermined weights of the component and the preset area; Determine the health score of the component according to the first fault level in the first periodic health status message, and determine the health score of the preset area according to the second fault level and the redundancy in the second periodic health status message; The health level of the whole machine is obtained by performing a weighted sum based on the weight and the health level score.

7. The system according to claim 5, characterized in that The ground system also includes: a human-computer interaction interface for displaying the comprehensive health assessment result, the alarm signal and / or the early warning signal.

8. The system according to claim 3, characterized in that The regional subsystem further includes: switching the regional controller according to the second fault level and the redundancy.

9. A health management method, characterized in that: A health assessment is performed on the onboard terminal based on the health management system described in any one of claims 1 to 6.

10. An electric aircraft, characterized in that: include: An onboard system in a health management system as claimed in any one of claims 1 to 6.

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