Method, system and readable storage medium for estimating weight of aircraft ewis

Abstract

The application provides an aircraft EWIS weight estimation method, system and readable storage medium, and the weight estimation method comprises the following steps: S1, establishing a parameter database of an existing aircraft; S2, comparing design parameters of a to-be-tested aircraft with parameter data in the database to obtain proportional data of the parameter data; S3, setting an influence coefficient according to a system design scheme of the to-be-tested aircraft and the proportional data of the parameter data; S4, obtaining weight increase and decrease data according to multi-electric technology and newly-added equipment of the to-be-tested aircraft; and S5, calculating an EWIS weight estimation value of the to-be-tested aircraft through the parameter database, the proportional data, the influence coefficient and the weight increase and decrease data. The application can not only estimate the weight of a cable, but also quickly and accurately and comprehensively estimate the weights of a wire harness assembly, a wire harness mounting piece, a separation panel, a wiring comprehensive device, a return flow network and the like in an EWIS system.

Description

[Technical Field]

[0001] This invention relates to the field of aircraft weight design technology, and in particular to an aircraft EWIS weight estimation method, system, and readable storage medium. [Background Technology]

[0002] Existing technologies propose a method for estimating aircraft cable weight, establishing a characteristic weight database for cables and using cable path models to estimate cable weight. However, this method is limited to cable weight estimation and does not address the weight estimation of other components and parts of the EWIS system. In existing cable weight estimation methods, aircraft cables, as a significant component of the overall aircraft weight, account for a larger proportion of the total system weight than ground-based aircraft (over 15%), and are primarily located in the forward fuselage, significantly impacting the aircraft's center of gravity. Traditional cable weight estimation methods mainly rely on empirical data, adjusting the cable weights of various aircraft systems based on existing equipment characteristics to arrive at a total weight and center of gravity distribution for all aircraft cables. The drawback of this method is:

[0003] 1) Narrow scope of application. The external dimensions and mission types of the new aircraft must be very close to those of the existing aircraft to ensure that the equipment architecture of the new aircraft is similar to that of the existing models and that the corresponding cable weights are comparable.

[0004] 2) Low estimation accuracy. Because the empirical data method is just a simple data comparison, it cannot reflect information such as cable length, material, and quantity, let alone the weight changes of special-configuration cables (such as those with added shielding sleeves, special cable laying in special locations, etc.).

[0005] 3) Lack of center of gravity data. Empirical data methods can only estimate the weight of the cable, but cannot reflect the distribution of the cable throughout the machine.

[0006] Therefore, it is necessary to study an aircraft EWIS weight estimation method, system, and readable storage medium to address the shortcomings of existing technologies and solve or mitigate one or more of the aforementioned problems. [Summary of the Invention]

[0007] In view of this, the present invention provides an aircraft EWIS weight estimation method, system and readable storage medium, which can not only estimate the weight of cables, but also quickly, accurately and comprehensively estimate the weight of wire harness assemblies, wire harness mounting parts, disconnect panels, cabling integration devices, return networks and so on in the EWIS system.

[0008] On one hand, the present invention provides an aircraft EWIS weight estimation method, the weight estimation method comprising:

[0009] S1: Establish a parameter database for existing aircraft;

[0010] S2: Compare the design parameters of the aircraft under test with the parameter data in the database to obtain the ratio data of the parameter data;

[0011] S3: Set the influence coefficient based on the proportional data of the system design scheme and parameter data of the aircraft under test;

[0012] S4: Obtain weight increase / decrease data based on the multi-electric technology and newly added equipment of the aircraft under test;

[0013] S5: Calculate the EWIS weight estimate of the aircraft under test using parameter database, proportional data, influence coefficients, and weight increase / decrease data.

[0014] In addition to the aspects and any possible implementations described above, an implementation is further provided, wherein S1 specifically involves: establishing a parameter database for existing aircraft based on the design parameters of existing aircraft models and the parameters of the ground integration verification platform for multi-electric aircraft.

[0015] In addition to the aspects described above and any possible implementation, an implementation is further provided in which the parameters in the parameter database in S1 include, but are not limited to, aircraft size, cabin layout, load capacity for each flight phase, and the length, weight and gauge of cables in the EWIS system, the number and weight of wiring harness assemblies, and the number and weight of mounting components and wiring devices.

[0016] In addition to the aspects described above and any possible implementation, a further implementation is provided in which the proportional data in S2 includes the proportional relationship between aircraft size and cabin arrangement.

[0017] In addition to the aspects and any possible implementations described above, a further implementation is provided in which the method for obtaining the proportional data in S2 further includes obtaining the proportional value between the EWIS system of the aircraft under test and the database data by combining the application of multi-electric technology on the aircraft under test and the influence of the return network, in conjunction with the change in load power.

[0018] In addition to the aspects and any possible implementations described above, a further implementation is provided, wherein the method for obtaining the influence coefficient in S3 specifically includes: based on the design scheme and parameter database of the EWIS system of the aircraft under test, combined with the proportional numerical relationship obtained in S2, a weighting coefficient is set according to the actual layout and quantity changes of EWIS on the aircraft, and this weighting coefficient is the influence coefficient.

[0019] In accordance with the aspects described above and any possible implementation thereof, an aircraft EWIS weight estimation system is further provided, the weight estimation system comprising:

[0020] Parameter Database Unit: Used to establish a parameter database for existing aircraft;

[0021] Ratio data acquisition unit: used to compare the design parameters of the aircraft under test with the parameter data in the database to obtain the ratio data of the parameter data;

[0022] Influence coefficient acquisition unit: Set the influence coefficient based on the system design scheme and parameter data ratio of the aircraft under test;

[0023] Weight increase / decrease data acquisition unit: used to acquire weight increase / decrease data based on the multi-electric technology and newly added equipment of the aircraft under test;

[0024] Weight estimation unit: Used to calculate the EWIS weight estimate of the aircraft under test using parameter database, proportional data, influence coefficients, and weight increase / decrease data.

[0025] In addition to the aspects described above and any possible implementation thereof, a readable storage medium is further provided, comprising: a memory storing a program; and a processor that, when executing the program, implements the weight estimation method.

[0026] Compared with the prior art, the present invention can achieve the following technical effects:

[0027] 1) Compared with traditional aircraft EWIS or cable weight estimation methods, this method can estimate the weight of the aircraft EWIS system more comprehensively and accurately, and plays an important supporting role in the weight estimation work in the preliminary design stage of the aircraft.

[0028] 2) The method of this invention has been applied and verified in the EWIS weight calculation of model aircraft and multi-electric aircraft ground integration test verification. The estimated results are not much different from the actual weight, which fully meets the requirements of the previous aircraft weight estimation work.

[0029] Of course, any product implementing this invention does not necessarily need to achieve all of the technical effects described above at the same time. [Attached Image Description]

[0030] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0031] Figure 1 This is a flowchart of a weight estimation method provided in one embodiment of the present invention.

Detailed Implementation Methods

[0032] To better understand the technical solution of the present invention, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0033] It should be understood that the described embodiments are merely some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0034] The terminology used in the embodiments of this invention is for the purpose of describing particular embodiments only and is not intended to limit the invention. The singular forms “a,” “the,” and “the” as used in the embodiments of this invention and the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise.

[0035] This invention provides an aircraft EWIS weight estimation method, system, and readable storage medium, which can be used for aircraft EWIS system weight estimation. It can realize the weight estimation of EWIS components and parts such as cables and connectors during the aircraft design phase, thus providing support for the overall aircraft weight estimation. The EWIS system is an Electrical Wiring Interconnection System, which is likened to the blood vessels and nervous system of an aircraft.

[0036] This invention provides an aircraft EWIS weight estimation method, the weight estimation method comprising:

[0037] S1: Establish a parameter database for existing aircraft;

[0038] S2: Compare the design parameters of the aircraft under test with the parameter data in the database to obtain the ratio data of the parameter data;

[0039] S3: Set the influence coefficient based on the proportional data of the system design scheme and parameter data of the aircraft under test;

[0040] S4: Obtain weight increase / decrease data based on the multi-electric technology and newly added equipment of the aircraft under test;

[0041] S5: Calculate the EWIS weight estimate of the aircraft under test using parameter database, proportional data, influence coefficients, and weight increase / decrease data.

[0042] S1 specifically involves establishing a parameter database for existing aircraft based on the design parameters of existing aircraft models and the parameters of the ground integration verification platform for multi-electric aircraft. The parameters in the parameter database in S1 include, but are not limited to, aircraft dimensions, cabin layout, load capacity for each flight phase, and the length, weight, and gauge of cables in the EWIS system, the number and weight of wiring harness assemblies, and the number and weight of installation components and wiring devices.

[0043] The proportional data in S2 includes the proportional relationship between aircraft dimensions and cabin layout. The method for obtaining the proportional data in S2 also includes obtaining the proportional value between the EWIS system of the aircraft under test and the database data by applying multi-electric technology to the aircraft under test and the influence of the return network, combined with the change of load power.

[0044] The method for obtaining the influence coefficient in S3 specifically includes: based on the design scheme and parameter database of the EWIS system of the aircraft under test, combined with the proportional numerical relationship obtained in S2, setting a weighting coefficient according to the actual layout and quantity changes of EWIS on the aircraft, and this weighting coefficient is the influence coefficient.

[0045] The calculation method in S5 is as follows (W is an abbreviation for weight):

[0046] (1) Weight of wire harness assembly: W 组件 =W1*X w1组件 +W2*X w2组件 +W3*X w3组件 +……

[0047] (2) Weight of wire harness mounting components: W 安装件 =W1*X w1安装件 +W2*X w2安装件 +W3*X w3安装件 +……

[0048] (3) Separate panel: W 分离面板 =W1*X w1分离面板 +W2*X w2分离面板 +W3*X w3分离面板 +……

[0049] (4) Cabling system: W 布线综合 =W1*X w1布线综合 +W2*X w2布线综合 +W3*X w3布线综合 +……

[0050] (5) Loop network: W 回路网

[0051] (6) Weight variation coefficient due to load: α (related to aircraft size, wiring requirements, and the impact of power changes on cable size), generally similar to the aircraft size ratio coefficient;

[0052] Weight estimation of EWIS system for newly developed aircraft (aircraft under test): W 新研EWIS系统 =W 组件 *(0.8-1.5)X w组件 +W 安装件 *(0.8-1.5)X w安装件 +W 分离面板 *(0.8-1.5)Xw分离面板 +W 布线综合 *(0.8-1.5)X w布线综合 +W 回路网 +α*W 现有飞机EWIS重量 .

[0053] The present invention also provides an aircraft EWIS weight estimation system, the weight estimation system comprising:

[0054] Parameter Database Unit: Used to establish a parameter database for existing aircraft;

[0055] Ratio data acquisition unit: used to compare the design parameters of the aircraft under test with the parameter data in the database to obtain the ratio data of the parameter data;

[0056] Influence coefficient acquisition unit: Set the influence coefficient based on the system design scheme and parameter data ratio of the aircraft under test;

[0057] Weight increase / decrease data acquisition unit: used to acquire weight increase / decrease data based on the multi-electric technology and newly added equipment of the aircraft under test;

[0058] Weight estimation unit: Used to calculate the EWIS weight estimate of the aircraft under test using parameter database, proportional data, influence coefficients, and weight increase / decrease data.

[0059] In addition to the aspects described above and any possible implementation thereof, a readable storage medium is further provided, comprising: a memory storing a program; and a processor that, when executing the program, implements the weight estimation method.

[0060] Example 1:

[0061] like Figure 1 As shown, the specific steps of this invention are as follows:

[0062] Step 1:

[0063] First, based on the design parameters of existing aircraft models and the parameters of the ground integration verification platform for multi-electric aircraft, including aircraft size, cabin layout, load capacity of each flight phase, and cable length / weight / gauge, number / weight of wiring harness components, number / weight of accessories such as installation parts and wiring devices in the EWIS system, an empirical parameter database is established using database statistical analysis tools (e.g., EXCEL, MySQL, etc.). The database can effectively realize data management and configuration, and facilitate subsequent calls. Specific statistical data examples in the database can include the following Tables 1-3.

[0064]

[0065] Table 1

[0066]

[0067] Table 2

[0068]

[0069] Table 3

[0070] The weight of wiring harness assemblies, wiring harness mounting components, separation panels, and wiring integration devices in each section of the existing aircraft is calculated.

[0071] Step Two:

[0072] The data in the database in step one is compared and analyzed with the existing parameters of the new aircraft model (the existing parameters can be obtained as preliminary reference data through the early scheme). The main analysis is based on the proportional relationship between the aircraft size and the cabin layout. It also takes into account the application of new technologies such as multi-electric systems in the new aircraft and the existence of a backflow network, combined with the change in load power, to obtain the proportional values ​​between the EWIS system of the new aircraft and the database data, as shown in Table 4 below.

[0073]

[0074]

[0075] Table 4

[0076] Step 3:

[0077] Based on the design scheme and experience data of the new aircraft EWIS system, and combined with the proportional numerical relationship calculated in step two, the influence coefficient (weighting coefficient) is set considering the impact of factors such as the actual layout and quantity changes of EWIS on the aircraft.

[0078] Considering the impact of aircraft size variations on EWIS components such as wiring harnesses in each section, and the weight advantages brought by new technologies such as multi-electric systems, the weighting coefficient for each region can be determined based on actual conditions and with reference to the length ratio coefficient in step two, within the range of length ratio coefficient X. W (0.8-1.5) times.

[0079] Step Four:

[0080] Using the database data, proportional values, and weighting coefficients obtained in steps one, two, and three, and taking into account the weight changes brought about by new technologies and equipment such as multi-electric systems, the weight estimate of the EWIS system is obtained through mathematical calculation.

[0081] (1) Weight of wire harness assembly: W 组件 =W1*X w1组件 +W2*X w2组件 +W3*Xw3组件 +……

[0082] (2) Weight of wire harness mounting components: W 安装件 =W1*X w1安装件 +W2*X w2安装件 +W3*X w3安装件 +……

[0083] (3) Separate panel: W 分离面板 =W1*X w1分离面板 +W2*X w2分离面板 +W3*X w3分离面板 +……

[0084] (4) Cabling system: W 布线综合 =W1*X w1布线综合 +W2*X w2布线综合 +W3*X w3布线综合 +……

[0085] (5) Loop network: W 回路网

[0086] (6) Weight variation coefficient due to load: α (related to aircraft size, wiring requirements, and the impact of power changes on cable size), generally similar to the aircraft size ratio coefficient.

[0087] Weight estimation of EWIS system for newly developed aircraft (aircraft under test): W 新研EWIS系统 =W 组件 *(0.8-1.5)X w组件 +W 安装件 *(0.8-1.5)X w安装件 +W 分离面板 *(0.8-1.5)X w分离面板 +W 布线综合 *(0.8-1.5)X w布线综合 +W 回路网 +α*W 现有飞机EWIS重量 .

[0088] This invention first establishes a database of aircraft dimensions, payload capacity, and EWIS system weight based on existing aircraft EWIS parameters. Then, it compares and analyzes the data in the database with the parameters of a newly developed aircraft to obtain proportional relationships. Based on the EWIS system design scheme and empirical data for the newly developed aircraft, it rationally sets influence coefficients (weighting coefficients). Finally, using the obtained database data, proportional relationships, and weighting coefficients, it mathematically calculates the estimated weight of the EWIS system. Each step is essential; the absence of any step will lead to incomplete and inaccurate estimation results.

[0089] While this invention also requires establishing a cable weight database, it eliminates the need for cable path models. Instead, it establishes a database of existing aircraft dimensions and load capacities at various stages of aircraft operation. Based on the database content, and considering the ratio of the database to the dimensions, load capacity, and cable gauge of the newly developed aircraft, and selecting appropriate influence coefficients, the weight of the aircraft's EWIS system is estimated. This method can not only estimate cable weight but also quickly, accurately, and comprehensively estimate the weight of wiring harness assemblies, wiring harness mounting components, disconnect panels, cabling integration devices, return networks, and other components within the EWIS system.

[0090] The foregoing has provided a detailed description of an aircraft EWIS weight estimation method, system, and readable storage medium provided in the embodiments of this application. The descriptions of the embodiments above are merely for the purpose of helping to understand the method and its core ideas; furthermore, those skilled in the art will recognize that, based on the ideas of this application, there will be changes in specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this application.

[0091] Certain terms are used in the specification and claims to refer to specific components. Those skilled in the art will understand that hardware manufacturers may use different names to refer to the same component. This specification and claims do not distinguish components based on differences in name, but rather on differences in function. The terms "comprising" and "including" used throughout the specification and claims are open-ended and should be interpreted as "comprising / including but not limited to". "Approximately" means that within an acceptable margin of error, those skilled in the art can solve the technical problem and substantially achieve the technical effect within a certain margin of error. The following descriptions in the specification are preferred embodiments for carrying out this application; however, these descriptions are for the purpose of illustrating the general principles of this application and are not intended to limit the scope of this application. The scope of protection of this application shall be determined by the appended claims.

[0092] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a product or system comprising a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a product or system. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the product or system that includes said element.

[0093] It should be understood that the term "and / or" used in this article is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, or B existing alone. Additionally, the character " / " in this article generally indicates that the preceding and following related objects have an "or" relationship.

[0094] The foregoing description illustrates and describes several preferred embodiments of this application. However, as previously stated, it should be understood that this application is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the application concept described herein through the foregoing teachings or techniques or knowledge in related fields. Any modifications and variations made by those skilled in the art that do not depart from the spirit and scope of this application should be within the protection scope of the appended claims.

Claims

1. A method for estimating the weight of an aircraft using EWIS, characterized in that, The weight estimation method includes: S1: Establish a parameter database for existing aircraft; S2: Compare the design parameters of the aircraft under test with the parameter data in the database to obtain the ratio data of the parameter data; S3: Set the influence coefficient based on the proportional data of the system design scheme and parameter data of the aircraft under test; S4: Obtain weight increase / decrease data based on the multi-electric technology and newly added equipment of the aircraft under test; S5: Calculate the EWIS weight estimate of the aircraft under test using parameter database, proportional data, influence coefficients, and weight increase / decrease data; The proportional data in S2 includes the proportional relationship between aircraft size and cabin layout; The proportional data in S2 also includes the ratio between the EWIS system of the aircraft under test and the database data. The ratio is obtained by combining the application of multi-electric technology on the aircraft under test and the influence of the return network with the change of load power. The method for obtaining the influence coefficient in S3 specifically includes: based on the design scheme and parameter database of the EWIS system of the aircraft under test, combined with the proportional numerical relationship obtained in S2, setting a weighting coefficient according to the actual layout and quantity changes of EWIS on the aircraft, and this weighting coefficient is the influence coefficient.

2. The weight estimation method according to claim 1, characterized in that, Specifically, S1 involves establishing a parameter database for existing aircraft based on the design parameters of existing aircraft models and the parameters of the ground integration verification platform for multi-electric aircraft.

3. The weight estimation method according to claim 2, characterized in that, The parameters in the parameter database in S1 include aircraft dimensions, cabin layout, load capacity for each flight phase, as well as the length, weight and gauge of cables in the EWIS system, the number and weight of wiring harness assemblies, and the number and weight of installation parts and wiring devices.

4. An aircraft EWIS weight estimation system, characterized in that, The weight estimation system includes: Parameter Database Unit: Used to establish a parameter database for existing aircraft; Ratio data acquisition unit: used to compare the design parameters of the aircraft under test with the parameter data in the database, and obtain the ratio data of the parameter data. The ratio data includes the ratio relationship between the aircraft size and the compartment layout. The proportional data also includes the ratio between the EWIS system of the aircraft under test and the database data. The ratio is obtained by combining the application of multi-electric technology on the aircraft under test and the influence of the return network with the change of load power. Influence Coefficient Acquisition Unit: Based on the system design scheme and parameter data ratio of the aircraft under test, the influence coefficient is set. The specific method for acquiring the influence coefficient includes: based on the EWIS system design scheme and parameter database of the aircraft under test, combined with the obtained proportional numerical relationship, and taking into account the actual layout and quantity changes of EWIS on the aircraft, a weighting coefficient is set, which is the influence coefficient. Weight increase / decrease data acquisition unit: used to acquire weight increase / decrease data based on the multi-electric technology and newly added equipment of the aircraft under test; Weight estimation unit: Used to calculate the EWIS weight estimate of the aircraft under test using parameter database, proportional data, influence coefficients, and weight increase / decrease data.

5. A readable storage medium, comprising: A memory, wherein the memory stores a program; A processor that, when executing the program, implements the weight estimation method as described in any one of claims 1 to 3.

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