An evaluation method and system for the configuration scheme of an aircraft distributed hybrid electric propulsion system

Abstract

This application belongs to the technical field of aircraft distributed hybrid electric propulsion system design, and specifically relates to an evaluation method and system for the configuration scheme of an aircraft distributed hybrid electric propulsion system. Among them, the evaluation method for the configuration scheme of an aircraft distributed hybrid electric propulsion system includes: Step 1, assign subjective and objective weights to each evaluation index; Step 2, comprehensively evaluate the subjective and objective weights of the evaluation indexes to determine the weights of each evaluation index; Step 3, collect the parameters of each evaluation index, and calculate the score of the configuration scheme of the aircraft distributed hybrid electric propulsion system based on the weights of each evaluation index.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft distributed hybrid-electric propulsion system design, and particularly relates to a method and system for evaluating the configuration scheme of an aircraft distributed hybrid-electric propulsion system. Background Art

[0002] An aircraft distributed hybrid-electric propulsion system includes a turbofan engine, a generator, an electrical energy storage device, an electric drive fan, and an energy distribution control device. Among them, there can be multiple electric drive fans, and each electric drive fan further includes a motor and a ducted fan. The energy distribution control device is divided into an electrical energy distribution control device and a mechanical energy distribution control device, as specifically shown in Figure 1 as follows.

[0003] The aircraft distributed hybrid-electric propulsion system can enhance the long-range flight ability of the aircraft, and is more economical and environmentally friendly, becoming the focus of the current development of aircraft propulsion systems.

[0004] Evaluating the configuration scheme of an aircraft distributed hybrid-electric propulsion system and selecting a suitable design and usage configuration from multiple configuration schemes is an important task in the design of an aircraft distributed hybrid-electric propulsion system. The aircraft distributed hybrid-electric propulsion system is completely different from the existing turbojet engines and turbofan engines with high maturity. Many electrical systems are added to it, and its overall performance is sensitive to weight. It is impossible to simply evaluate its configuration scheme based on performance indicators. In view of this, this application is proposed. Summary of the Invention

[0005] The purpose of this application is to provide a method and system for evaluating the configuration scheme of an aircraft distributed hybrid-electric propulsion system, so as to comprehensively evaluate the configuration scheme of an aircraft distributed hybrid-electric propulsion system based on weight and performance indicators, and support the design work of an aircraft distributed hybrid-electric propulsion system.

[0006] The technical solution of this application is as follows:

[0007] On the one hand, a method for evaluating the configuration scheme of an aircraft distributed hybrid-electric propulsion system is provided, including:

[0008] Step 1: Assign subjective and objective weights to each evaluation index. Among them, the evaluation indexes include the fuel consumption rate of the propulsion system, the efficiency of the propulsion system, the motor power density, the battery energy density, the physical flow of the ducted fan, the motor power, and the battery power;

[0009] Step 2: Combine the subjective and objective weights of the evaluation indexes to determine the weight of each evaluation index;

[0010] Step 3: Collect the parameters of each evaluation index, and calculate the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system based on the weight of each evaluation index.

[0011] Optionally, in the above evaluation method for the aircraft distributed hybrid electric propulsion system configuration scheme, in step one, the subjective weights of each evaluation index are assigned. Specifically, the method of expert scoring is adopted to assign the subjective weights of each evaluation index. Among them, the assignment of the subjective weight of the j-th evaluation index is a j ;

[0012] In step one, the objective weights of each evaluation index are assigned. Among them, the assignment of the objective weight of the j-th evaluation index is b j :

[0013] Among them, μ j is the entropy value of the j-th evaluation index.

[0014] Optionally, in the above evaluation method for the aircraft distributed hybrid electric propulsion system configuration scheme, in step one,

[0015] k = 1 / lnm;

[0016] Among them,

[0017] k is the calculation coefficient of the entropy value of the evaluation index;

[0018] m is the number of observation samples of the evaluation index;

[0019] c ij is the proportion of the observed value of the i-th observation sample of the j-th evaluation index;

[0020]

[0021] Among them,

[0022] x ij is the observed value of the j-th evaluation index in the i-th observation sample.

[0023] Optionally, in the above evaluation method for the aircraft distributed hybrid electric propulsion system configuration scheme, in step two, the weight of the j-th evaluation index is determined as w j :

[0024] w j = α j ·a j +(1 - α j )·b j ;

[0025] Among them,

[0026] α j is the weight value coefficient of the j-th evaluation index.

[0027] Optionally, in the above evaluation method for the configuration scheme of the aircraft distributed hybrid-electric propulsion system, in step two:

[0028] α = (α1, α2,......, α7);

[0029] W1 = (a1, a2,......, a7);

[0030] W2 = (b1, b2,......, b7);

[0031] Among them,

[0032] α is a row vector composed of the weight value coefficients of each evaluation index;

[0033] W1 is a row vector composed of the subjective weights of each evaluation index;

[0034] W2 is a row vector composed of the objective weights of each evaluation index.

[0035] Optionally, in the above evaluation method for the configuration scheme of the aircraft distributed hybrid-electric propulsion system, in step three, calculating the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system is specifically as follows:

[0036]

[0037] Among them,

[0038] S is the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system;

[0039] x j is the parameter of the j-th evaluation index;

[0040] x sj is the expected value of the j-th evaluation index, or the target value closest to the ideal for the j-th evaluation index.

[0041] On the other hand, an evaluation system for the configuration scheme of the aircraft distributed hybrid-electric propulsion system is provided to implement the above evaluation method for the configuration scheme of the aircraft distributed hybrid-electric propulsion system, including:

[0042] Subjective and objective evaluation index weight assignment module: used to assign subjective and objective weights to each evaluation index. Among them, the evaluation indexes include the fuel consumption rate of the propulsion system, the efficiency of the propulsion system, the motor power density, the battery energy density, the physical flow of the ducted fan, the motor power, and the battery power;

[0043] Evaluation index weight determination module: used to comprehensively evaluate the subjective and objective weights of the evaluation indexes to determine the weights of each evaluation index;

[0044] Configuration plan scoring calculation module: used to collect the parameters of each evaluation index, and calculate the score of the configuration plan of the aircraft distributed hybrid electric propulsion system based on the weights of each evaluation index.

[0045] Optionally, in the above-mentioned aircraft distributed hybrid electric propulsion system configuration plan evaluation system, in the subjective and objective evaluation index weight assignment module, the subjective weights of each evaluation index are assigned by means of expert scoring. Among them, the assignment of the subjective weight of the j-th evaluation index is a j ;

[0046] The objective weights of each evaluation index are assigned. Among them, the assignment of the objective weight of the j-th evaluation index is b j :

[0047] where μ j is the entropy value of the j-th evaluation index;

[0048] In step one,

[0049] k = 1 / lnm;

[0050] where

[0051] k is the calculation coefficient of the evaluation index entropy value;

[0052] m is the number of observation samples of the evaluation index;

[0053] c ij is the proportion of the observed value of the i-th observation sample of the j-th evaluation index;

[0054]

[0055] where

[0056] x ij is the observed value of the j-th evaluation index in the i-th observation sample.

[0057] Optionally, in the above-mentioned aircraft distributed hybrid electric propulsion system configuration plan evaluation system,

[0058] In the evaluation index weight determination module, the weight of the j-th evaluation index is determined as w j :

[0059] w j = α j ·a j +(1 - α j )·b j ;

[0060] where

[0061] α jis the weight value coefficient of the j-th evaluation index;

[0062]

[0063] α = (α1, α2,......, α7);

[0064] W1 = (a1, a2,......, a7);

[0065] W2 = (b1, b2,......, b7);

[0066] where,

[0067] α is a row vector composed of the weight value coefficients of each evaluation index;

[0068] W1 is a row vector composed of the subjective weights of each evaluation index;

[0069] W2 is a row vector composed of the objective weights of each evaluation index.

[0070] Optionally, in the above aircraft distributed hybrid electric propulsion system configuration scheme evaluation system, in the configuration scheme scoring calculation module, the score of the aircraft distributed hybrid electric propulsion system configuration scheme is calculated as follows:

[0071]

[0072] where,

[0073] S is the score of the aircraft distributed hybrid electric propulsion system configuration scheme;

[0074] x j is the parameter of the j-th evaluation index;

[0075] x sj is the expected value of the j-th evaluation index, or the target value closest to the ideal of the j-th evaluation index.

[0076] This application has at least the following beneficial technical effects:

[0077] Provide an evaluation method and system for the configuration scheme of an aircraft distributed hybrid electric propulsion system. Using the fuel consumption rate of the propulsion system, the efficiency of the propulsion system, the motor power density, the battery energy density, the physical flow of the ducted fan, the motor power, and the battery power as evaluation indicators, realize the comprehensive evaluation of the thrust, fuel consumption rate, weight, etc. of the aircraft distributed hybrid electric propulsion system configuration scheme, and can effectively support the design work of the aircraft distributed hybrid electric propulsion system. BRIEF DESCRIPTION OF THE DRAWINGS

[0078] Figure 1 is a schematic diagram of an aircraft distributed hybrid electric propulsion system;

[0079] Figure 2 It is a schematic diagram of the evaluation method for the configuration scheme of the aircraft distributed hybrid-electric propulsion system provided by the embodiments of the present application;

[0080] Figure 3 It is a schematic diagram of the evaluation system for the configuration scheme of the aircraft distributed hybrid-electric propulsion system provided by the embodiments of the present application.

[0081] To better illustrate this embodiment, some contents in the drawings are omitted and are only for illustrative purposes and should not be construed as a limitation to the present application. Specific Embodiments

[0082] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely in conjunction with the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, which are only used to explain the present application rather than limit the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design.

[0083] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should be the ordinary meanings understood by those of ordinary skill in the field to which the present application belongs. The "including" used in the description of the present application means that the concept appearing before this word covers the concepts listed after this word and their equivalents, without excluding other related concepts.

[0084] The comprehensive evaluation index system for mechanical product design usually consists of five basic attributes, including mechanism function attributes, mechanism working performance attributes, mechanism dynamic performance attributes, economic attributes, and structural compactness attributes. According to the characteristics of the aircraft distributed hybrid-electric propulsion system, the comprehensive evaluation index system for its configuration scheme can be designed to mainly include three basic attributes: comprehensive performance, advancement, and structural realizability.

[0085] The specific evaluation system indicators are determined according to the representative parameters of each type of evaluation indicator. The main representative parameters of the comprehensive performance of the aircraft distributed hybrid-electric propulsion system are the fuel consumption rate of the propulsion system and the efficiency of the propulsion system. The fuel consumption rate of the propulsion system and the efficiency of the propulsion system are also one of the design objectives of the propulsion system. Since the aircraft distributed hybrid-electric propulsion system is developed based on the existing turbofan engine, the level of the existing turbofan engine is an invariant and is not within the scope of consideration of the advancedness indicators of the aircraft distributed hybrid-electric propulsion system. However, the electrical system is a newly added system, and the motor power density and battery energy density can characterize the manufacturing level and advancedness of the motor and battery, and can be used as the main representative parameters of the advancedness of the aircraft distributed hybrid-electric propulsion system. The main representative parameters of the structural realizability of the aircraft distributed hybrid-electric propulsion system are the size of the ducted fan and the weight of the electrical system. Among them, the size of the ducted fan can be characterized by the diameter of the ducted fan, and the diameter of the ducted fan is directly related to the physical flow rate of the ducted fan. Therefore, the physical flow rate of the ducted fan can be used to characterize the size of the ducted fan; the weight of the electrical system includes the weight of the motor and the weight of the battery. Among them, the weight of the motor is directly related to the motor power and power density. In the case where the motor power density is used as the main representative parameter of advancedness, the motor power can be used to characterize the weight of the motor, and the weight of the battery is directly related to the battery power, usage duration, and energy density. Since the propulsion system has a consistent battery usage method and the battery energy density is used as the main representative parameter of advancedness, the battery power can be used to characterize the weight of the battery.

[0086] Based on the above, the fuel consumption rate of the propulsion system, the efficiency of the propulsion system, the motor power density, the battery energy density, the physical flow rate of the ducted fan, the motor power, and the battery power can be used as evaluation indicators to comprehensively evaluate the configuration scheme of the aircraft distributed hybrid-electric propulsion system. Based on this, the embodiment of the present application provides a method for evaluating the configuration scheme of the aircraft distributed hybrid-electric propulsion system. As Figure 2 shown, first, subjective and objective weights are assigned to each evaluation indicator, then, the weights of each evaluation indicator are comprehensively determined, and finally, using the weights of each evaluation indicator and combining the Euclidean distance metric, the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system is calculated. Furthermore, the scores of each configuration scheme can be compared, and the configuration scheme with a higher score can be selected as the appropriate design and usage configuration.

[0087] Step 1: Assign subjective and objective weights to each evaluation indicator.

[0088] The evaluation indicators specifically include the fuel consumption rate of the propulsion system, the efficiency of the propulsion system, the motor power density, the battery energy density, the physical flow rate of the ducted fan, the motor power, and the battery power, a total of 7 evaluation indicators.

[0089] Assign subjective weights to each evaluation index, considering the importance of each evaluation index. Specifically, the subjective weights of each evaluation index can be assigned by expert scoring. Among them, the assignment of the subjective weight of the j-th evaluation index is a j , and the subjective weights of each evaluation index can be standardized and corrected to make Or perform normalization to make

[0090] Assign objective weights to each evaluation index. Among them, the assignment of the objective weight of the j-th evaluation index is b j :

[0091] Among them, μ j Is the entropy value of the j-th evaluation index.

[0092]

[0093] k = 1 / lnm;

[0094] Among them,

[0095] k is the calculation coefficient of the entropy value of the evaluation index;

[0096] m is the number of observation samples of the evaluation index;

[0097] c ij Is the proportion of the observed value of the i-th observation sample of the j-th evaluation index.

[0098]

[0099] Among them,

[0100] x ij Is the observed value of the j-th evaluation index in the i-th observation sample.

[0101] For 7 evaluation indexes, with the observed values of m observation samples, construct an observed value matrix X = (x ij ) m×7 :

[0102]

[0103] The objective weights of each evaluation index can be standardized and corrected to make Or perform normalization to make

[0104] Step 2: Combine the subjective and objective weights of the comprehensive evaluation index to determine the weights of each evaluation index.

[0105] The weight of the j-th evaluation index is w j :

[0106] w j = α j · a j + (1 - α j )· b j ;

[0107] Among them,

[0108] α j is the weight value coefficient of the j-th evaluation index, within the range of 0 to 1, and is determined according to the characteristics of the j-th evaluation index.

[0109] The determination of the weight value coefficients of each evaluation index is based on the characteristics of the evaluation index and can be specifically referred to as follows:

[0110]

[0111] α = (α1, α2,......, α7);

[0112] W1 = (a1, a2,......, a7);

[0113] W2 = (b1, b2,......, b7);

[0114] Among them,

[0115] α is a row vector composed of the weight value coefficients of each evaluation index;

[0116] W1 is a row vector composed of the subjective weights of each evaluation index;

[0117] W2 is a row vector composed of the objective weights of each evaluation index.

[0118] Step 3: Collect the parameters of each evaluation index, and calculate the score of the aircraft distributed hybrid electric propulsion system configuration scheme based on the weights of each evaluation index.

[0119]

[0120] Among them,

[0121] S is the score of the aircraft distributed hybrid electric propulsion system configuration scheme;

[0122] x j is the parameter of the j-th evaluation index;

[0123] x sj is the expected value of the j-th evaluation index, or the target value closest to the ideal of the j-th evaluation index.

[0124] If there are n configuration schemes for the aircraft distributed hybrid-electric propulsion system, the evaluation method for the configuration scheme of the aircraft distributed hybrid-electric propulsion system disclosed in the above embodiments can be used to calculate the scores S1, S2, …, S of each configuration scheme in sequence. n Furthermore, by comparing the scores of each configuration scheme, the configuration scheme with a higher score can be selected as the suitable design and usage configuration.

[0125] Based on the analysis of the typical parameters of the aircraft distributed hybrid-electric propulsion system, the evaluation method for the configuration scheme of the aircraft distributed hybrid-electric propulsion system disclosed in the above embodiments selects the specific fuel consumption of the propulsion system, propulsion system efficiency, motor power density, battery energy density, physical flow of the ducted fan, motor power, and battery power as evaluation indicators, and incorporates the typical characteristics of each system into the index evaluation system to achieve a comprehensive evaluation of the thrust, specific fuel consumption, weight, etc. of the configuration scheme of the aircraft distributed hybrid-electric propulsion system. To a certain extent, it can avoid the subjectivity brought by manual evaluation and can be implemented by designing corresponding programs to improve the evaluation efficiency.

[0126] An evaluation system for the configuration scheme of an aircraft distributed hybrid-electric propulsion system is used to implement the evaluation method for the configuration scheme of the aircraft distributed hybrid-electric propulsion system disclosed in the above embodiments, as Figure 3 shown, including:

[0127] The subjective and objective evaluation index weight assignment module: used to assign subjective and objective weights to each evaluation index. Among them, the evaluation indexes include the specific fuel consumption of the propulsion system, propulsion system efficiency, motor power density, battery energy density, physical flow of the ducted fan, motor power, and battery power;

[0128] The evaluation index weight determination module: used to comprehensively consider the subjective and objective weights of the evaluation indexes to determine the weights of each evaluation index;

[0129] The configuration scheme score calculation module: used to collect the parameters of each evaluation index and calculate the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system based on the weights of each evaluation index.

[0130] In the subjective and objective evaluation index weight assignment module, the subjective weights of each evaluation index are assigned by means of expert scoring. Among them, the assignment of the subjective weight of the jth evaluation index is a j ;

[0131] The objective weights of each evaluation index are assigned. Among them, the assignment of the objective weight of the jth evaluation index is b j :

[0132] where μ j is the entropy value of the jth evaluation index;

[0133] In step one,

[0134] k = 1 / lnm;

[0135] wherein,

[0136] k is the calculation coefficient of the entropy value of the evaluation index;

[0137] m is the number of observation samples of the evaluation index;

[0138] c ij is the proportion of the observed value of the i-th observation sample of the j-th evaluation index;

[0139]

[0140] wherein,

[0141] x ij is the observed value of the j-th evaluation index in the i-th observation sample.

[0142] In the evaluation index weight determination module, the weight of the j-th evaluation index is determined as w j :

[0143] w j = α j ·a j +(1 - α j )·b j ;

[0144] wherein,

[0145] α j is the weight value coefficient of the j-th evaluation index;

[0146]

[0147] α = (α1, α2,......, α7);

[0148] W1 = (a1, a2,......, a7);

[0149] W2 = (b1, b2,......, b7);

[0150] wherein,

[0151] α is a row vector composed of the weight value coefficients of each evaluation index;

[0152] W1 is a row vector composed of the subjective weights of each evaluation index;

[0153] W2 is a row vector composed of the objective weights of each evaluation index.

[0154] In the configuration scheme scoring calculation module, calculate the score of the aircraft distributed hybrid electric propulsion system configuration scheme, specifically as follows:

[0155]

[0156] Among them,

[0157] S is the score of the aircraft distributed hybrid electric propulsion system configuration scheme;

[0158] x j is the parameter of the j-th evaluation index;

[0159] x sj is the expected value of the j-th evaluation index, or the target value closest to the ideal for the j-th evaluation index.

[0160] For the aircraft distributed hybrid electric propulsion system configuration scheme evaluation system disclosed in the above embodiments, since it corresponds to the aircraft distributed hybrid electric propulsion system configuration scheme evaluation method disclosed in the above embodiments and is described relatively simply, for the specific relevant parts, reference can be made to the relevant descriptions in the part of the aircraft distributed hybrid electric propulsion system configuration scheme evaluation method, and its technical effects can also be referred to the technical effects of the relevant parts of the aircraft distributed hybrid electric propulsion system configuration scheme evaluation method, which will not be elaborated here.

[0161] So far, the technical solutions of the present application have been described in combination with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. An evaluation method for the configuration scheme of an aircraft distributed hybrid electric propulsion system, characterized in that, Including: Step 1: Assign subjective and objective weights to each evaluation index. The evaluation indexes include the fuel consumption rate of the propulsion system, the efficiency of the propulsion system, the motor power density, the battery energy density, the physical flow of the ducted fan, the motor power, and the battery power; Step 2: Integrate the subjective and objective weights of the evaluation indexes to determine the weights of each evaluation index; Step 3: Collect the parameters of each evaluation index, and calculate the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system based on the weights of each evaluation index; In Step 1, subjective weights are assigned to each evaluation index. Specifically, the method of expert scoring is adopted to assign subjective weights to each evaluation index. Among them, the assignment of the subjective weight of the j-th evaluation index is a j ; In Step 1, assign objective weights to each evaluation index. Among them, the objective weight of the j-th evaluation index is assigned as b j : Among them, μ j is the entropy value of the j-th evaluation index; In step one, k = 1 / lnm; Wherein, k is the calculation coefficient of the entropy value of the evaluation index; m is the number of observation samples of the evaluation index; c ij is the proportion of the observed value of the i-th observation sample for the j-th evaluation index; Wherein, x ij is the observed value of the j-th evaluation index for the i-th observed sample; In step two, determine that the weight of the j-th evaluation index is w j : w j = α j · a j + (1 - α j )· b j ; Wherein, α j is the weight value coefficient of the j-th evaluation index; In Step 2, there is: α＝(α1,α2,......,α7)； W1 = (a1, a2,......, a7); W2 = (b1, b2,......, b7); Wherein, α is a row vector composed of the weight value coefficients of each evaluation index; W1 is a row vector composed of the subjective weights of each evaluation index; W2 is a row vector composed of the objective weights of each evaluation index; In Step 3, calculating the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system is specifically: Wherein, S is the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system; x j is the parameter of the j-th evaluation index; x sj is the expected value of the j-th evaluation index, or the target value closest to the ideal for the j-th evaluation index.

2. An evaluation system for the configuration scheme of an aircraft distributed hybrid-electric propulsion system, which is used to implement the evaluation method for the configuration scheme of the aircraft distributed hybrid-electric propulsion system described in claim 1, characterized in that, Including: Subjective and objective evaluation index weight assignment module: used to assign subjective and objective weights to each evaluation index. The evaluation indexes include the fuel consumption rate of the propulsion system, the efficiency of the propulsion system, the motor power density, the battery energy density, the physical flow of the ducted fan, the motor power, and the battery power; Evaluation index weight determination module: used to integrate the subjective and objective weights of the evaluation indexes to determine the weights of each evaluation index; Configuration scheme score calculation module: used to collect the parameters of each evaluation index, and calculate the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system based on the weights of each evaluation index; In the subjective and objective evaluation index weight assignment module, the subjective weights of each evaluation index are assigned by means of expert scoring. Among them, the assignment of the subjective weight of the j-th evaluation index is a j ; Assign objective weights to each evaluation index. Among them, the objective weight assignment for the j-th evaluation index is b j : Among them, μ j is the entropy value of the j-th evaluation index; In Step 1, k = 1 / lnm; Wherein, k is the calculation coefficient of the entropy value of the evaluation index; m is the number of observation samples of the evaluation index; c ij is the proportion of the observed value of the i-th observation sample for the j-th evaluation index; Wherein, x ij is the observed value of the j-th evaluation index for the i-th observed sample; In the evaluation index weight determination module, the weight of the j-th evaluation index is determined as w j : w j = α j · a j + (1 - α j )· b j ; Wherein, α j is the weight value coefficient of the j-th evaluation index; α＝(α1,α2,......,α7)； W1 = (a1, a2,......, a7); W2 = (b1, b2,......, b7); Wherein, α is a row vector composed of the weight value coefficients of each evaluation index; W1 is a row vector composed of the subjective weights of each evaluation index; W2 is a row vector composed of the objective weights of each evaluation index; In the configuration scheme score calculation module, calculating the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system is specifically: Wherein, S is the score of the configuration scheme of the aircraft distributed hybrid-electric propulsion system; x j is the parameter of the j-th evaluation index; x sj is the expected value of the j-th evaluation index, or the target value closest to the ideal for the j-th evaluation index.

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