A method of maintaining an eVTOL electric drive system and related apparatus

Abstract

The application discloses a maintenance method of an eVTOL electric drive system and related equipment, and relates to the technical field of equipment maintenance. The method comprises the following steps: acquiring operation data of a plurality of electric drive systems of an electric vertical take-off and landing aircraft (eVTOL); determining a maintenance time window of each electric drive system based on the operation data; acquiring voyage task information and maintenance resource information of the eVTOL; and based on the maintenance time window, combining and optimizing the maintenance time of the plurality of electric drive systems with the voyage task information and the maintenance resource information as constraints, to generate a cooperative maintenance plan of the plurality of electric drive systems. The application can reduce the number of shutdowns, improve the availability of the aircraft, and reduce the occupation of maintenance resources by cooperatively planning the maintenance time of the plurality of electric drive systems.

Description

Technical Field

[0001] This application relates to the field of equipment maintenance technology, and in particular to a maintenance method and related equipment for an eVTOL electric drive system. Background Technology

[0002] With the development of urban air mobility, eVTOL (Electric Vertical Take-off and Landing) aircraft, due to their distributed electric propulsion architecture, typically employ multiple independent electric drive systems to provide lift and thrust. The different installation locations of these electric drive systems on the aircraft, along with variations in load, heat dissipation conditions, and aerodynamic environments, result in different actual degradation processes and require maintenance at different times within the operational cycle.

[0003] In existing technologies, maintenance decisions for electric drive systems typically employ an independent judgment method based on state thresholds. This involves real-time collection of operating parameters for each electric drive system using sensors, and triggering a maintenance alarm when any parameter exceeds a preset threshold. However, this method of independently determining maintenance needs for a single electric drive system fails to consider the multiple electric drive systems on the aircraft as a whole. This results in asynchronous triggering of maintenance requirements for each electric drive system, leading to frequent groundings, increased unplanned downtime, reduced operational availability, and higher overall maintenance costs. Therefore, a maintenance method for eVTOL electric drive systems is urgently needed to address the aforementioned technical problems. Summary of the Invention

[0004] The summary section introduces a series of simplified concepts, which will be further explained in detail in the detailed description section. This summary section is not intended to limit the key and essential technical features of the claimed technical solutions, nor is it intended to determine the scope of protection of the claimed technical solutions.

[0005] In a first aspect, this application proposes a maintenance method for an eVTOL electric drive system, comprising: Acquire operational data from multiple electric drive systems on an electric vertical takeoff and landing (eVTOL) aircraft; Based on the aforementioned operational data, a maintenance time window is determined for each electric drive system; Obtain eVTOL flight mission information and maintenance resource information; Based on the maintenance time window, and constrained by the voyage mission information and the maintenance resource information, the maintenance timing of multiple electric drive systems is combined and optimized to generate a collaborative maintenance plan for the multiple electric drive systems.

[0006] In some implementations, determining the maintenance time window for each electric drive system based on the operational data includes: For each electric drive system, a corresponding degradation rate assessment model is established based on the operating data of the electric drive system, wherein the degradation rate assessment model is used to characterize the difference in degradation rate of the electric drive system under different operating conditions. For each electric drive system, the degradation trend curve of the electric drive system is determined according to the degradation rate evaluation model corresponding to the electric drive system. For each electric drive system, a maintenance time window is determined based on the degradation trend curve of the electric drive system and a preset maintenance threshold, wherein the maintenance time window includes the earliest maintenance start time and the latest maintenance start time.

[0007] In some embodiments, establishing a corresponding degradation rate assessment model based on the operating data of the electric drive system includes: Historical operating conditions features are extracted from the operating data of the electric drive system. These historical operating conditions features are used to characterize the degree of accumulation of operating stress experienced by the electric drive system during historical operation. Based on the historical characteristics of the operating conditions, the degradation rate mapping relationship of the electric drive system under different operating conditions is determined. The degradation rate mapping relationship is used to characterize the correspondence between the stress accumulation degree and the degradation rate under different operating conditions. Based on the degradation rate mapping relationship, a degradation rate evaluation model for the electric drive system is established.

[0008] In some implementations, the flight mission information includes the eVTOL's mission execution time window and ground parking time window within a preset planned period. The mission execution time window is the period during which the eVTOL performs flight missions, and the ground parking time window is the period during which the eVTOL is parked on the ground. The maintenance resource information includes the available time periods for maintenance personnel and the inventory status of maintenance spare parts within the preset planning period. The available time periods are the periods when maintenance personnel are capable of performing operations, and the inventory status is the available quantity of maintenance spare parts at each time point.

[0009] In some implementations, the step of combining and optimizing the maintenance timing of multiple electric drive systems based on the maintenance time window, constrained by the voyage mission information and the maintenance resource information, to generate a collaborative maintenance plan for the multiple electric drive systems includes: Based on the maintenance time window of each electric drive system, as well as the voyage mission information and the maintenance resource information, a maintenance timing combination optimization model is constructed with the goal of minimizing maintenance resource occupancy. The maintenance timing combination optimization model is solved to obtain a coordinated maintenance plan for the multiple electric drive systems.

[0010] In some implementations, the step of constructing a maintenance timing combination optimization model with the objective of minimizing maintenance resource occupancy, based on the maintenance time window of each electric drive system, the voyage mission information, and the maintenance resource information, includes: The variables to be solved in the maintenance timing combination optimization model are determined, wherein the variables to be solved include the maintenance period of each electric drive system; Determine the constraints of the maintenance timing combination optimization model, wherein the constraints include: The maintenance period for each electric drive system falls within the corresponding maintenance time window for that electric drive system. The maintenance period for each electric drive system falls within the ground downtime window. Within the same ground downtime window, the sum of maintenance hours corresponding to maintenance periods for different electric drive systems shall not exceed the available time of maintenance personnel corresponding to that ground downtime window; Within the same ground downtime window, the sum of the required number of spare parts for maintenance during different electric drive system maintenance periods shall not exceed the available number of spare parts for maintenance during that ground downtime window. Determine the objective function of the maintenance timing combination optimization model, wherein the objective function is used to calculate the maintenance resource occupancy, and the maintenance resource occupancy is positively correlated with the number of downtimes.

[0011] In some implementations, solving the optimization model for the maintenance timing combination to obtain a coordinated maintenance plan for the multiple electric drive systems includes: Based on the maintenance time window of each electric drive system and the ground downtime time window, a set of candidate maintenance periods is generated for each electric drive system, wherein the set of candidate maintenance periods includes multiple candidate maintenance periods; For each electric drive system, a candidate maintenance period is selected from the set of candidate maintenance periods for that electric drive system, and all the selected candidate maintenance periods for electric drive systems are combined into a maintenance timing combination scheme. Iterate through all combinations of the candidate maintenance time periods for all electric drive systems to generate multiple maintenance timing combination schemes; From the multiple maintenance timing combinations, select the maintenance timing combination that satisfies the constraints; The maintenance resource occupancy for each maintenance timing combination scheme is calculated based on the objective function. The combination of maintenance timings that minimizes the amount of maintenance resources required is determined as the collaborative maintenance plan.

[0012] Secondly, this application proposes a maintenance device for an eVTOL electric drive system, comprising: The operation data acquisition unit is used to acquire the operation data of multiple electric drive systems on the electric vertical takeoff and landing (eVTOL) aircraft. A time window determination unit is used to determine the maintenance time window for each electric drive system based on the operating data. The constraint information determination unit is used to acquire eVTOL flight mission information and maintenance resource information; The maintenance plan determination unit is used to combine and optimize the maintenance timing of multiple electric drive systems based on the maintenance time window and constrained by the voyage mission information and the maintenance resource information, so as to generate a collaborative maintenance plan for the multiple electric drive systems.

[0013] Thirdly, an electronic device includes: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program stored in the memory to implement the steps of the maintenance method for the eVTOL electric drive system of any one of the first aspects.

[0014] Fourthly, this application also proposes a computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements the steps of the maintenance method for the eVTOL electric drive system of any one of the first aspects.

[0015] In summary, the maintenance method for the eVTOL electric drive system provided in this application acquires operational data from multiple electric drive systems on the electric vertical takeoff and landing (eVTOL) aircraft. By collecting operational data from multiple electric drive systems, it simultaneously grasps the differences in the status of each electric drive system under actual operating conditions, rather than judging the health status of a single system. Based on the operational data, a maintenance time window is determined for each electric drive system. This maintenance time window provides the time range within which maintenance can be scheduled for each electric drive system without functional failure, ensuring that the maintenance timing for each electric drive system falls within this range. Furthermore, it acquires flight mission information and maintenance resource information for the eVTOL aircraft, incorporating the aircraft's future flight mission arrangements and the availability of resources such as maintenance personnel and spare parts into the decision-making process, ensuring that the maintenance plan matches the actual operation and maintenance support conditions of the aircraft. Based on the maintenance time windows of each electric drive system and constrained by flight mission information and maintenance resource information, the maintenance timing of multiple electric drive systems is combined and optimized. Multiple maintenance needs that were originally triggered separately on the time axis are centralized into the same optimization framework for arrangement. By coordinating and adjusting the execution timing of each maintenance task, a collaborative maintenance plan for multiple electric drive systems is generated. This merges multiple scattered maintenance shutdowns into fewer planned shutdowns, reducing the number of unplanned downtimes caused by maintenance, thereby improving the operational availability of the aircraft and reducing the overall maintenance cost. Attached Figure Description

[0016] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit this specification. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 This is a schematic diagram of the maintenance method for the eVTOL electric drive system provided in the embodiments of this application; Figure 2 This is a schematic diagram of the maintenance device structure for the eVTOL electric drive system provided in the embodiments of this application; Figure 3 A schematic diagram of the maintenance electronic equipment for the eVTOL electric drive system provided in the embodiments of this application. Detailed Implementation

[0017] The terms "first," "second," "third," "fourth," etc. (if present) in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments described herein can be implemented in orders other than those illustrated or described herein. Furthermore, "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that includes a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus. The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them.

[0018] This application relates to the field of equipment maintenance technology, and more particularly to maintenance methods for the electric drive system of eVTOL. With the rapid development of UAM (Urban Air Mobility), eVTOL aircraft, as core vehicles, are evolving from conceptual design to commercial operation. eVTOL aircraft typically employ a distributed electric propulsion architecture, which configures multiple independent EDS (Electric Drive Systems) to provide lift and thrust. Each EDS is an electromechanical unit including an electric motor, power inverter, controller, cooling components, and transmission components. Unlike traditional aircraft with centralized power architectures, the multiple EDS in an eVTOL exhibit significant differences in operating conditions due to variations in installation location, load conditions, heat dissipation environment, and aerodynamic loads. For example, the EDS located on the front windward side has better heat dissipation but experiences greater aerodynamic fluctuations, while the rear EDS has poorer heat dissipation conditions, and the junction temperature fluctuations of the power semiconductor devices in EDS that frequently perform maneuvers are severe. These differences result in varying actual degradation rates (such as bearing wear, winding insulation aging, IGBT module fatigue, etc.) for each EDS, and the optimal time for maintenance for each is also discretely distributed at different times within the operating cycle.

[0019] To address the aforementioned issues, this application proposes a maintenance method and related equipment for an eVTOL electric drive system, which coordinates and optimizes the maintenance timing of multiple electric drive systems on an aircraft. In a specific application scenario, after an eVTOL aircraft completes a certain period of operation, multi-dimensional operational data accumulated by all electric drive systems on the aircraft during the past operating period is acquired. Based on the actual degradation state of each system, its maintenance time window is determined, i.e., the flexible time interval within which maintenance can be scheduled for each system without functional failure. Simultaneously, flight mission information and maintenance resource information of the aircraft within a preset planned time period are acquired to determine which time windows in the future will be used for flight missions, which time windows will be ground-based, and the available time slots for maintenance personnel and the availability of spare parts. Using the maintenance time window of each electric drive system, flight mission arrangement and maintenance resource availability as constraints, and aiming to minimize the number of downtimes caused by maintenance, the maintenance timing of multiple electric drive systems is planned, and a collaborative maintenance plan is determined to coordinate multiple maintenance tasks to be executed within the same downtime window. This reduces the number of unplanned downtimes caused by maintenance, improves the operational availability of the aircraft and reduces overall resource consumption.

[0020] To facilitate understanding of the technical solution of this application, several technical features involved in this application will be explained below.

[0021] The electric drive system in this application refers to an independent electric drive unit on an eVTOL aircraft used to provide lift or thrust. Each electric drive system typically consists of an electric motor, a power inverter, a controller, cooling components, and transmission components. On an eVTOL aircraft, the actual operating conditions of each electric drive system differ due to their different installation locations and the flight attitude control tasks they undertake, resulting in different degradation rates.

[0022] The maintenance time window in this application refers to the time interval within which maintenance operations can be performed on a specific electric drive system, determined based on its operating data and degradation trends, without the risk of functional failure. The maintenance time window includes the earliest and latest maintenance start times. The earliest maintenance start time is the earliest permissible time to begin maintenance operations on the electric drive system, and the latest maintenance start time is the latest permissible time to begin maintenance operations on the electric drive system. Starting maintenance operations at the latest maintenance start time ensures that all maintenance operations are completed before the latest maintenance completion time. Exceeding the latest maintenance start time will expose the system to the risk of functional failure.

[0023] The degradation rate assessment model in this application refers to an assessment model established based on historical operating data of electric drive systems to characterize the rate of health degradation of the system under different operating conditions. Since different electric drive systems have experienced different levels of stress from operating conditions such as long operating times at high temperatures and high torque output frequencies in the past, their degradation rate assessment models reflect the differences in degradation rates caused by these differences in operating conditions.

[0024] The operating condition history characteristics in this application refer to information extracted from the operating data of the electric drive system to characterize the degree of accumulated operating stress experienced by the system during historical operation, such as the proportion of high-temperature operation time, the frequency of high torque output, and the severity of current fluctuations. These operating condition history characteristics reflect the intensity of the workload the system has endured in past operation and are used to establish a differentiated degradation rate assessment model.

[0025] The degradation trend curve in this application refers to a predicted curve output by the degradation rate assessment model, used to describe the change of the health status index of the electric drive system over time. The degradation trend curve reflects the expected decline trajectory of the system's health status during future operation.

[0026] The flight mission information in this application refers to the flight mission arrangements of the eVTOL aircraft within a preset planned time period, including the mission execution time window and the ground parking time window. The mission execution time window is the period during which the aircraft performs flight missions, and the ground parking time window is the period during which the aircraft is parked on the ground and available for maintenance work.

[0027] The maintenance resource information in this application refers to the availability of maintenance resources within a preset planning period, including the available time slots for maintenance personnel and the inventory status of spare parts. The available time slots for maintenance personnel represent the time range within which maintenance personnel are capable of performing operations, and the inventory status represents the available quantity of various types of spare parts at each point in time.

[0028] The combinatorial optimization in this application refers to not determining the maintenance timing for each electric drive system individually, but rather treating the maintenance timing of multiple electric drive systems on the aircraft as a whole. Under the premise of considering their respective maintenance time windows, downtime windows caused by flight missions, and maintenance resource constraints, a set of coordinated maintenance execution schemes are sought to achieve the optimal global objective (such as minimizing maintenance resource consumption).

[0029] The collaborative maintenance plan in this application refers to a maintenance scheme output after optimizing the combination of maintenance times for multiple electric drive systems on an aircraft. The collaborative maintenance plan reduces the total number of downtimes by advancing or delaying the maintenance times of certain systems and concentrating them into the same or a few ground downtime windows for simultaneous execution.

[0030] The maintenance resource occupancy in this application refers to a comprehensive evaluation index of the maintenance resources occupied by a certain maintenance timing combination scheme. In this application, the maintenance resource occupancy is positively correlated with the number of downtimes. The fewer the number of downtimes, the smaller the maintenance resource occupancy. The optimization objective is to find the maintenance timing combination scheme that minimizes the maintenance resource occupancy.

[0031] The candidate maintenance period in this application refers to several alternative time periods that can be selected as actual maintenance periods, determined based on the intersection of the maintenance time window and the ground downtime windows of a specific electric drive system during the process of solving the collaborative maintenance plan. Each candidate maintenance period simultaneously satisfies the conditions of being within the maintenance time window of the system and within a certain ground downtime window.

[0032] The maintenance timing combination scheme in this application refers to selecting one candidate maintenance time period from the set of candidate maintenance time periods for each electric drive system, and combining all the selected maintenance time periods to form a complete maintenance schedule. Different selection methods correspond to different maintenance timing combination schemes. By traversing all possible combinations and selecting the scheme that satisfies all constraints and minimizes maintenance resource consumption, the final collaborative maintenance plan is obtained.

[0033] Please see Figure 1 This is a schematic flowchart of a maintenance method for an eVTOL electric drive system provided in an embodiment of this application, which may specifically include: S110: Acquire operational data of multiple electric drive systems on the electric vertical takeoff and landing (eVTOL) aircraft; For example, multi-dimensional information generated by each electric drive system during actual operation is collected. This information reflects the actual operating conditions of different electric drive systems due to differences in installation location, load conditions, and heat dissipation environment.

[0034] S120. Based on the operating data, determine the maintenance time window for each electric drive system; For example, for each electric drive system, a degradation rate assessment model is established based on its operating data to characterize the differences in degradation rates under different operating conditions. This model determines the degradation trend curve of the electric drive system. Then, combined with a preset maintenance threshold, the earliest and latest maintenance times for the electric drive system without functional failure are determined, thus obtaining the maintenance time window for the electric drive system. The maintenance time window for each electric drive system provides a flexible time interval within which maintenance can be scheduled.

[0035] S130: Obtain eVTOL flight mission information and maintenance resource information; For example, the time series of eVTOL missions within a preset planning period is obtained, marking the time windows when the aircraft is performing missions and the time windows when it is parked on the ground. Simultaneously, the available time slots for maintenance personnel and the available inventory of maintenance spare parts within this preset planning period are obtained. This information incorporates the constraints of the aircraft itself and maintenance conditions into the decision-making process, ensuring that the generated maintenance plan is matched with the aircraft's flight mission schedule and maintenance resources.

[0036] S140. Based on the maintenance time window and constrained by voyage mission information and maintenance resource information, the maintenance timing of multiple electric drive systems is combined and optimized to generate a collaborative maintenance plan for multiple electric drive systems.

[0037] For example, the maintenance time window of each electric drive system is used as the allowable range of maintenance opportunities for each system. The ground downtime window in the flight mission information and the personnel availability time and spare parts inventory in the maintenance resource information are used as constraints. The maintenance opportunities of multiple electric drive systems are coordinated as a whole to find the maintenance opportunity combination scheme that minimizes the total number of downtimes and generate a collaborative maintenance plan that concentrates multiple maintenance tasks into the same ground downtime window for execution.

[0038] In summary, the maintenance method for the eVTOL electric drive system provided in this application acquires operational data from multiple electric drive systems on the electric vertical takeoff and landing (eVTOL) aircraft. By collecting operational data from multiple electric drive systems, the method understands the differences in the state of each electric drive system under actual operating conditions, rather than judging the health status of a single system. Based on the operational data, a maintenance time window is determined for each electric drive system. This maintenance time window provides the time interval within which maintenance can be scheduled for each electric drive system without functional failure, ensuring that the maintenance opportunity for each electric drive system falls within the specified range. Furthermore, the method acquires flight mission information and maintenance resource information for the eVTOL aircraft, incorporating the aircraft's future flight mission arrangements and the availability of resources such as maintenance personnel and spare parts into the decision-making process, ensuring that the maintenance plan matches the actual operation and maintenance support conditions of the aircraft. Based on the maintenance time windows of each electric drive system and constrained by flight mission information and maintenance resource information, the maintenance timing of multiple electric drive systems is combined and optimized. Multiple maintenance needs that were originally triggered separately on the time axis are centralized into the same optimization framework for planning. By coordinating and adjusting the execution timing of each maintenance task, a collaborative maintenance plan for multiple electric drive systems is generated. This merges multiple scattered maintenance shutdowns into fewer planned shutdowns, reducing the number of unplanned downtimes caused by maintenance, thereby improving the operational availability of the aircraft and reducing the overall maintenance cost.

[0039] In some instances, maintenance time windows for each electric drive system are determined based on operational data, including: For each electric drive system, a corresponding degradation rate assessment model is established based on the operating data of the electric drive system, including: Historical operating conditions features are extracted from the operating data of the electric drive system. These historical operating conditions features are used to characterize the degree of accumulation of operating stress experienced by the electric drive system during historical operation. Based on the historical characteristics of the operating conditions, the degradation rate mapping relationship of the electric drive system under different operating conditions is determined. The degradation rate mapping relationship is used to characterize the correspondence between the stress accumulation degree and the degradation rate under different operating conditions. Based on the degradation rate mapping relationship, a degradation rate evaluation model for electric drive systems is established. The degradation rate evaluation model is used to characterize the differences in degradation rate of electric drive systems under different operating conditions. For each electric drive system, the degradation trend curve of the electric drive system is determined according to the degradation rate assessment model corresponding to the electric drive system. For each electric drive system, a maintenance time window is determined based on the degradation trend curve of the electric drive system and a preset maintenance threshold. The maintenance time window includes the earliest maintenance start time and the latest maintenance start time.

[0040] For example, for each electric drive system, historical operating characteristics are extracted from the operating data accumulated during the system's historical operation, and a degradation rate assessment model corresponding to the electric drive system is established based on these historical operating characteristics. The operating data includes the three-phase current waveforms and motor winding temperatures recorded by the electric drive system in different flight sorties.

[0041] The historical operating characteristics extracted from the above operating data include high-temperature operating duration, high torque output frequency, and severe current fluctuation. The high-temperature operating duration characterizes the cumulative degree of high temperature conditions experienced by the electric drive system during the historical operating period. The high torque output frequency characterizes the frequency with which the electric drive system was subjected to high mechanical loads during the historical operating period. The severe current fluctuation characterizes the cumulative degree of electrical stress fluctuation experienced by the electric drive system during the historical operating period.

[0042] In one optional implementation, the high-temperature operating duration is the cumulative duration during which the motor winding temperature of the electric drive system exceeds a preset temperature threshold; the high torque output frequency is the cumulative number of times the output torque of the electric drive system exceeds a preset torque threshold during its historical operation; the high torque output frequency is calculated from three-phase current waveform data, that is, the q-axis current component is obtained by coordinate transformation based on the three-phase current waveform data, and the product of the q-axis current component and the torque constant is taken as the output torque; the severity of current fluctuation is the cumulative number of times during the historical operation of the electric drive system that the ratio of the instantaneous value of the three-phase current waveform to the rated current exceeds a preset fluctuation multiple.

[0043] After extracting historical operating characteristics such as high-temperature operating duration, high torque output frequency, and the severity of current fluctuations, the degradation rate mapping relationship of the electric drive system under different operating conditions was determined based on these historical characteristics. The degradation rate mapping relationship characterizes the correspondence between the degree of stress accumulation and the degradation rate under different operating conditions. Specifically, the longer the high-temperature operating duration, the greater the acceleration of the winding insulation aging rate relative to its baseline value; the higher the high torque output frequency, the greater the acceleration of the bearing wear rate relative to its baseline value; and the higher the severity of current fluctuations, the greater the acceleration of the power semiconductor device fatigue rate relative to its baseline value. This correspondence maps the degree of stress accumulation reflected by the historical operating characteristics to an accelerating trend in the degradation rate.

[0044] The establishment of the degradation rate mapping relationship can be implemented in different ways depending on the actual application scenario. In one optional implementation method, the degradation rate mapping relationship is established using a hybrid approach based on physical models and data-driven methods. Specifically, based on the physical model of the failure mechanism of key components of the electric drive system, the baseline values ​​of degradation rates for each failure mode, such as bearing wear, winding insulation aging, and power semiconductor device fatigue, are determined under standard operating conditions. The baseline values ​​can be obtained through accelerated life testing of components on a bench or historical statistical data of the same model of product. Then, the actual degradation data recorded in the historical maintenance records of the same model of electric drive system are used as training samples. Regression analysis is used to determine the acceleration coefficients of high-temperature operating time on winding insulation aging rate, high torque output frequency on bearing wear rate, and the degree of current fluctuation on power semiconductor device fatigue rate, thus forming a mapping relationship from historical operating conditions to degradation acceleration coefficients.

[0045] In another alternative implementation, the degradation rate mapping is established using a deep learning model. Suitable deep learning models include multilayer perceptrons, long short-term memory networks, or convolutional neural networks. The selected deep learning model is trained using high-temperature operating duration, high torque output frequency, and the severity of current fluctuations as input features, and the actual health degradation rate of the electric drive system over historical periods as the output label. After training, the model outputs a corresponding degradation rate prediction based on the input historical operating conditions, learning the nonlinear mapping relationship between the degree of accumulated stress and the degradation rate.

[0046] After determining the degradation rate mapping relationship using any of the above methods, a degradation rate assessment model for the electric drive system is established based on this mapping relationship. The degradation rate assessment model takes the high-temperature operating duration, high torque output frequency, and severe current fluctuations of the electric drive system as inputs. Through the established degradation rate mapping relationship, these historical operating conditions are converted into degradation acceleration coefficients. When using a hybrid approach combining physical models and data-driven methods, the degradation acceleration coefficients are multiplied by the degradation rate baseline values ​​for each failure mode to obtain the health status decay rate of the electric drive system in subsequent operation. When using a deep learning model, the health status decay rate is directly output by the deep neural network model. The health status decay rate reflects the personalized degradation process of the electric drive system due to its own operating history. Electric drive systems with longer high-temperature operating durations and higher high torque output frequencies exhibit faster health status decay rates, while electric drive systems with lower levels of historical operating conditions exhibit slower health status decay rates. The health condition decay rate is used as the output of the degradation rate assessment model to generate the degradation trend curve of the electric drive system. The decay slope of the degradation trend curve is determined by the health condition decay rate, and the differences in degradation rate caused by the differences in installation location, load conditions and heat dissipation environment of each electric drive system are reflected in the maintenance time window.

[0047] After establishing a degradation rate assessment model and outputting the health status decay rate of the electric drive system, a degradation trend curve for the electric drive system is determined based on the corresponding degradation rate assessment model. The degradation trend curve, with operating time as the horizontal axis and the health status index as the vertical axis, describes the predicted trajectory of the electric drive system's health status index changing over operating time. The starting point of the degradation trend curve is the health status index of the electric drive system at the current moment, determined based on the health status assessment result at the time of the most recent operating data acquisition. The decay slope of the degradation trend curve is determined by the health status decay rate output by the degradation rate assessment model; that is, the faster the health status decay rate, the greater the slope of the health status index decreasing over operating time; the slower the health status decay rate, the smaller the slope of the health status index decreasing over operating time. Using the current health status index as the starting point of the degradation trend curve, and extending forward along the time axis according to the health status decay rate, a predicted trajectory of the health status index decay over time is generated. This trajectory reflects the expected path of change of the health status index over time, assuming the electric drive system continues to operate under its current conditions without maintenance.

[0048] It should be noted that the health status index is the ratio of the current remaining usable life of the electric drive system to its rated total life, or the ratio of the current performance level of the electric drive system to its performance level when it was brand new. A health status index of 100% indicates that the system is in brand new condition, with excellent performance and no degradation; a health status index of 0% indicates that the system has completely failed or has reached the limit state that requires replacement; the process of the health status index decaying from 100% to 0% reflects the gradual degradation of the system during operation.

[0049] After determining the degradation trend curve, the maintenance time window for the electric drive system is determined based on the degradation trend curve and the preset maintenance threshold. The preset maintenance threshold is a pre-set lower limit value of the health status index. When the health status index of the electric drive system drops to the preset maintenance threshold along the degradation trend curve, it indicates that the electric drive system has reached a critical state requiring maintenance. If it continues to operate without maintenance, it will face the risk of functional failure.

[0050] The moment when the health status index on the degradation trend curve first drops to the preset maintenance threshold is defined as the latest maintenance completion time for the electric drive system. The latest maintenance completion time indicates that all maintenance operations for the electric drive system must be completed before this moment. If this moment is exceeded, the health status index will fall below the preset maintenance threshold, and the operational reliability of the electric drive system cannot be guaranteed. The latest maintenance start time is obtained by working backwards from the latest maintenance completion time, which is the latest maintenance completion time minus the maintenance time. If maintenance is performed after this latest maintenance start time, the maintenance completion time will exceed the latest maintenance completion time.

[0051] The earliest maintenance start time is determined by adding a preset safety time margin to the current time. The earliest maintenance start time indicates the earliest reasonable time to start maintenance operations on the electric drive system. The preset safety time margin is used to ensure that the electric drive system has sufficient remaining health condition to safely complete the currently scheduled flight mission before maintenance is performed.

[0052] The earliest and latest maintenance start times constitute the maintenance time window of the electric drive system. The maintenance time window is the time interval during which maintenance operations can be performed without functional failure. Maintenance can be started at any time within this interval, and the maintenance operations can be completed before the latest maintenance completion time, so that the entire maintenance period is always within the safe operating range above the preset maintenance threshold.

[0053] In summary, each electric drive system in this application embodiment obtains a degradation rate assessment model and degradation trend curve based on its own historical operating characteristics, and determines a maintenance time window. This window includes the earliest and latest maintenance start times, providing a flexible time interval for scheduling maintenance operations without causing functional failures. Different electric drive systems exhibit varying degradation rates due to differences in installation location and operating conditions, resulting in differences in the distribution and width of their respective maintenance time windows on the time axis. The time window allows for the optimization of maintenance timing combinations for multiple electric drive systems. By appropriately advancing or delaying the maintenance start time of some systems within the window range, originally dispersed maintenance needs can be aligned to be executed within the same ground shutdown window, merging multiple asynchronously triggered shutdowns into fewer planned shutdowns.

[0054] In some instances, flight mission information includes the eVTOL's mission execution time window and ground parking time window within a preset planned period. The mission execution time window is the period during which the eVTOL performs flight missions, and the ground parking time window is the period during which the eVTOL is parked on the ground. Maintenance resource information includes the available time slots for maintenance personnel within the preset planning period and the inventory status of maintenance spare parts. Available time slots are the time slots during which maintenance personnel are capable of performing the work, and inventory status is the available quantity of maintenance spare parts at each time point.

[0055] For example, flight mission information describes the temporal distribution between the eVTOL's flight mission schedule and ground parking status within a preset planning period, including two types of time intervals: mission execution time windows and ground parking time windows. The mission execution time window is the period during which the eVTOL is performing a flight mission; during this period, the aircraft is in the air operational or takeoff / landing preparation phase, and no maintenance work can be carried out. The ground parking time window is the period during which the eVTOL is parked on the ground; during this period, the aircraft is parked on the ground, and maintenance personnel can perform maintenance operations on the electric drive system. The mission execution time window and the ground parking time window do not overlap on the timeline.

[0056] For any electric drive system, the time period occupied by its maintenance operation is called the maintenance period. This maintenance period must be completely included within at least one ground downtime window. That is, the start time of the maintenance period must not be earlier than the start time of the ground downtime window into which it falls, and the end time of the maintenance period must not be later than the end time of the ground downtime window. The entire process of maintenance operation from start to finish is completed while the aircraft is parked on the ground and does not overlap with any mission execution time window.

[0057] Maintenance resource information describes the availability of maintenance support conditions within a pre-planned time period, specifically including the available time slots for maintenance personnel and the inventory status of spare parts. The available time slots for maintenance personnel represent the time range during which maintenance personnel are capable of performing tasks, ensuring they are on duty and possess the necessary skills and qualifications to perform electric drive system maintenance. The available time slots for maintenance personnel vary depending on the ground downtime window and the personnel's shift schedule. The inventory status of spare parts indicates the available quantity of various spare parts at each point in time within the pre-planned time period. This inventory status changes over time due to spare parts consumption and replenishment. The available quantity at each point in time is the actual number of spare parts stored in the inventory at that time.

[0058] For any maintenance operation of an electric drive system, the required personnel working time must be within the time frame defined by the available personnel hours. Specifically, within the same ground downtime window, the total maintenance hours required for all electric drive systems scheduled for maintenance must not exceed the total available personnel hours for that ground downtime window. Exceeding this total time means that all scheduled maintenance tasks cannot be completed within that window. Simultaneously, the consumption of various spare parts required for the maintenance operation of each electric drive system must not exceed the available quantity of that type of spare part recorded in the inventory status at the corresponding time point. Within the same ground downtime window, the total demand for the same type of spare parts for all electric drive system maintenance tasks must not exceed the available inventory quantity of that type of spare part at the corresponding time point of that window. Exceeding this limit means that sufficient spare parts cannot be obtained within that window to support all scheduled maintenance operations.

[0059] In summary, this application embodiment incorporates flight mission information and maintenance resource information into the maintenance plan decision-making process by obtaining flight mission information and maintenance resource information, thereby integrating the aircraft's future flight mission arrangements with the availability of maintenance personnel and spare parts. Flight mission information indicates which time intervals within a preset planning period are suitable for maintenance operations, while maintenance resource information indicates the upper limit of the actual number of maintenance personnel and spare parts available within each time interval suitable for maintenance operations. These two types of information together provide constraint boundaries for optimizing the combination of maintenance opportunities for multiple electric drive systems. This ensures that the generated collaborative maintenance plan reduces the number of downtimes while guaranteeing that maintenance tasks within each downtime window are completed when personnel and spare parts conditions are met, thus avoiding the inability to execute the maintenance plan due to insufficient maintenance resources.

[0060] In some instances, based on maintenance time windows and constrained by voyage mission information and maintenance resource information, the maintenance timing of multiple electric drive systems is combined and optimized to generate collaborative maintenance plans for multiple electric drive systems, including: Based on the maintenance time window of each electric drive system, as well as the voyage mission information and maintenance resource information, a maintenance timing combination optimization model is constructed with the goal of minimizing maintenance resource occupancy. The maintenance timing combination optimization model is solved to obtain a coordinated maintenance plan for multiple electric drive systems.

[0061] For example, when constructing a maintenance timing combination optimization model with the goal of minimizing maintenance resource occupancy, the maintenance period of each electric drive system is determined as the variable to be solved. Constraints are set according to the maintenance time window of each electric drive system, the ground downtime time window in the flight mission information, and the available time of maintenance personnel and the status of spare parts inventory in the maintenance resource information. This ensures that each maintenance period must be within the corresponding maintenance time window and a certain ground downtime time window at the same time, and that the sum of maintenance man-hours corresponding to all maintenance periods within the same ground downtime time window does not exceed the available time of maintenance personnel and the sum of spare parts demand does not exceed the available quantity of spare parts inventory.

[0062] When solving the maintenance timing combination optimization model, firstly, a set of candidate maintenance time periods is generated based on the intersection of the maintenance time window of each electric drive system and the downtime window of each local area. Then, a candidate maintenance time period combination is selected from the set of candidate maintenance time periods of each electric drive system as a maintenance timing combination scheme. After traversing all combination methods, the scheme that meets the constraints is selected. Then, the maintenance resource occupancy of each feasible scheme is calculated through the objective function. Finally, the scheme with the minimum maintenance resource occupancy is determined as the collaborative maintenance plan.

[0063] In some instances, maintenance timing combination optimization models are constructed based on the maintenance time window of each electric drive system, as well as voyage mission information and maintenance resource information, with the objective of minimizing maintenance resource occupancy. These include: The variables to be solved in the maintenance timing combination optimization model are determined, including the maintenance period of each electric drive system. The constraints of the maintenance timing combination optimization model are determined, including: The maintenance period for each electric drive system falls within the corresponding maintenance time window for the electric drive system. The maintenance period for each electric drive system falls within the ground downtime window. Within the same ground downtime window, the sum of maintenance hours corresponding to maintenance periods for different electric drive systems shall not exceed the available time of maintenance personnel corresponding to that ground downtime window; Within the same ground downtime window, the sum of the required number of spare parts for maintenance during different electric drive system maintenance periods shall not exceed the available number of spare parts for maintenance during that ground downtime window. The objective function of the maintenance timing combination optimization model is determined, whereby the objective function is used to calculate the maintenance resource occupancy, which is positively correlated with the number of downtimes.

[0064] For example, a maintenance timing combination optimization model is constructed with the goal of minimizing maintenance resource occupancy. The variable to be solved in the model is the maintenance period of each electric drive system, where the maintenance period represents the specific time period occupied by each electric drive system to perform maintenance operations.

[0065] After determining the variables to be solved, the constraints that the model needs to satisfy are determined: The first constraint is that the maintenance period of each electric drive system must be completely within the maintenance time window corresponding to that electric drive system, that is, the start time of the maintenance period is not earlier than the earliest maintenance start time, and the end time of the maintenance period is not later than the latest maintenance start time plus the maintenance duration; The second constraint is that the maintenance period of each electric drive system must be completely within at least one ground downtime time window in the flight mission information, that is, the maintenance period must not overlap with any mission execution time window; The third constraint is that within the same ground downtime time window, the sum of the maintenance man-hours corresponding to the maintenance periods of different electric drive systems does not exceed the available time of maintenance personnel corresponding to the ground downtime time window, that is, the total man-hour demand of all maintenance tasks arranged within the window does not exceed the total man-hours that maintenance personnel can provide within the window; The fourth constraint is that within the same ground downtime time window, the sum of the quantity of maintenance spare parts required for the maintenance periods of different electric drive systems does not exceed the available quantity of maintenance spare parts corresponding to the ground downtime time window, that is, the consumption of various types of spare parts by all maintenance tasks arranged within the window does not exceed the actual storage quantity of such spare parts in the inventory at the corresponding time point.

[0066] After determining the constraints, an objective function for the maintenance timing combination optimization model is constructed. This objective function calculates the maintenance resource occupancy, which is positively correlated with the number of downtimes. The number of downtimes is the number of ground downtime windows occupied by maintenance tasks within a pre-planned time period. Regardless of whether maintenance tasks for one or more electric drive systems are scheduled within the same ground downtime window, the downtime is counted as one. Therefore, fewer downtimes result in less maintenance resource occupancy. After determining the variables to be solved, the constraints, and the objective function, the maintenance timing combination optimization model is established. This model uses the maintenance time periods of each electric drive system as decision variables. Under the premise of satisfying the constraints of maintenance time windows, ground downtime windows, maintenance man-hours, and spare parts quantity, it seeks the combination of maintenance time periods for each electric drive system that minimizes the number of downtimes.

[0067] It should be noted that maintenance resource occupancy is an evaluation indicator of the maintenance resources consumed by a maintenance timing combination scheme. In this application, maintenance resource occupancy is determined by the number of downtimes; fewer downtimes result in lower maintenance resource occupancy, and more downtimes result in higher maintenance resource occupancy. The maintenance man-hours and spare parts requirements of each electric drive system are determined by its own degradation state. The sum of the total maintenance man-hours and the sum of the total spare parts requirements for all electric drive systems remain unchanged under different maintenance timing combinations, and do not increase or decrease due to adjustments in maintenance timing. Therefore, the total maintenance man-hours and total spare parts requirements are not considered factors affecting the change in maintenance resource occupancy. Each downtime is accompanied by fixed resource consumption resulting from the aircraft switching from operational to maintenance status, including aircraft arrival scheduling, maintenance site occupation, maintenance equipment allocation, pre- and post-maintenance status checks and release signing, etc. These fixed resource consumptions are directly related to the number of downtimes, but not to the number of maintenance tasks performed within a single downtime window. Therefore, by coordinating the maintenance tasks of multiple electric drive systems within the same ground downtime window, the total number of downtimes is reduced, which reduces the repetition of the aforementioned fixed resource consumption and thus lowers the overall level of maintenance resource occupancy.

[0068] In some instances, solving the maintenance timing combination optimization model yields coordinated maintenance plans for multiple electric drive systems, including: Based on the maintenance time window and the ground downtime window for each electric drive system, a set of candidate maintenance periods is generated for each electric drive system, wherein the set of candidate maintenance periods includes multiple candidate maintenance periods; For each electric drive system, select a candidate maintenance period from the set of candidate maintenance periods for that electric drive system, and combine all the selected candidate maintenance periods for electric drive systems into a maintenance timing combination scheme. Iterate through all combinations of candidate maintenance time periods for all electric drive systems to generate multiple maintenance timing combination schemes; From multiple maintenance timing combinations, select the maintenance timing combination that meets the constraints; The maintenance resource occupancy for each maintenance timing combination is calculated based on the objective function; The combination of maintenance times that minimize the use of maintenance resources is determined as the collaborative maintenance plan.

[0069] For example, when solving the maintenance timing combination optimization model, a set of candidate maintenance periods for each electric drive system is generated based on the maintenance time window of each electric drive system and the ground downtime windows in the flight mission information. Specifically, for each electric drive system, the intersection of the system's maintenance time window with the ground downtime windows is calculated. Each intersection corresponds to a candidate maintenance period, which satisfies the condition that it falls within the maintenance time window of the electric drive system and within a certain ground downtime window. The set of all intersections constitutes the set of candidate maintenance periods for the electric drive system.

[0070] After generating a set of candidate maintenance periods for each electric drive system, a candidate maintenance period is selected from that set for each system. The selected candidate maintenance periods for all electric drive systems are then combined to form a maintenance timing combination scheme. Each maintenance timing combination scheme assigns a specific maintenance period to each electric drive system, describing an arrangement for distributing maintenance tasks across various ground downtime windows.

[0071] Iterate through all possible combinations of candidate maintenance time periods for all electric drive systems. That is, for each candidate maintenance time period in the first set of candidate maintenance time periods for electric drive systems, combine it with each candidate maintenance time period in the second set of candidate maintenance time periods for electric drive systems, and so on until all electric drive systems are covered, generating all possible combinations of maintenance times.

[0072] After generating all maintenance timing combination schemes, each maintenance timing combination scheme is checked one by one to see if it meets the constraints. The constraints include that the maintenance period of each electric drive system is within its maintenance time window, the maintenance period of each electric drive system is within the ground downtime window, the sum of maintenance man-hours of different electric drive systems within the same ground downtime window does not exceed the available maintenance personnel time of the corresponding window, and the sum of spare parts demand of different electric drive systems within the same ground downtime window does not exceed the available spare parts quantity of the corresponding window. Maintenance timing combination schemes that do not meet any of the constraints are eliminated, and maintenance timing combination schemes that meet all constraints are retained.

[0073] For each maintenance timing combination that satisfies the constraints, its maintenance resource occupancy is calculated according to the objective function. The maintenance resource occupancy is determined by the number of ground downtime windows occupied by the combination; the fewer the number of ground downtime windows occupied, the smaller the maintenance resource occupancy. The maintenance resource occupancy of all maintenance timing combinations that satisfy the constraints is compared, and the maintenance timing combination with the smallest maintenance resource occupancy is determined as the collaborative maintenance plan. This collaborative maintenance plan represents the ground downtime window in which each electric drive system performs maintenance operations.

[0074] Please see Figure 2 The diagram below illustrates the structure of a maintenance device for an eVTOL electric drive system, as provided in this application embodiment. The device includes: The operation data acquisition unit 21 is used to acquire the operation data of multiple electric drive systems on the electric vertical takeoff and landing aircraft eVTOL. The time window determination unit 22 is used to determine the maintenance time window for each electric drive system based on the operating data; The constraint information determination unit 23 is used to obtain eVTOL flight mission information and maintenance resource information; The maintenance plan determination unit 24 is used to combine and optimize the maintenance timing of multiple electric drive systems based on the maintenance time window and constrained by voyage mission information and maintenance resource information, so as to generate a collaborative maintenance plan for multiple electric drive systems.

[0075] Please see Figure 3 This application also provides an electronic device 300, including a memory 310, a processor 320, and a computer program 311 stored in the memory 310 and executable on the processor. When the processor 320 executes the computer program 311, it implements the steps of a maintenance method for an eVTOL electric drive system.

[0076] Since the electronic device described in this embodiment is the device used to implement the maintenance device of the eVTOL electric drive system in the embodiments of this application, those skilled in the art can understand the specific implementation method and various variations of the electronic device in this embodiment based on the method described in the embodiments of this application. Therefore, how the electronic device implements the method in the embodiments of this application will not be described in detail here. Any device used by those skilled in the art to implement the method in the embodiments of this application is within the scope of protection of this application.

[0077] In practice, when the computer program 311 is executed by the processor, it can implement any of the embodiments corresponding to the first aspect.

[0078] It should be noted that the descriptions of each embodiment in the above embodiments have different focuses. For parts that are not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0079] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

[0080] Although preferred embodiments have been described in this specification, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications beyond the scope of this specification.

[0081] Obviously, those skilled in the art can make various modifications to this specification without departing from its spirit and scope. Therefore, this specification also intends to include any modifications that fall within the scope of the claims and their equivalents.

Claims

1. A maintenance method for an eVTOL electric drive system, characterized in that, include: Acquire operational data from multiple electric drive systems on an electric vertical takeoff and landing (eVTOL) aircraft; Based on the aforementioned operational data, a maintenance time window is determined for each electric drive system; Obtain eVTOL flight mission information and maintenance resource information; Based on the maintenance time window, and constrained by the voyage mission information and the maintenance resource information, the maintenance timing of multiple electric drive systems is combined and optimized to generate a collaborative maintenance plan for the multiple electric drive systems.

2. The method according to claim 1, characterized in that, The determination of the maintenance time window for each electric drive system based on the operational data includes: For each electric drive system, a corresponding degradation rate assessment model is established based on the operating data of the electric drive system, wherein the degradation rate assessment model is used to characterize the difference in degradation rate of the electric drive system under different operating conditions. For each electric drive system, the degradation trend curve of the electric drive system is determined according to the degradation rate evaluation model corresponding to the electric drive system. For each electric drive system, a maintenance time window is determined based on the degradation trend curve of the electric drive system and a preset maintenance threshold, wherein the maintenance time window includes the earliest maintenance start time and the latest maintenance start time.

3. The method according to claim 2, characterized in that, The step of establishing a corresponding degradation rate assessment model based on the operating data of the electric drive system includes: Historical operating conditions features are extracted from the operating data of the electric drive system. These historical operating conditions features are used to characterize the degree of accumulation of operating stress experienced by the electric drive system during historical operation. Based on the historical characteristics of the operating conditions, the degradation rate mapping relationship of the electric drive system under different operating conditions is determined. The degradation rate mapping relationship is used to characterize the correspondence between the stress accumulation degree and the degradation rate under different operating conditions. Based on the degradation rate mapping relationship, a degradation rate evaluation model for the electric drive system is established.

4. The method according to claim 1, characterized in that, The flight mission information includes the eVTOL's mission execution time window and ground parking time window within a preset planning period. The mission execution time window is the period during which the eVTOL performs flight missions, and the ground parking time window is the period during which the eVTOL is parked on the ground. The maintenance resource information includes the available time periods for maintenance personnel and the inventory status of maintenance spare parts within the preset planning period. The available time periods are the periods when maintenance personnel are capable of performing operations, and the inventory status is the available quantity of maintenance spare parts at each time point.

5. The method according to claim 1, characterized in that, Based on the maintenance time window, and constrained by the voyage mission information and the maintenance resource information, the maintenance timing of multiple electric drive systems is combined and optimized to generate a collaborative maintenance plan for the multiple electric drive systems, including: Based on the maintenance time window of each electric drive system, as well as the voyage mission information and the maintenance resource information, a maintenance timing combination optimization model is constructed with the goal of minimizing maintenance resource occupancy. The maintenance timing combination optimization model is solved to obtain a coordinated maintenance plan for the multiple electric drive systems.

6. The method according to claim 5, characterized in that, The step of constructing a maintenance timing combination optimization model with the objective of minimizing maintenance resource occupancy, based on the maintenance time window of each electric drive system, the voyage mission information, and the maintenance resource information, includes: The variables to be solved in the maintenance timing combination optimization model are determined, wherein the variables to be solved include the maintenance period of each electric drive system; Determine the constraints of the maintenance timing combination optimization model, wherein the constraints include: The maintenance period for each electric drive system falls within the corresponding maintenance time window for that electric drive system. The maintenance period for each electric drive system falls within the ground downtime window. Within the same ground downtime window, the sum of maintenance hours corresponding to maintenance periods for different electric drive systems shall not exceed the available time of maintenance personnel corresponding to that ground downtime window; Within the same ground downtime window, the sum of the required number of spare parts for maintenance during different electric drive system maintenance periods shall not exceed the available number of spare parts for maintenance during that ground downtime window. Determine the objective function of the maintenance timing combination optimization model, wherein the objective function is used to calculate the maintenance resource occupancy, and the maintenance resource occupancy is positively correlated with the number of downtimes.

7. The method according to claim 6, characterized in that, Solving the optimization model for the maintenance timing combination yields a coordinated maintenance plan for the multiple electric drive systems, including: Based on the maintenance time window of each electric drive system and the ground downtime time window, a set of candidate maintenance periods is generated for each electric drive system, wherein the set of candidate maintenance periods includes multiple candidate maintenance periods; For each electric drive system, a candidate maintenance period is selected from the set of candidate maintenance periods for that electric drive system, and all the selected candidate maintenance periods for electric drive systems are combined into a maintenance timing combination scheme. Iterate through all combinations of the candidate maintenance time periods for all electric drive systems to generate multiple maintenance timing combination schemes; From the multiple maintenance timing combinations, select the maintenance timing combination that satisfies the constraints; The maintenance resource occupancy for each maintenance timing combination scheme is calculated based on the objective function. The combination of maintenance timings that minimizes the amount of maintenance resources required is determined as the collaborative maintenance plan.

8. A maintenance device for an eVTOL electric drive system, characterized in that, include: The operation data acquisition unit is used to acquire the operation data of multiple electric drive systems on the electric vertical takeoff and landing (eVTOL) aircraft. A time window determination unit is used to determine the maintenance time window for each electric drive system based on the operating data. The constraint information determination unit is used to acquire eVTOL flight mission information and maintenance resource information; The maintenance plan determination unit is used to combine and optimize the maintenance timing of multiple electric drive systems based on the maintenance time window and constrained by the voyage mission information and the maintenance resource information, so as to generate a collaborative maintenance plan for the multiple electric drive systems.

9. An electronic device, comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that the processor, when executing the computer program stored in the memory, implements the steps of the maintenance method for the eVTOL electric drive system as described in any one of claims 1 to 7.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the steps of the maintenance method for the eVTOL electric drive system as described in any one of claims 1 to 7.

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