Comprehensive evaluation method and device for health state of aircraft

Abstract

The invention belongs to the technical field of aircraft state monitoring, and provides an aircraft health state comprehensive evaluation method and device, and the method comprises the steps: constructing a multi-level index system based on a plurality of aircraft health state indexes, constructing a weight judgment matrix according to correlation degrees between a plurality of subsystems of the aircrafts in the multi-level index system and the health state indexes of the aircrafts; different aircraft health state indexes correspond to different weight judgment matrixes; under the condition that the weight judgment matrix meets the consistency requirement, a target analysis method is adopted to evaluate the health state comprehensive efficiency of the aircraft and the subsystems according to the aircraft health state indexes corresponding to the weight judgment matrix, and an evaluation result is obtained; wherein the target analysis method comprises at least one of analytic hierarchy process, fuzzy analytic hierarchy process and entropy weight method. According to the method, the comprehensive evaluation accuracy and efficiency of the health state of the aircraft are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft state monitoring, in particular to an aircraft health state comprehensive evaluation method and device. BACKGROUND

[0002] Under the background of rapid development of low-altitude economy, safe operation of aircraft has become the core problem of the industry; aircraft health state comprehensive evaluation belongs to a typical multi-dimension fusion problem, and each evaluation dimension has significant difference in contribution to the overall goal.

[0003] In the related art, the health state of the aircraft is mainly evaluated by using a fault diagnosis and prediction method. Since there is a complex nonlinear correlation between components of the aircraft in terms of structure, function and utility transmission, the overall reliability of the system cannot be comprehensively quantified by simply superimposing the health states of the components, and the evaluation conclusion has a significant low reliability. In addition, the existing researches mainly use a Bayesian network and other weighting strategies to process such problems. When the system presents a highly complex feature (a large number of subsystems and a high degree of performance index refinement), the full-parameter evaluation paradigm will face the problem of dimension explosion, resulting in a large amount of calculation of the aircraft health evaluation, thereby causing low evaluation efficiency. SUMMARY

[0004] The present application provides an aircraft health state comprehensive evaluation method and device to solve the defects that the aircraft health state evaluation method in the prior art cannot comprehensively quantify the overall health state of the system, and the calculation amount of the aircraft health state evaluation using the full-parameter evaluation paradigm is too large, resulting in unreliable aircraft health evaluation results and low evaluation efficiency. The method provided by the present application improves the accuracy and efficiency of the comprehensive evaluation of the aircraft health state.

[0005] The present application provides an aircraft health state comprehensive evaluation method, comprising: A multi-level index system is constructed based on a plurality of aircraft health state indexes, and a weight judgment matrix is constructed according to the correlation between a plurality of subsystems of the aircraft and the aircraft health state indexes in the multi-level index system; different aircraft health state indexes correspond to different weight judgment matrices; In the case that the weight judgment matrix meets the consistency requirement, the health state comprehensive performance of the aircraft and each subsystem is evaluated according to the aircraft health state indexes corresponding to the weight judgment matrix by using a target analysis method, and an evaluation result is obtained; wherein the target analysis method comprises at least one of analytic hierarchy process, fuzzy analytic hierarchy process and entropy weight method.

[0006] According to the aircraft health state comprehensive evaluation method provided by the present application, the plurality of aircraft health state indexes are obtained by the following steps: A plurality of aircraft health indicators are calculated according to a plurality of subsystems of the aircraft, aircraft design specifications, historical failure data and expert experience data.

[0007] According to the aircraft health comprehensive evaluation method provided by the application, the weight judgment matrix meets the consistency requirement through the following steps: For each weight judgment matrix, if the consistency ratio of the weight judgment matrix is lower than the ratio threshold, it is determined that the weight judgment matrix meets the consistency requirement. If the consistency ratio of the weight judgment matrix exceeds the ratio threshold, the correlation between the aircraft health indicator corresponding to the weight judgment matrix and the subsystem is adjusted.

[0008] According to the aircraft health comprehensive evaluation method provided by the application, the plurality of aircraft health indicators include positive indicators, negative indicators and interval type indicators. Before the aircraft health comprehensive performance of the aircraft and each subsystem is evaluated according to the aircraft health indicators corresponding to the weight judgment matrix, the method further comprises: The positive indicators, the negative indicators and the interval type indicators are respectively subjected to multi-scale normalization processing to obtain processed aircraft health indicators.

[0009] According to the aircraft health comprehensive evaluation method provided by the application, the plurality of subsystems include an avionics system, a power subsystem, an electromechanical system and a body subsystem. The aircraft health indicators corresponding to the avionics system include attitude control performance and acceleration characteristics. The aircraft health indicators corresponding to the power subsystem include battery health, voltage characteristics and internal resistance characteristics. The aircraft health indicators corresponding to the electromechanical system include propeller speed and position control accuracy. The aircraft health indicators corresponding to the body subsystem include total mass and moment of inertia.

[0010] According to the aircraft health comprehensive evaluation method provided by the application, after the evaluation result is obtained, the method further comprises: The evaluation result corresponding to the aircraft and the evaluation results respectively corresponding to the plurality of subsystems are weighted and summed to obtain a comprehensive evaluation result. According to the correlation between the health state level and the health state score, the health state level corresponding to the comprehensive evaluation result is determined.

[0011] The application also provides an aircraft health comprehensive evaluation device, comprising: The indicator system construction module is used to construct a multi-level indicator system based on multiple aircraft health status indicators, and to construct a weight judgment matrix according to the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system; different aircraft health status indicators correspond to different weight judgment matrices. The evaluation module, provided that the weight judgment matrix meets the consistency requirements, evaluates the overall health status effectiveness of the aircraft and each subsystem based on the aircraft health status index corresponding to the weight judgment matrix, and obtains the evaluation result.

[0012] According to the present invention, a comprehensive health status assessment device for aircraft is provided, the device further includes: The health level determination module is used to perform a weighted summation of the evaluation results corresponding to the aircraft and the evaluation results corresponding to the multiple subsystems after obtaining the evaluation results, so as to obtain a comprehensive evaluation result. The health status level corresponding to the comprehensive assessment result is determined based on the correlation between the health status level and the health status score.

[0013] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the comprehensive assessment method for aircraft health status as described above.

[0014] The present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the comprehensive assessment method for aircraft health status as described above.

[0015] The present invention also provides a computer program product, including a computer program that, when executed by a processor, implements the comprehensive assessment method for aircraft health status as described above.

[0016] The method and apparatus for comprehensive assessment of aircraft health status provided by this invention constructs a multi-level indicator system based on multiple aircraft health status indicators, and constructs a weight judgment matrix according to the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system. Under the condition that the weight judgment matrix meets the consistency requirements, the target analysis method is used to evaluate the comprehensive health status effectiveness of the aircraft and each subsystem according to the aircraft health status indicators corresponding to the weight judgment matrix, and the evaluation results are obtained, thereby improving the accuracy and efficiency of comprehensive assessment of aircraft health status. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 This is a flowchart illustrating the comprehensive health status assessment method for aircraft provided by the present invention.

[0019] Figure 2 This is one of the structural schematic diagrams of the comprehensive health status assessment device for aircraft provided by the present invention.

[0020] Figure 3 This is the second structural schematic diagram of the comprehensive health status assessment device for aircraft provided by the present invention.

[0021] Figure 4 This is a schematic diagram of the structure of the electronic device provided by the present invention. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0023] The following is combined Figures 1-3 The present invention describes a method and apparatus for comprehensive assessment of the health status of aircraft.

[0024] Figure 1 This is a flowchart illustrating the comprehensive health status assessment method for aircraft provided by the present invention, as shown below. Figure 1 As shown, the method includes the following steps: Step 110: Construct a multi-level indicator system based on multiple aircraft health status indicators, and construct a weight judgment matrix according to the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system; different aircraft health status indicators correspond to different weight judgment matrices.

[0025] In this step, multiple aircraft health indicators include attitude control performance, acceleration characteristics, battery health, and propeller speed.

[0026] In this step, the aircraft's multiple subsystems include at least two of the avionics system, power subsystem, electromechanical system, and airframe subsystem.

[0027] In this step, a hierarchical structure is adopted to establish the above-mentioned multi-level indicator system, which includes a target layer, a criterion layer, and an indicator layer.

[0028] The target layer includes overall aircraft health status information, the criteria layer includes information on each subsystem of the aircraft, such as the airframe and power subsystems, and the indicator layer includes multiple aircraft health status indicators.

[0029] In this embodiment, the relative importance of each element in the criterion layer and the indicator layer is compared and scored pairwise to construct the weight judgment matrix of the criterion layer and the indicator layer.

[0030] In this embodiment, relative importance can be determined based on prior data such as expert experience. For example, based on expert experience, the degree of correlation between different subsystems and different indicators can be determined to be a certain value between 0 and 10.

[0031] For example, the 1-9 scale method can be used to construct a weight judgment matrix based on expert knowledge. 1 indicates that two elements are equally important, 9 indicates that one element is extremely more important than the other, and the intermediate values ​​represent different degrees of importance difference.

[0032] In this embodiment, relative importance can be determined based on features that describe the degree of correlation between two data points.

[0033] For example, this embodiment describes relative importance through the following automated execution process: (1) Establish the initial matrix of the target layer-criteria layer (the default parameters are derived from expert judgment knowledge, but can also be entered and adjusted). For reconnaissance missions of aircraft, the importance of each subsystem is ranked as follows: avionics system > power subsystem ≈ electro-electronics system > airframe structure subsystem.

[0034] Based on the above analysis, the target layer-criteria layer judgment matrix is ​​constructed as follows: ; For patrol missions of aircraft, the importance of each subsystem is ranked as follows: power subsystem > avionics system > electro-electronics system > airframe structure subsystem.

[0035] The target layer-criteria layer judgment matrix is ​​constructed as follows: ; (2) Perform consistency check on the weight judgment matrix of the target layer-criteria layer; where the weights of the above parameters are derived from expert judgment, and the corresponding matrix input triggering procedure is user input confirmation.

[0036] In this embodiment, based on the scoring results, the formula for calculating the weight judgment matrix between each pair of the target layer, criterion layer, and indicator layer is as follows: ; in, a 11 The element in the first row and first column of this matrix represents the correlation between the first subsystem and the first aircraft health status indicator, and so on; each aircraft health status indicator corresponds to a different weight judgment matrix.

[0037] Step 120: Under the condition that the weight judgment matrix meets the consistency requirement, the target analysis method is used to evaluate the comprehensive health status effectiveness of the aircraft and each subsystem based on the aircraft health status index corresponding to the weight judgment matrix, and the evaluation result is obtained; wherein, the target analysis method includes at least one of the following: hierarchical analysis, fuzzy hierarchical analysis and entropy weight method.

[0038] In this step, since expert scoring or algorithmic scoring may be subjective and inconsistent, it is necessary to perform a consistency check on the constructed weight judgment matrix.

[0039] For example, when the consistency ratio calculated by the weight judgment matrix meets the preset conditions, it is confirmed that the weight allocation of the weight judgment matrix is ​​reasonable, that is, it passes the consistency test; if the consistency ratio does not meet the conditions, it is necessary to adjust the correlation between the aircraft health status index and the subsystem corresponding to the weight judgment matrix until the consistency requirements are met, so as to ensure the scientificity and reliability of the weight judgment matrix.

[0040] In this embodiment, the target analysis method includes one or more of the following: hierarchical analysis, fuzzy hierarchical analysis, and entropy weight method.

[0041] Specifically, in this embodiment, based on the weight judgment matrix that has passed the consistency test, the analytic hierarchy process (AHP), fuzzy AHP, and entropy weight method are used to calculate the comprehensive health status performance evaluation value of the aircraft in each subsystem and as a whole, thus obtaining the evaluation result, which is used to quantitatively reflect the health level of the aircraft.

[0042] The comprehensive health status assessment method for aircraft provided in this invention constructs a multi-level indicator system based on multiple aircraft health status indicators, and constructs a weight judgment matrix based on the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system. Under the condition that the weight judgment matrix meets the consistency requirements, the target analysis method is used to evaluate the comprehensive health status effectiveness of the aircraft and each subsystem based on the aircraft health status indicators corresponding to the weight judgment matrix, and the evaluation results are obtained, thereby improving the accuracy and efficiency of comprehensive health status assessment of aircraft.

[0043] In some embodiments, multiple aircraft health status indicators are obtained through the following steps: multiple aircraft health status indicators are calculated based on multiple subsystems of the aircraft, aircraft design specifications, historical fault data and expert experience data.

[0044] In this embodiment, the subsystem is the avionics system, and the aircraft health status indicators are attitude control performance and acceleration characteristics.

[0045] (1) Data acquisition: The three-axis angular velocity (ω) is acquired in real time through the inertial measurement unit (IMU) of the flight control system. x , ω y , ω z ) and Euler angles (roll φ, pitch θ, yaw ψ), combined with GPS positioning data and barometer altitude data; (2) Establish a decision tree logic model: Set threshold ranges (e.g., angular velocity deviation ±0.5 rad / s, height fluctuation ±3 m); if the data exceeds the threshold, trigger an anomaly alarm and record it in the anomaly monitoring database; (3) Calculation of indicators: (3.1) The attitude control accuracy is represented by the root mean square error (RMSE) between the real-time attitude angle and the preset trajectory angle. (3.2) Use an accelerometer to collect triaxial acceleration ( a x , a y , a z This, combined with health behavior models (such as LSTM neural networks), predicts theoretical acceleration under normal flight conditions and is used to represent acceleration characteristics.

[0046] The comprehensive health status assessment method for aircraft provided in this invention calculates multiple aircraft health status indicators by using multiple subsystems of the aircraft, aircraft design specifications, historical fault data, and expert experience data. This improves the reliability of obtaining aircraft health status indicators and provides reliable data support for the subsequent construction of a multi-level indicator system.

[0047] In some embodiments, the consistency requirement of the weight judgment matrix is ​​confirmed by the following steps: for each weight judgment matrix, if the consistency ratio of the weight judgment matrix is ​​lower than the ratio threshold, the weight judgment matrix is ​​determined to meet the consistency requirement; if the consistency ratio of the weight judgment matrix exceeds the ratio threshold, the correlation between the aircraft health status index corresponding to the weight judgment matrix and the subsystem is adjusted.

[0048] In this embodiment, the correlation between the aircraft health status indicators and the subsystems can be adjusted based on expert experience data.

[0049] In this embodiment, the ratio threshold can be set according to user needs, for example, ratio threshold = 0.1.

[0050] In this embodiment, since expert scoring may be subjective and inconsistent, it is necessary to perform a consistency check on the constructed weight judgment matrix. The consistency check is determined by whether the CR value calculated from the weight judgment matrix is ​​less than 0.1. The calculation process is as follows: (1) Calculate the largest eigenvalue of the weight judgment matrix ; Specifically, (1.1) based on the constructed weight judgment matrix, the elements are normalized to normalize the square root vector into the desired feature vector. It can be expressed by the following formula: ; (1.2) Sum the terms of the same row of the normalized matrix, then divide by n to obtain the weight of each indicator, as shown in the following formula: ; in, For the first i The weights corresponding to each indicator.

[0051] (1.3) After obtaining the weight values ​​of each evaluation factor for the overall target layer and the weight of each indicator, the largest eigenvalue of the judgment matrix is ​​calculated using the following formula. : ; (2) The following formula is used to calculate the result. CI value: ; (3) Calculate the random consistency index CR using the following formula: ; In this embodiment, the CR value obtained by combining the CI and RI values ​​is the standard for the consistency test of the judgment matrix. The RI value can be obtained by looking up a table. Generally, if the CR value is less than 0.1, the judgment matrix satisfies the consistency test. If the CR value is greater than 0.1, it indicates that there is no consistency. When this requirement is not met, experts should adjust the data in the judgment matrix until the consistency test is passed.

[0052] In this embodiment, the correlation between the aircraft health status indicators and the subsystems can also be adjusted by using heuristic rules and a consistency matrix approximation method.

[0053] Specifically, this embodiment can utilize the mathematical properties of the consistency matrix (proportional rows) to calculate the deviation matrix between the current matrix and the ideal consistency matrix, and locate the element with the largest deviation; then, based on the "principle of minimum modification," it can perform targeted correction on the deviation elements: if a ij If the element in the i-th row and j-th column of the judgment matrix deviates from a reasonable proportion, it is finely adjusted to a nearby scale value according to the direction of the deviation (e.g., changing 4 to 3 or 5), iterating until the CR meets the target. This method can be combined with domain knowledge to adjust priorities in advance, avoiding disruption of key decision-making logic.

[0054] The comprehensive assessment method for aircraft health status provided in this invention determines that the weight judgment matrix meets the consistency requirements when the consistency ratio of the weight judgment matrix is ​​lower than the ratio threshold; when the consistency ratio of the weight judgment matrix exceeds the ratio threshold, the correlation between the aircraft health status indicators corresponding to the weight judgment matrix and the subsystems is adjusted. Through CR threshold control and dynamic adjustment of correlation, the method can provide underlying technical support for aviation safety for aircraft with multiple coupled subsystems.

[0055] In some embodiments, the multiple aircraft health status indicators include positive indicators, negative indicators, and interval indicators; before evaluating the comprehensive health status effectiveness of the aircraft and each subsystem based on the aircraft health status indicators corresponding to the weight judgment matrix, the comprehensive aircraft health status evaluation method further includes: performing multi-scale normalization processing on the positive indicators, negative indicators, and interval indicators respectively to obtain the processed aircraft health status indicators.

[0056] In this embodiment, after determining the indicator system and weights, the collected parameters of various aircraft indicators are standardized to eliminate the influence of differences in the dimensions and numerical ranges of different indicators.

[0057] Specifically, for positive indicators (the higher the value, the better), the following formula is used for calculation: ; For the inverse indicator (the smaller the value, the better), the following formula is used for calculation: ; For interval-type indicators, the following formula is used for calculation: ; in, The optimal target value for the indicator (such as the ideal operating parameters of the equipment design). The original monitoring values ​​of the indicators (such as parameters collected by aircraft sensors). This is the maximum value allowed for the indicator. This is the minimum value allowed by the indicator. For normalized After normalizing the input sensor data, the output is dimensionless 0-1 data for each sensor.

[0058] The comprehensive assessment method for aircraft health status provided in this invention improves the accuracy and reliability of the comprehensive assessment of aircraft health status by performing multi-scale normalization on positive, negative, and interval indicators among multiple aircraft health status indicators to obtain processed aircraft health status indicators.

[0059] In some embodiments, the multiple subsystems include an avionics system, a propulsion subsystem, an electromechanical system, and an airframe subsystem; wherein, the aircraft health status indicators corresponding to the avionics system include attitude control performance and acceleration characteristics; the aircraft health status indicators corresponding to the propulsion subsystem include battery health, voltage characteristics, and internal resistance characteristics; the aircraft health status indicators corresponding to the electromechanical system include propeller speed and position control accuracy; and the aircraft health status indicators corresponding to the airframe subsystem include total mass and moment of inertia.

[0060] Regarding attitude control performance, since the roll rate, pitch rate and yaw rate of an aircraft are directly related to whether the UAV can maintain the predetermined flight attitude and its ability to respond to external disturbances, this embodiment measures the attitude stability and controllability of the UAV by angular velocity.

[0061] Regarding acceleration characteristics, since acceleration data reflects the rate of change of the UAV's motion state, it is crucial for predicting motion trajectory and evaluating control accuracy. This embodiment evaluates the control system's response speed and stability to commands by using X-axis acceleration, Y-axis acceleration, and Z-axis acceleration.

[0062] It should be noted that battery health reflects the effectiveness of the intelligent battery management system and is also an important basis for predicting potential failures. A healthy battery means higher safety standards and more reliable flight assurance. Battery voltage directly affects the power output and stability of the drone. Voltage fluctuations and downward trends can serve as important indicators of battery health and remaining energy. Battery internal resistance reflects the internal losses and health of the battery. Increased internal resistance usually means battery aging or damage, which will lead to decreased energy conversion efficiency and increased heat generation.

[0063] Regarding propeller speed, it directly reflects the effectiveness of the electronic speed controller's (ESC) PWM frequency and control algorithm. Stable propeller speed is crucial for achieving smooth flight, especially in multi-rotor drones, where coordinated operation between different propellers is a key factor in ensuring flight stability.

[0064] Regarding position control accuracy, the X-axis position and Y-axis position reflect the position control accuracy of the UAV on the horizontal plane. Position control accuracy is crucial for performing precise flight missions (such as hovering and path tracking).

[0065] Regarding total mass, it is a fundamental parameter affecting the flight performance of UAVs. It is directly related to the load on the power system and flight time. Changes in mass distribution may lead to changes in flight characteristics, thereby affecting overall effectiveness.

[0066] Regarding rotational inertia, the X-axis rotational inertia and Y-axis rotational inertia directly affect the attitude response characteristics of the UAV. A larger rotational inertia means higher stability but a slower response speed, while a smaller rotational inertia has the opposite effect. The proper configuration of rotational inertia is crucial for balancing stability and maneuverability.

[0067] Specifically, (1) the weighted judgment matrix constructed by the avionics system including six key index parameters, namely roll rate, pitch rate, yaw rate, roll axis acceleration, yaw axis acceleration, and pitch axis acceleration, is as follows: ; (2) The power subsystem uses the following weighted judgment matrix constructed from the performance indicators of lithium polymer batteries—battery health, steady-state voltage characteristics, and internal resistance changes: ; (3) The weighted judgment matrix of the electromechanical system, which is constructed using two parameters—propeller speed range and position control accuracy—is as follows: ; (4) The weight judgment matrix of the body subsystem, constructed using the change in total body mass and the calculated moment of inertia parameters, is as follows: .

[0068] The comprehensive health status assessment method for aircraft provided in this invention divides the aircraft into four major subsystems: avionics, power, electromechanical, and airframe. It sets differentiated health status indicators for each subsystem and constructs a multi-dimensional and hierarchical assessment system. This design achieves a shift from single-parameter monitoring to system-level health management, further improving the accuracy of comprehensive health status assessment for aircraft.

[0069] In some embodiments, after obtaining the evaluation results, the comprehensive health status evaluation method for aircraft further includes: weighting and summing the evaluation results corresponding to the aircraft and the evaluation results corresponding to multiple subsystems respectively to obtain a comprehensive evaluation result; and determining the health status level corresponding to the comprehensive evaluation result based on the correlation between the health status level and the health status score.

[0070] In this embodiment, the final comprehensive performance result is obtained by weighting the subjective and objective comprehensive performance calculation results composed of the analytic hierarchy process, fuzzy analytic hierarchy process and entropy weight method using a linear weighting algorithm, and the calculated score is finally mapped to the performance evaluation.

[0071] Specifically, the weighted summation formula is used to calculate the subsystem and overall health status assessment values ​​under various effectiveness assessment methods. The weighted summation formula can be expressed as follows: ; in, S 综合 To comprehensively evaluate the results, S j For the first j Subsystem scores (corresponding to the evaluation results of each subsystem). η j This is a penalty factor (1 for normal state, and adjusted downwards according to the threshold for abnormal state). w j For the first j The weighting factors corresponding to each subsystem.

[0072] In this embodiment, the comprehensive evaluation result is between 0 and 1. Different health status levels can be set with corresponding threshold standards, such as excellent (evaluation value ≥ 0.8), good (0.6-0.8), average (0.4-0.6), and poor (< 0.4). The calculation results are mapped to the corresponding health status levels, which makes it easier to intuitively display the current health status of the aircraft.

[0073] The comprehensive health status assessment method for aircraft provided in this invention obtains a comprehensive assessment result by weighted summation of the assessment results corresponding to the aircraft and the assessment results corresponding to multiple subsystems. Based on the correlation between health status level and health status score, the health status level corresponding to the comprehensive assessment result is determined. Through hierarchical weighted fusion and dynamic level mapping, the core pain points of "misjudging the global status due to local faults" and "lagging maintenance response" in aircraft health assessment are solved, thereby reducing the full life cycle operation and maintenance cost while ensuring safety.

[0074] Figure 2 This is one of the structural schematic diagrams of the comprehensive health status assessment device for aircraft provided by the present invention. Figure 2 In the embodiment shown, an aircraft health status comprehensive assessment device includes an indicator system establishment module 1, a matrix consistency verification module 2, a comprehensive performance assessment module 3, and a calculation result integration module 4; wherein, the indicator system establishment module 1 includes a hierarchical structure construction module 101 and a weight judgment matrix construction module 102; the comprehensive performance assessment module 3 includes a multi-scale normalization processing module 301 and a subjective and objective weight calculation module 302.

[0075] Among them, the hierarchical structure construction module 101 is used to construct a multi-level indicator system based on multiple aircraft health status indicators, and the weight judgment matrix construction module 102 is used to construct a weight judgment matrix based on the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system.

[0076] The matrix consistency check module 2 is used to determine whether the weight judgment matrix meets the consistency requirements if the consistency ratio of the weight judgment matrix is ​​lower than the ratio threshold, and to adjust the correlation between the aircraft health status index corresponding to the weight judgment matrix and the subsystem if the consistency ratio of the weight judgment matrix exceeds the ratio threshold.

[0077] The multi-scale normalization processing module 301 is used to perform multi-scale normalization processing on positive indicators, negative indicators and interval indicators respectively to obtain the processed aircraft health status indicators; the subjective and objective weight calculation module 302 is used to perform weighted summation of the evaluation results corresponding to the aircraft and the evaluation results corresponding to multiple subsystems respectively to obtain the comprehensive evaluation result.

[0078] The calculation result integration module 4 is used to determine the health status level corresponding to the comprehensive assessment result based on the correlation between the health status level and the health status score.

[0079] The comprehensive assessment device for aircraft health status provided by the present invention is described below. The comprehensive assessment device for aircraft health status described below and the comprehensive assessment method for aircraft health status described above can be referred to in correspondence.

[0080] Figure 3 This is the second structural schematic diagram of the comprehensive health status assessment device for aircraft provided by the present invention, as shown below. Figure 3 As shown, the comprehensive health status assessment device for aircraft includes: an indicator system construction module 310 and an assessment module 320.

[0081] The indicator system construction module 310 is used to construct a multi-level indicator system based on multiple aircraft health status indicators, and to construct a weight judgment matrix according to the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system; different aircraft health status indicators correspond to different weight judgment matrices. The evaluation module 320, under the condition that the weight judgment matrix meets the consistency requirements, evaluates the comprehensive health status effectiveness of the aircraft and each subsystem based on the aircraft health status index corresponding to the weight judgment matrix, and obtains the evaluation results.

[0082] The comprehensive health status assessment device for aircraft provided in this invention constructs a multi-level indicator system based on multiple aircraft health status indicators, and constructs a weight judgment matrix based on the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system. Under the condition that the weight judgment matrix meets the consistency requirements, the target analysis method is used to evaluate the comprehensive health status effectiveness of the aircraft and each subsystem based on the aircraft health status indicators corresponding to the weight judgment matrix, and the evaluation results are obtained, thereby improving the accuracy and efficiency of comprehensive health status assessment of aircraft.

[0083] In some embodiments, the aircraft health status comprehensive assessment device further includes: a health level determination module, which, after obtaining the assessment results, performs a weighted summation of the assessment results corresponding to the aircraft and the assessment results corresponding to multiple subsystems respectively to obtain a comprehensive assessment result; and determines the health status level corresponding to the comprehensive assessment result based on the correlation between the health status level and the health status score.

[0084] The comprehensive health status assessment device for aircraft provided in this invention obtains a comprehensive assessment result by weighted summation of the assessment results corresponding to the aircraft and the assessment results corresponding to multiple subsystems. Based on the correlation between the health status level and the health status score, the health status level corresponding to the comprehensive assessment result is determined. Through hierarchical weighted fusion and dynamic level mapping, the core pain points of "misjudging the global status due to local faults" and "lagging maintenance response" in aircraft health assessment are solved, thereby reducing the full life cycle operation and maintenance cost while ensuring safety.

[0085] Figure 4 An example is a schematic diagram of the physical structure of an electronic device, such as... Figure 4As shown, the electronic device may include: a processor 410, a communication interface 420, a memory 430, and a communication bus 440, wherein the processor 410, the communication interface 420, and the memory 430 communicate with each other through the communication bus 440. The processor 410 can call logical instructions in the memory 430 to execute a comprehensive assessment method for aircraft health status. This method includes: constructing a multi-level indicator system based on multiple aircraft health status indicators, and constructing a weight judgment matrix according to the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system; different aircraft health status indicators correspond to different weight judgment matrices; under the condition that the weight judgment matrix meets the consistency requirement, using the objective analysis method to evaluate the comprehensive health status effectiveness of the aircraft and each subsystem according to the aircraft health status indicators corresponding to the weight judgment matrix, and obtaining the evaluation result; wherein the objective analysis method includes at least one of hierarchical analysis, fuzzy hierarchical analysis, and entropy weight method.

[0086] Furthermore, the logical instructions in the aforementioned memory 430 can be implemented as software functional units and, when sold or used as independent products, can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0087] On the other hand, the present invention also provides a computer program product, which includes a computer program that can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the comprehensive assessment method for aircraft health status provided by the above methods. The method includes: constructing a multi-level indicator system based on multiple aircraft health status indicators, and constructing a weight judgment matrix according to the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system; different aircraft health status indicators correspond to different weight judgment matrices; and, under the condition that the weight judgment matrix meets the consistency requirements, using a target analysis method to evaluate the comprehensive health status effectiveness of the aircraft and each subsystem according to the aircraft health status indicators corresponding to the weight judgment matrix, and obtaining the evaluation result; wherein, the target analysis method includes at least one of hierarchical analysis, fuzzy hierarchical analysis, and entropy weight method.

[0088] In another aspect, the present invention also provides a non-transitory computer-readable storage medium storing a computer program thereon. When executed by a processor, the computer program is implemented to perform the comprehensive assessment method for aircraft health status provided by the above methods. The method includes: constructing a multi-level indicator system based on multiple aircraft health status indicators, and constructing a weight judgment matrix according to the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system; different aircraft health status indicators correspond to different weight judgment matrices; and, provided that the weight judgment matrix meets the consistency requirements, using a target analysis method to evaluate the comprehensive health status effectiveness of the aircraft and each subsystem based on the aircraft health status indicators corresponding to the weight judgment matrix, thereby obtaining the evaluation result; wherein the target analysis method includes at least one of hierarchical analysis, fuzzy hierarchical analysis, and entropy weight method.

[0089] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0090] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0091] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention 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; and these 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 the present invention.

Claims

1. A comprehensive assessment method for the health status of an aircraft, characterized in that, include: A multi-level indicator system is constructed based on multiple aircraft health status indicators, and a weight judgment matrix is ​​constructed according to the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system; different aircraft health status indicators correspond to different weight judgment matrices. When the weight judgment matrix meets the consistency requirement, the target analysis method is used to evaluate the comprehensive health status effectiveness of the aircraft and each subsystem based on the aircraft health status index corresponding to the weight judgment matrix, and the evaluation result is obtained; wherein, the target analysis method includes at least one of hierarchical analysis, fuzzy hierarchical analysis and entropy weight method.

2. The comprehensive assessment method for aircraft health status according to claim 1, characterized in that, The multiple aircraft health status indicators were obtained through the following steps: Multiple aircraft health status indicators are calculated based on various subsystems of the aircraft, aircraft design specifications, historical fault data, and expert experience data.

3. The comprehensive assessment method for aircraft health status according to claim 1, characterized in that, The consistency requirement of the weight judgment matrix is ​​confirmed through the following steps: For each weight judgment matrix, if the consistency ratio of the weight judgment matrix is ​​lower than the ratio threshold, it is determined that the weight judgment matrix meets the consistency requirement. If the consistency ratio of the weight judgment matrix exceeds the ratio threshold, the correlation between the aircraft health status index corresponding to the weight judgment matrix and the subsystem is adjusted.

4. The comprehensive assessment method for aircraft health status according to claim 1, characterized in that, The multiple aircraft health status indicators include positive indicators, negative indicators, and interval indicators; Before evaluating the overall health status performance of the aircraft and its subsystems based on the aircraft health status index corresponding to the weight judgment matrix, the method further includes: The positive index, the negative index, and the interval index are subjected to multi-scale normalization to obtain the processed aircraft health status index.

5. The comprehensive assessment method for aircraft health status according to claim 1, characterized in that, The multiple subsystems include avionics, power, electro-electronics and airframe subsystems; Among them, the aircraft health status indicators corresponding to the avionics system include attitude control performance and acceleration characteristics; The aircraft health status indicators corresponding to the power subsystem include battery health, voltage characteristics, and internal resistance characteristics. The aircraft health status indicators corresponding to the electro-electronic system include propeller speed and position control accuracy. The aircraft health status indicators corresponding to the airframe subsystems include total mass and moment of inertia.

6. The comprehensive assessment method for aircraft health status according to claim 1, characterized in that, After obtaining the evaluation results, the method further includes: The evaluation results corresponding to the aircraft and the evaluation results corresponding to the multiple subsystems are weighted and summed to obtain the comprehensive evaluation result. The health status level corresponding to the comprehensive assessment result is determined based on the correlation between the health status level and the health status score.

7. A comprehensive health status assessment device for aircraft, characterized in that, include: The indicator system construction module is used to construct a multi-level indicator system based on multiple aircraft health status indicators, and to construct a weight judgment matrix according to the correlation between multiple subsystems of the aircraft and each aircraft health status indicator in the multi-level indicator system. Different aircraft health status indicators correspond to different weight judgment matrices; The evaluation module, provided that the weight judgment matrix meets the consistency requirements, evaluates the overall health status effectiveness of the aircraft and each subsystem based on the aircraft health status index corresponding to the weight judgment matrix, and obtains the evaluation result.

8. The comprehensive assessment device for aircraft health status according to claim 7, characterized in that, The device further includes: The health level determination module is used to perform a weighted summation of the evaluation results corresponding to the aircraft and the evaluation results corresponding to the multiple subsystems after obtaining the evaluation results, so as to obtain a comprehensive evaluation result. The health status level corresponding to the comprehensive assessment result is determined based on the correlation between the health status level and the health status score.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and running on the processor, characterized in that, When the processor executes the computer program, it implements the comprehensive assessment method for the health status of an aircraft as described in any one of claims 1 to 6.

10. A non-transitory 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 comprehensive assessment method for the health status of an aircraft as described in any one of claims 1 to 6.

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