Aircraft distributed hybrid electric propulsion system configuration scheme evaluation method and system

Abstract

The invention belongs to the technical field of airplane distributed hybrid electric propulsion system design, and particularly relates to an airplane distributed hybrid electric propulsion system configuration scheme evaluation method and system, and the method comprises the steps: 1, carrying out the assignment of subjective and objective weights of all evaluation indexes; 2, integrating subjective and objective weights of the evaluation indexes, and determining the weight of each evaluation index; and step 3, collecting parameters of each evaluation index, and calculating a score of the aircraft distributed hybrid electric propulsion system configuration scheme based on the weight of each evaluation index.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft distributed hybrid-electric propulsion system design, and specifically relates to an aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method and system. Background Art

[0002] The aircraft distributed hybrid electric propulsion system includes a turbofan engine, a generator, an electric storage device, an electric drive fan, and an energy distribution control device, wherein there can be multiple electric drive fans, each of which further includes a motor and a ducted fan. The energy distribution control device is divided into an electric energy distribution control device and a mechanical energy distribution control device. Figure 1 shown.

[0003] Aircraft distributed hybrid-electric propulsion systems can improve the aircraft's long-range flight capabilities and are more economical and environmentally friendly, becoming the focus of current aircraft propulsion system development.

[0004] Evaluating the configuration scheme of aircraft distributed hybrid electric propulsion system and selecting the appropriate design and use configuration from multiple configuration schemes are important tasks in the design of aircraft distributed hybrid electric propulsion system. Aircraft distributed hybrid electric propulsion system is completely different from the existing highly mature turbojet engine and turbofan engine. Many electrical systems are added to it, and the overall performance is sensitive to weight. Its configuration scheme cannot be evaluated simply from performance indicators. In view of this, this application is proposed. Summary of the invention

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

[0006] The technical solution of this application is: On the one hand, a configuration scheme evaluation method for a distributed hybrid-electric propulsion system of an aircraft is provided, comprising: Step 1: Assign subjective and objective weights to each evaluation index, where the evaluation indexes include propulsion system fuel consumption rate, propulsion system efficiency, motor power density, battery energy density, ducted fan physical flow, motor power, and battery power; The subjective weight of each evaluation index is assigned by experts. The subjective weight of each evaluation index is assigned as ; Assign objective weights to each evaluation index, among which The objective weight of each evaluation index is assigned as : ,in, For the The entropy value of the evaluation index; ; ; in, is the calculation coefficient of the entropy value of the evaluation index; is the number of observation samples for the evaluation index; For the evaluation index, The proportion of observations in the observation sample; ; in, For the The evaluation index is The observed value of the observation sample; Step 2: Comprehensively consider the subjective and objective weights of the evaluation indicators and determine the weight of each evaluation indicator; Step 3: Collect the parameters of each evaluation indicator, and calculate the score of the aircraft distributed hybrid-electric propulsion system configuration scheme based on the weight of each evaluation indicator.

[0007] Optionally, in the above-mentioned aircraft distributed hybrid electric propulsion system configuration scheme evaluation method, in step 2, determining The weight of the evaluation index is : ; in, For the The weight coefficient of the evaluation index.

[0008] Optionally, in the above-mentioned aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method, step 2 includes: ; ; ; ; in, is a row vector consisting of the weight coefficients of each evaluation index; is a row vector consisting of the subjective weights of each evaluation index; is a row vector consisting of the objective weights of each evaluation index.

[0009] Optionally, in the above-mentioned aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method, in step 3, the score of the aircraft distributed hybrid-electric propulsion system configuration scheme is calculated, specifically: ; in, To score the configuration options for aircraft distributed hybrid-electric propulsion systems; For the Parameters of the evaluation indicators; For the The expected value of the evaluation index, or The evaluation index is closest to the ideal target value.

[0010] On the other hand, a system for evaluating configuration schemes of a distributed hybrid-electric propulsion system of an aircraft is provided, which is used to implement the above-mentioned method for evaluating configuration schemes of a distributed hybrid-electric propulsion system of an aircraft, comprising: Subjective and objective evaluation index weight assignment module: used to assign subjective and objective weights to each evaluation index, including propulsion system fuel consumption rate, propulsion system efficiency, motor power density, battery energy density, ducted fan physical flow, motor power, and battery power; Evaluation index weight determination module: used to comprehensively consider the subjective and objective weights of evaluation indexes and determine the weights of each evaluation index; Configuration scheme scoring calculation module: used to collect the parameters of each evaluation index and calculate the score of the aircraft distributed hybrid electric propulsion system configuration scheme based on the weight of each evaluation index;

[0011] In the subjective and objective evaluation index weight assignment module, the subjective weight of each evaluation index is assigned by expert scoring. The subjective weight of each evaluation index is assigned as ; Assign objective weights to each evaluation index, among which The objective weight of each evaluation index is assigned as : ,in, For the The entropy value of the evaluation index; ; ; in, is the calculation coefficient of the entropy value of the evaluation index; is the number of observation samples for the evaluation index; For the evaluation index, The proportion of observations in the observation sample; ; in, For the The evaluation index is The observed value of the observation sample.

[0012] Optionally, in the above-mentioned aircraft distributed hybrid electric propulsion system configuration scheme evaluation system, in the evaluation index weight determination module, the first The weight of the evaluation index is : ; in, For the The weight coefficient of each evaluation index; ; ; ; ; in, is a row vector consisting of the weight coefficients of each evaluation index; is a row vector consisting of the subjective weights of each evaluation index; is a row vector consisting of the objective weights of each evaluation index.

[0013] Optionally, in the above-mentioned 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, specifically: ; in, To score the configuration options for aircraft distributed hybrid-electric propulsion systems; For the Parameters of the evaluation indicators; For the The expected value of the evaluation index, or The evaluation index is closest to the ideal target value.

[0014] This application has at least the following beneficial technical effects: Provided is a configuration scheme evaluation method and system for an aircraft distributed hybrid-electric propulsion system. The method uses propulsion system fuel consumption rate, propulsion system efficiency, motor power density, battery energy density, ducted fan physical flow, motor power, and battery power as evaluation indicators to achieve a comprehensive evaluation of the aircraft distributed hybrid-electric propulsion system configuration scheme in terms of thrust, fuel consumption rate, weight, etc., and can effectively support the design of the aircraft distributed hybrid-electric propulsion system. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the aircraft's distributed hybrid-electric propulsion system; Figure 2 It is a schematic diagram of an aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method provided in an embodiment of the present application; Figure 3 It is a schematic diagram of an aircraft distributed hybrid-electric propulsion system configuration scheme evaluation system provided in an embodiment of the present application.

[0016] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0017] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to 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 accompanying drawings, and other related parts can refer to the general design.

[0018] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the common meanings understood by those skilled in the art in the field to which this application belongs. The term "include" used in the description of this application means that the concepts appearing before the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0019] The comprehensive evaluation index system of mechanical product design is usually composed of five basic attributes, including mechanism function attributes, mechanism working performance attributes, mechanism dynamic performance attributes, economy attributes, and structural compactness attributes. According to the characteristics of the aircraft distributed hybrid-electric propulsion system, a comprehensive evaluation index system for its configuration scheme can be designed, which mainly includes three basic attributes: comprehensive performance, advancement, and structural feasibility.

[0020] The specific evaluation system indicators are determined according to the representative parameters of each type of evaluation indicators. The main representative parameters of the comprehensive performance of the aircraft distributed hybrid-electric propulsion system are the propulsion system fuel consumption rate and propulsion system efficiency. The propulsion system fuel consumption rate and propulsion system efficiency are also one of the design goals 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 a constant and is not within the scope of consideration of the aircraft distributed hybrid-electric propulsion system advanced indicators. However, the electrical system is a newly added system. The motor power density and battery energy density can characterize the manufacturing level and advancement of the motor and battery, and can be used as the main representative parameters of the aircraft distributed hybrid-electric propulsion system advanced. The main representative parameters of the structural feasibility of the aircraft distributed hybrid-electric propulsion system are the size of the ducted fan and the weight of the electrical system. 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 of the ducted fan. Therefore, the size of the ducted fan can be characterized by the physical flow of the ducted fan; the weight of the electrical system includes the weight of the motor and the weight of the battery. The weight of the motor is directly related to the motor power and power density. When the motor power density is used as the main representative parameter of advancement, the weight of the motor can be characterized by the motor power. The weight of the battery is directly related to the battery power, usage time and energy density. Since the propulsion system uses the battery in the same way and the battery energy density is used as the main representative parameter of advancement, the weight of the battery can be characterized by the battery power.

[0021] In summary, the propulsion system fuel consumption rate, propulsion system efficiency, motor power density, battery energy density, ducted fan physical flow, motor power, and battery power can be used as evaluation indicators to comprehensively evaluate the aircraft distributed hybrid electric propulsion system configuration scheme. Based on this, the embodiment of the present application provides an aircraft distributed hybrid electric propulsion system configuration scheme evaluation method, such as Figure 2 As shown in the figure, firstly, the subjective and objective weights of each evaluation index are assigned, then, the weights of each evaluation index are comprehensively determined, and finally, the weights of each evaluation index are used in combination with the Euclidean distance metric to calculate the score of the aircraft distributed hybrid-electric propulsion system configuration scheme. Then, the scores of each configuration scheme can be compared, and the configuration scheme with a higher score can be selected as the appropriate design configuration.

[0022] Step 1: Assign subjective and objective weights to each evaluation indicator.

[0023] The specific evaluation indicators include propulsion system fuel consumption rate, propulsion system efficiency, motor power density, battery energy density, duct fan physical flow, motor power, and battery power, a total of 7 evaluation indicators.

[0024] Assign subjective weights to each evaluation indicator, considering the importance of each evaluation indicator. Specifically, the subjective weights of each evaluation indicator can be assigned by expert scoring. The subjective weight of each evaluation index is assigned as , and the subjective weights of each evaluation index can be standardized and corrected. , or normalize it so that .

[0025] Assign objective weights to each evaluation index, among which The objective weight of each evaluation index is assigned as : ,in, For the The entropy value of the evaluation index.

[0026] ; ; in, is the calculation coefficient of the entropy value of the evaluation index; is the number of observation samples for the evaluation index; For the evaluation index, The proportion of observations in the observation sample.

[0027] ; in, For the The evaluation index is The observed value of the observation sample.

[0028] For the seven evaluation indicators, The observation values ​​of observation samples are used to construct the observation value matrix : .

[0029] The objective weights of each evaluation index can be standardized and corrected. , or normalize it so that .

[0030] Step 2: Comprehensively consider the subjective and objective weights of the evaluation indicators to determine the weight of each evaluation indicator.

[0031] No. The weight of the evaluation index is : ; in, For the The weight coefficient of the evaluation index is in the range of 0 to 1. The characteristics of each evaluation indicator are determined.

[0032] The weight coefficient of each evaluation index is determined based on the characteristics of the evaluation index, which can be specifically referred to as follows: ; ; ; ; in, is a row vector consisting of the weight coefficients of each evaluation index; is a row vector consisting of the subjective weights of each evaluation index; is a row vector consisting of the objective weights of each evaluation index.

[0033] Step 3: Collect the parameters of each evaluation indicator, and calculate the score of the aircraft distributed hybrid-electric propulsion system configuration scheme based on the weight of each evaluation indicator.

[0034] ; in, To score the configuration options for aircraft distributed hybrid-electric propulsion systems; For the Parameters of the evaluation indicators; For the The expected value of the evaluation index, or The evaluation index is closest to the ideal target value.

[0035] If there are n configuration schemes for the aircraft distributed hybrid electric propulsion system, the aircraft distributed hybrid electric propulsion system configuration scheme evaluation method disclosed in the above embodiment can be used to calculate the score of each configuration scheme in turn. , ,……, , and then compare the scores of each configuration scheme, and select the configuration scheme with a higher score as the appropriate design configuration.

[0036] The aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method disclosed in the above embodiment, based on the analysis of typical parameters of the aircraft distributed hybrid-electric propulsion system, selects the propulsion system fuel consumption rate, propulsion system efficiency, motor power density, battery energy density, ducted fan physical flow, motor power, and battery power as evaluation indicators, and adds the typical characteristics of each system to the indicator evaluation system to achieve a comprehensive evaluation of the aircraft distributed hybrid-electric propulsion system configuration scheme in terms of thrust, fuel consumption rate, weight, etc., which can avoid the objectivity caused by human evaluation to a certain extent, and can design corresponding programs to implement it, so as to improve the efficiency of the evaluation.

[0037] An aircraft distributed hybrid-electric propulsion system configuration scheme evaluation system is used to implement the aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method disclosed in the above embodiment, such as Figure 3 As shown, including: Subjective and objective evaluation index weight assignment module: used to assign subjective and objective weights to each evaluation index, including propulsion system fuel consumption rate, propulsion system efficiency, motor power density, battery energy density, ducted fan physical flow, motor power, and battery power; Evaluation index weight determination module: used to comprehensively consider the subjective and objective weights of evaluation indexes and determine the weights of each evaluation index; Configuration scheme scoring calculation module: used to collect the parameters of each evaluation indicator, and calculate the score of the aircraft distributed hybrid-electric propulsion system configuration scheme based on the weight of each evaluation indicator.

[0038] In the subjective and objective evaluation index weight assignment module, the subjective weight of each evaluation index is assigned by expert scoring. The subjective weight of each evaluation index is assigned as ; Assign objective weights to each evaluation index, among which The objective weight of each evaluation index is assigned as : ,in, For the The entropy value of the evaluation index; ; ; in, is the calculation coefficient of the entropy value of the evaluation index; is the number of observation samples for the evaluation index; For the evaluation index, The proportion of observations in the observation sample; ; in, For the The evaluation index is The observed value of the observation sample.

[0039] In the evaluation index weight determination module, determine the The weight of the evaluation index is : ; in, For the The weight coefficient of each evaluation index; ; ; ; ; in, is a row vector consisting of the weight coefficients of each evaluation index; is a row vector consisting of the subjective weights of each evaluation index; is a row vector consisting of the objective weights of each evaluation index.

[0040] In the configuration scheme scoring calculation module, the score of the aircraft distributed hybrid electric propulsion system configuration scheme is calculated, specifically: ; in, To score the configuration options for aircraft distributed hybrid-electric propulsion systems; For the Parameters of the evaluation indicators; For the The expected value of the evaluation index, or The evaluation index is closest to the ideal target value.

[0041] With regard to the aircraft distributed hybrid-electric propulsion system configuration scheme evaluation system disclosed in the above-mentioned embodiment, since it corresponds to the aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method disclosed in the above-mentioned embodiment, the description is relatively simple. For specific related matters, please refer to the relevant description of the aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method part. Its technical effects can also refer to the technical effects of the relevant parts of the aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method, which will not be repeated here.

[0042] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles 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 scope of protection of the present application.

Claims

1. A configuration scheme evaluation method for a distributed hybrid-electric propulsion system of an aircraft, characterized in that: include: Step 1: Assign subjective and objective weights to each evaluation index, where the evaluation indexes include propulsion system fuel consumption rate, propulsion system efficiency, motor power density, battery energy density, ducted fan physical flow, motor power, and battery power; The subjective weight of each evaluation index is assigned by experts. The subjective weight of each evaluation index is assigned as ; Assign objective weights to each evaluation index, among which The objective weight of each evaluation index is assigned as : ,in, For the The entropy value of the evaluation index; ； ； in, is the calculation coefficient of the entropy value of the evaluation index; is the number of observation samples for the evaluation index; For the evaluation index, The proportion of observations in the observation sample; ； in, For the The evaluation index is The observed value of the observation sample; Step 2: Comprehensively consider the subjective and objective weights of the evaluation indicators and determine the weight of each evaluation indicator; Step 3: Collect the parameters of each evaluation indicator, and calculate the score of the aircraft distributed hybrid-electric propulsion system configuration scheme based on the weight of each evaluation indicator.

2. The aircraft distributed hybrid electric propulsion system configuration scheme evaluation method according to claim 1, characterized in that: In step 2, determine The weight of the evaluation index is : ； in, For the The weight coefficient of the evaluation index.

3. The aircraft distributed hybrid electric propulsion system configuration scheme evaluation method according to claim 2, characterized in that: In step 2, there are: ; ； ； ； in, is a row vector consisting of the weight coefficients of each evaluation index; is a row vector consisting of the subjective weights of each evaluation index; is a row vector consisting of the objective weights of each evaluation index.

4. The aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method according to claim 3, characterized in that: In step 3, the score of the aircraft distributed hybrid electric propulsion system configuration scheme is calculated, specifically: ； in, To score the configuration options for aircraft distributed hybrid-electric propulsion systems; For the Parameters of the evaluation indicators; For the The expected value of the evaluation index, or The evaluation index is closest to the ideal target value.

5. An aircraft distributed hybrid-electric propulsion system configuration scheme evaluation system, used to implement the aircraft distributed hybrid-electric propulsion system configuration scheme evaluation method according to claim 1, characterized in that: include: Subjective and objective evaluation index weight assignment module: used to assign subjective and objective weights to each evaluation index, including propulsion system fuel consumption rate, propulsion system efficiency, motor power density, battery energy density, ducted fan physical flow, motor power, and battery power; Evaluation index weight determination module: used to comprehensively consider the subjective and objective weights of evaluation indexes and determine the weights of each evaluation index; Configuration scheme scoring calculation module: used to collect the parameters of each evaluation index and calculate the score of the aircraft distributed hybrid electric propulsion system configuration scheme based on the weight of each evaluation index; In the subjective and objective evaluation index weight assignment module, the subjective weight of each evaluation index is assigned by expert scoring. The subjective weight of each evaluation index is assigned as ; Assign objective weights to each evaluation index, among which The objective weight of each evaluation index is assigned as : ,in, For the The entropy value of the evaluation index; ； ； in, is the calculation coefficient of the entropy value of the evaluation index; is the number of observation samples for the evaluation index; For the evaluation index, The proportion of observations in the observation sample; ； in, For the The evaluation index is The observed value of the observation sample.

6. The aircraft distributed hybrid electric propulsion system configuration scheme evaluation system according to claim 5, characterized in that: In the evaluation index weight determination module, determine the The weight of the evaluation index is : ； in, For the The weight coefficient of each evaluation index; ； ； ； ； in, is a row vector consisting of the weight coefficients of each evaluation index; is a row vector consisting of the subjective weights of each evaluation index; is a row vector consisting of the objective weights of each evaluation index.

7. The aircraft distributed hybrid electric propulsion system configuration scheme evaluation system according to claim 6, characterized in that: In the configuration scheme scoring calculation module, the score of the aircraft distributed hybrid electric propulsion system configuration scheme is calculated, specifically: ； in, To score the configuration options for aircraft distributed hybrid-electric propulsion systems; For the Parameters of the evaluation indicators; For the The expected value of the evaluation index, or The evaluation index is closest to the ideal target value.

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