KR102396920B1 - Apparatus for select trial aircraft and method for improving aircraft performance - Google Patents

Abstract

The present invention provides a prototype aircraft selection device and an aircraft performance improvement method capable of selecting an aircraft with the highest complexity among aircraft of the same type as a prototype aircraft. According to the present invention, the prototype aircraft selection device comprises: a classifier for classifying aircraft of similar groups into different derivative models according to mission characteristics; a calculator for confirming whether or not components required to operate additional equipment to be added to the aircraft are loaded for each derivative model and calculating the unloaded number of unloaded components for each derivative model; and a selector for selecting a derivative model to be used as a prototype according to the unloaded number. Accordingly, it is possible to stably improve the performance of aircraft by selecting the aircraft with the highest complexity among a plurality of aircraft as a prototype.

Description

Prototype selection device and aircraft performance improvement method

The present invention relates to a prototype selection device and an aircraft performance improvement method, and more particularly, to a prototype selection device capable of stably improving the performance of aircraft by selecting an aircraft with the highest complexity among aircraft of the same type as a prototype, and It relates to a method for improving aircraft performance.

In general, the military operates a plurality of aircraft of the same type. Aircraft can be adapted to the circumstances of military service. Therefore, there are various derivative models according to the modification even for the same type of aircraft.

At this time, the performance improvement of the entire aircraft of the same type may proceed. To this end, a prototype can be manufactured and tested and operational evaluation can be performed. When the prototype passes the test and operational evaluation, performance improvement of the actual aircraft is carried out.

However, there is a difference in the type and structure of the payload between the prototype and the derivative model. For example, the derived model may have a more complex structure than the prototype, or payload equipment not mounted on the prototype may be mounted on the derived model. Therefore, when the performance improvement of the derived model is performed based on the prototype, a problem may occur while operating the derived model.

KR 2014-0061805 A

The present invention provides a prototype selection device and an aircraft performance improvement method capable of selecting an aircraft with the highest complexity among aircraft of the same type as a prototype.

The present invention provides a prototype selection device and an aircraft performance improvement method that can stably perform performance improvement of aircraft.

The present invention is a classifier for classifying aircraft of similar groups into different derivative models according to mission characteristics; a calculator for confirming for each derivative model whether or not components necessary to operate additional equipment to be added to the aircraft are mounted, and calculating the number of unmounted components for each derivative model; and a selector for selecting a derived model to be used as a prototype according to the number of unmounted units.

The divider may include: an aircraft information input unit for inputting shape information of each of the aircraft and information on on-board equipment mounted on each of the aircraft; and a derived model definition unit for defining a derivative model according to the shape information and the on-board equipment information input to the aircraft information input unit.

The calculator may include: a parts information input unit for inputting part information of each of the constituent parts and information on equipment mounted on each of the derived models; a parts comparison unit for comparing the component parts with the mounted equipment mounted on each of the derived models by using the information input to the parts information input unit; and a calculation unit for calculating the number of components not mounted on each of the derived models by summing the number of components not mounted on each of the derived models.

The selector includes: a scoring unit for analyzing each of the derived models and calculating a score indicating complexity for each derived model; and a selection unit for comparing the scores calculated by the scoring unit and selecting a derivative model having the highest score as a tense.

The scoring unit may include: an equipment scoring unit for calculating an equipment score for each derived model according to the number of non-mounted units of each of the derived models and the number of equipment mounted on each of the derived models; a structural scoring unit for modeling each of the derived models and calculating a structural score according to the structural analysis result for each derived model; a location scoring unit for calculating a location score for each derived model according to the number of times that another derived model and the location at which the additional equipment is added overlap; an electric load scoring unit for calculating a load score according to an increase in electric load due to the addition of the additional equipment for each derivative model; and a summing unit for summing the equipment score, the structure score, the location score, and the load score for each derived model.

The scoring unit further includes a weight applying unit for applying different weights to each of the equipment score, the structure score, the location score, and the load score according to a preset condition.

The selector further includes a display unit for visually displaying the derived models selected by the selector and the derived models arranged in the order of the calculated scores.

The aircraft are modified differently according to mission characteristics, and the aircraft of the similar group include aircraft of the same type.

The present invention is a process of classifying aircraft of similar groups into different derived models according to mission characteristics; a process of checking whether or not the components necessary to operate the additional equipment to be added to the aircraft are mounted for each derivative model, and calculating the number of unmounted components for each derivative model; The process of selecting a derivative model to be used as a prototype according to the number of non-mounted units; The process of loading additional equipment on the selected prototype and conducting tests and operational evaluations; And if the prototype passes the test and operation evaluation, the process of loading additional equipment on the aircraft not selected as the prototype; includes.

The process of classifying the aircraft into different derivative models according to mission characteristics may include: acquiring shape information of each of the aircraft and information on on-board equipment mounted on each of the aircraft; and defining a derivative model according to the shape information and the on-board equipment information.

The process of obtaining the shape information and the on-board equipment information may include a process of three-dimensionally scanning the external appearance of each of the aircraft; and a process of confirming the production and modification history of each of the aircraft.

The process of calculating the number of non-mounted components of the non-mounted components for each derived model may include: obtaining part information of each of the component parts and information on equipment mounted on each of the derived models; a process of comparing a list of on-board equipment mounted on each of the derivative models with a list of the components; and calculating the number of non-mounted parts for each derived model by summing the number of components not mounted on each of the derived models.

The process of selecting a derived model to be used as the tense includes: analyzing each of the derived models and assigning a score indicating the complexity to each derived model; and a process of comparing the scores of the derived models and selecting the derived model having the highest score as the tense.

The process of assigning a score indicating the complexity to each derived model includes: assigning an equipment score to each of the derived models according to the number of non-mounted models of each of the derived models and the number of on-board equipment loaded in each of the derived models; a process of modeling each of the derived models and assigning a structural score to each of the derived models according to the results of structural analysis; a process of assigning a location score to each of the derived models according to the number of times that another derived model and the location at which the additional equipment is added overlap; a process of assigning a load score to each of the derived models according to an increase in electrical load due to the addition of the additional equipment; and adding up the equipment score, the structure score, the location score, and the load score for each derived model.

The step of assigning the equipment score may include: assigning a first equipment score having a larger value in the order of the number of unmounted numbers being greater; a process of assigning a second equipment score having a larger value in the order in which a lot of on-board equipment capable of interworking with the additional equipment is mounted; and a process of giving a third equipment score of a larger value in the order of the number of mounted equipment.

The process of assigning the structural score may include: assigning a first structural score according to whether or not structural reinforcement of each of the derived models due to the additional equipment is required; a process of giving a second structure score according to whether the weight balance of each of the derived models is changed due to the additional equipment; a process of giving a third structure score according to a change in the total weight of each of the derived models due to the additional equipment; and a process of assigning a fourth structure score according to whether the wiring structure of each of the derived models is changed due to the additional equipment.

The process of assigning the load score may include calculating a load difference by subtracting the maximum allowable electric load of each of the derived models from the sum of the electric loads of the on-board equipment mounted on each of the derived models and the additional equipment; and a process of assigning a load score having a larger value according to the order in which the load difference is increased.

Before adding up the equipment score, the structure score, the location score, and the load score for each derivative model, the equipment score, the structure score, the location score, and the load score are different from each other according to a preset condition. The process of applying a weight; further includes.

After selecting the derived model having the highest score as a tense, the method further includes the process of visually displaying the selected derived model and the ranking of the derived models arranged in the order of the calculated scores higher.

According to embodiments of the present invention, an aircraft having the highest complexity among aircraft of the same type may be selected as a prototype. Accordingly, since other aircraft have relatively lower complexity than the prototype, a problem may not occur during operation even if the performance of other aircraft is improved based on the prototype. Accordingly, performance improvement of the entire aircraft can be stably performed. In addition, since the performance improvement structure of other aircraft is also included in the performance improvement design range of the aircraft with the highest complexity, it is possible to efficiently perform performance improvement by saving the resources (time or cost) required for the performance improvement design of other aircraft. can

1 is a view showing the structure of a prototype selection device according to an embodiment of the present invention.
2 is a flowchart illustrating a method for improving aircraft performance according to an embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in more detail with reference to the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but will be implemented in various different forms, and only these embodiments allow the disclosure of the present invention to be complete, and the scope of the invention to those of ordinary skill in the art completely It is provided to inform you. In order to explain the invention in detail, the drawings may be exaggerated, and like reference numerals refer to like elements in the drawings.

1 is a view showing the structure of a prototype selection device according to an embodiment of the present invention. Hereinafter, a prototype selection device according to an embodiment of the present invention will be described.

The prototype selection device is a device for selecting a derivative model to be used as a prototype (or reference aircraft) among aircraft of the same type. Referring to FIG. 1 , the prototype selection device 100 includes a classifier 110 , a calculator 120 , and a selector 140 .

The classifier 110 may classify aircraft of similar groups into different derivative models according to mission characteristics. Aircrafts of a similar group may be aircraft of the same type. Even aircraft of the same type can be modified differently depending on mission characteristics. Accordingly, the shape of the aircraft may be partially changed due to the modification, or the type of equipment mounted on the aircraft may be changed. Therefore, by analyzing the aircraft with the classifier 110, it is possible to classify the aircraft into different derivative models. The classifier 110 includes an aircraft information input unit 111 and a model definition unit 112 .

The aircraft information input unit 111 may receive shape information of each of the aircraft and information on on-board equipment mounted on each of the aircraft. For example, shape information can be obtained by three-dimensionally scanning the appearance of each aircraft, and on-board equipment information can be obtained by checking the production and remodeling history of each of the aircraft, and then input to the aircraft information input unit 111. .

The derivative model definition unit 112 may be connected to send and receive signals to and from the aircraft information input unit 111 . Accordingly, the derived model definition unit 112 may define the derived model according to the shape information and the on-board equipment information input to the aircraft information input unit 111 . For example, after comparing the shapes of aircraft using shape information, aircraft with different shapes are classified into different derivative models, or after comparing the payloads mounted on aircraft using payload information Aircraft can be divided into different derivative models. In addition, aircraft having the same shape and the same payload equipment can be classified as one derivative model. Therefore, even aircraft of the same type may be modified according to mission characteristics and classified into different derivative models.

The calculator 120 may be connected to send and receive signals to and from the classifier 110 . The calculator 120 may check whether the components necessary for operating additional equipment to be added to the aircraft are mounted for each derivative model, and calculate the unmounted number of components that are not mounted for each derivative model. The calculator 120 includes a parts information input unit 121 , a parts comparison unit 122 , and a calculation unit 123 .

The parts information input unit 121 may be connected to exchange signals with the derived model definition unit 112 . Accordingly, the parts information input unit 121 arranges the on-board equipment information input to the aircraft information input unit 111 for each derived model classified by the derived model definition unit 112, so that the on-board equipment information for each derived model can be obtained. there is. In addition, it is possible to check the part information of each of the components necessary to operate the additional equipment and input it to the parts information input unit 121 .

The parts comparing unit 122 may be connected to send and receive signals to and from the parts information input unit 121 . Accordingly, the parts comparison unit 122 may use the information input to the parts information input unit 121 to compare the component parts with the equipment mounted on each of the derived models. For example, it is possible to compare a list of mounted equipment mounted on each of the derivative models and a list of components. Accordingly, it can be checked whether or not a component already mounted as a mounting device among the component parts is present in each of the derived models.

The calculator 123 may be connected to the parts comparator 122 to send and receive a signal. Accordingly, the calculator 123 may receive a list of components not included in each of the derived models from the parts comparison unit 122 . Accordingly, the calculator 123 may calculate the number of non-mounted parts for each derived model by summing the number of components not mounted on each of the derived models.

Meanwhile, as shown in FIG. 1 , the prototype selection device 100 may further include a structure analyzer 130 . The structural analyzer 130 may perform structural analysis after modeling the shape in which additional equipment is mounted in each of the derived models by using the shape information of each of the aircraft input to the aircraft information input unit 111 . In addition, the structural analyzer 130 may calculate the weight balance and weight change of the aircraft after the additional equipment is mounted for each derivative model.

The selector 140 may be connected to send and receive signals to and from the calculator 120 and the structure analyzer 130 . The selector 140 may select a derived model to be used as a prototype according to the number of unmounted units calculated by the calculator 120 . The selector 140 includes a scoring unit 141 and a selector 142 .

The scoring unit 141 may analyze each of the derived models to calculate a score indicating complexity for each derived model. The complexity means the complexity of the structure or configuration of the derived model, and the higher the complexity, the higher the difficulty of mounting additional equipment. The scoring unit 141 includes an equipment scoring unit 141a, a structure scoring unit 141b, a location scoring unit 141c, an electric load scoring unit 141d, and a summing unit 141e.

The equipment scoring unit 141a may be connected to the calculator 123 to send and receive signals. The equipment scoring unit 141a may calculate an equipment score according to the number of non-mounted models of each of the derived models and the number of equipment mounted on each of the derived models for each derived model. For example, the equipment scoring unit 141a assigns a large value of equipment score to the derived models in the order of the number of unmounted numbers, or gives a large value to the derived models in the order in which the number of on-board equipment interlocking with additional equipment is mounted. Equipment points can be given, or a large value of equipment points can be given to derived models in the order of the number of mounted equipment.

The structure scoring unit 141b may be connected to the structure analyzer 130 to send and receive signals. Accordingly, the structure scoring unit 141b may model each of the derived models and calculate a structure score according to the structural analysis result for each derived model. For example, the structure scoring unit 141b assigns a structure score to the derived models depending on whether structural reinforcement is required due to the additional equipment, or provides a structure to the derived models according to whether the weight balance and the total weight due to the additional equipment change. Scores can be given, or structural points can be given to derived models depending on whether the wiring structure is changed due to additional equipment.

The location scoring unit 141c may calculate a location score for each derived model according to the number of times that another derived model and a location where additional equipment is added overlap. In other words, since the location where additional equipment is mounted may vary depending on the structure of the derived model, it is possible to give the location score of a large value to the derived models in the order of the number of overlapping locations where other derived models and additional equipment are installed. can

The electric load scoring unit 141d may calculate a load score according to an increase in electric load due to the addition of additional equipment for each derived model. That is, the electric load scoring unit 141d calculates the load difference by subtracting the maximum allowable electric load of each of the derived models from the sum of the electric loads of the on-board equipment and the additional equipment of each of the derived models, and the greater the load difference, the greater the number of derived models. can be given a large load score.

The summing unit 141e may be connected to the equipment scoring unit 141a, the structure scoring unit 141b, the location scoring unit 141c, and the electric load scoring unit 141d to send and receive signals. Accordingly, the summing unit 141e may sum the equipment score, the structure score, the location score, and the load score for each derived model.

Meanwhile, as shown in FIG. 1 , the scoring unit 141 may further include a weight applying unit 141f. The weight application unit 141f may apply different weights to each of the equipment score, the structure score, the location score, and the load score according to a preset condition. For example, when the user determines that the equipment score is a relatively important factor and the load score is a relatively insignificant factor, the weight application unit 141f applies a relatively large weight to the equipment score to make it relatively It is possible to increase the value and decrease the value relatively by applying a relatively low weight to the load score. Also, the weight application unit 141f may transmit the weighted scores to the summation unit 141e, and the summation unit 141e may add the weighted scores.

The selection unit 142 may be connected to the scoring unit 141 to send and receive signals. Accordingly, the selection unit 142 may compare the scores of the derived models that are summed and calculated by the summation unit 141e. Accordingly, the selection unit 142 may select the derived model having the highest summed score as the tense.

Meanwhile, as shown in FIG. 1 , the selector 140 may further include a display unit 143 . For example, the display unit 143 may be a display. Accordingly, the display unit 143 may display the derivative model selected by the selection unit 142 to the user. The user may select a derivative model displayed on the display unit 143 to mount the on-board equipment and perform a test and operational evaluation. Also, the display unit 143 may visually display the rankings of the derived models arranged in the order of the calculated scores. Therefore, if the test and operation evaluation cannot be performed by mounting the on-board equipment on the derivative model selected as the first priority due to the work schedule, etc. .

As such, the aircraft with the highest complexity among the plurality of aircraft can be selected as the prototype. Therefore, since other aircraft have relatively lower complexity than the prototype, problems may not occur during operation even if the performance of other aircraft is improved based on the prototype. Accordingly, performance improvement of the entire aircraft can be stably performed. In addition, since the performance improvement structure of other aircraft is also included in the performance improvement design range of the aircraft with the highest complexity, it is possible to efficiently perform performance improvement by saving the resources (time or cost) required for the performance improvement design of other aircraft. can

2 is a flowchart illustrating a method for improving aircraft performance according to an embodiment of the present invention. Hereinafter, a method for improving aircraft performance according to an embodiment of the present invention will be described.

The aircraft performance improvement method is to select a derivative model to be used as a prototype among the aircraft, perform system design based on the prototype, mount the on-board equipment on the prototype according to the design, perform tests and operational evaluation, and then perform tests and operational evaluations of the remaining aircraft for performance improvement. It is a method of mounting additional equipment on the whole. 2, the aircraft performance improvement method is a process of classifying aircraft of similar groups into different derivative models according to mission characteristics (S110), and whether or not the components necessary to operate additional equipment to be added to the aircraft are mounted. The process of checking for each derivative model and calculating the number of unmounted components for each derived model (S120), the process of selecting a derivative model to be used as a prototype according to the number of unmounted models (S130), and mounting additional equipment on the selected prototype And, the process of performing the test and operational evaluation (S140), and if the prototype passes the test and operation evaluation, it includes a process (S150) of loading additional equipment on the aircraft not selected as the prototype.

At this time, the process of classifying aircrafts of similar groups into different derivative models according to mission characteristics, checking whether the components necessary to operate additional equipment to be added to the aircraft are installed for each derivative model, and The process of calculating the unmounted number for each derived model, and the process of selecting a derived model to be used as a prototype according to the unmounted number may be performed by the prototype selection device 100 according to an embodiment of the present invention having the structure as shown in FIG. 1 . there is. However, the present invention is not limited thereto and may be performed in various ways.

First, aircraft of similar groups are divided into different derived models according to mission characteristics (S110). To this end, shape information of each of the aircraft and information on the on-board equipment mounted on each of the aircraft may be obtained. The shape information can be obtained by three-dimensional scanning the appearance of each of the aircraft, and the on-board equipment information can be obtained by checking the production and remodeling history of each of the aircraft. The process of three-dimensionally scanning the external appearance of the aircraft and the process of confirming the manufacturing and remodeling histories of the aircraft may be performed simultaneously or in a different order. In addition, a derived model can be defined according to shape information and on-board equipment information. For example, after comparing the shapes of aircraft using shape information, aircraft with different shapes are classified into different derivative models, or after comparing the payloads mounted on aircraft using payload information Aircraft can be divided into different derivative models. Therefore, even aircraft of the same type may be modified according to mission characteristics and classified into different derivative models.

Then, it is checked for each derived model whether the components necessary to operate the additional equipment to be added to the aircraft are mounted, and the number of unmounted components that are not mounted is calculated for each derived model (S120). Even if the aircraft is of the same type, the payload equipment mounted on each derivative model may be different. Accordingly, in some of the derivative models, the components for operating the additional equipment may be already loaded as the on-board equipment, and the types of the components mounted as the on-board equipment for each derivative model may be different. Accordingly, it is possible to check the type and number of component parts not mounted for each derivative model.

To this end, it is possible to obtain part information of each of the component parts and information on the equipment mounted on each of the derived models. Information on parts of components can be obtained by checking the specifications of additional equipment, and information on on-board equipment can be obtained by checking the production and modification history of each aircraft.

In addition, using the two pieces of information, it is possible to compare the on-board equipment and components mounted on each of the derived models. For example, a list of payload equipment mounted on each of the derived models may be compared with a list of components. Accordingly, it is possible to check whether or not there are already mounted components among the components for each derived model. After comparing the two lists, it is possible to calculate the number of unmounted parts for each derived model by adding up the number of components not mounted for each derived model.

Next, a derived model to be used as a prototype is selected according to the number of non-mounted units (S130). That is, the process for selecting the derivative model with the highest complexity as the tense can be performed.

To this end, by analyzing each of the derived models, a score indicating the complexity of each derived model may be assigned. Scores may include equipment scores, rescue scores, location scores, and load scores.

Equipment points may be given to each of the derived models according to the number of non-mounted models of each of the derived models and the number of equipment mounted on each of the derived models. For example, by comparing the number of unmounted models of the derived models, a first equipment score having a larger value may be given in the order of the number of unmounted models being greater, and a first equipment score having a smaller value may be given as the number is smaller. By comparing the number of on-board equipment that can be interlocked with additional equipment in each of the derived models, a second equipment score with a higher value may be given in the order in which it is most loaded, and a second equipment score with a smaller value may be given as the number is smaller. By comparing the number of on-board equipment mounted on each of the derived models, a third equipment score with a larger value may be given in the order of the number, and a third equipment score with a smaller value may be given as the number is smaller. The first equipment score, the second equipment score, and the third equipment score may be summed for each derived model to calculate an equipment score for each derived model.

The structural score may be given to each of the derived models according to the results of structural analysis by modeling the shape of each of the derived models. In other words, it is possible to model a shape in which additional equipment is mounted on each of the derived models, conduct a structural analysis, and calculate a structural score according to the result. For example, a relatively large first structural score is given to a derived model that is judged to require structural reinforcement due to additional equipment, and a relatively small first structural score is assigned to a derived model judged that structural reinforcement is not necessary. can be given In the case of a derivative model with a large fluctuation in weight balance due to additional equipment, a relatively large second structure score may be given, and in the case of a derivative model with a small weight balance fluctuation, a relatively small second structure score may be given. In the case of a derivative model with a large change in total weight due to additional equipment, a relatively large third structure score may be given, and as the total weight change is small, a relatively small third structure score may be given. In the case of a derivative model with a large amount of change in the wiring structure due to additional equipment, a relatively large fourth structure score may be given, and in the case of a derivative model with a small amount of change in the wiring structure, a relatively small fourth structure score may be given. The first structural score, the second structural score, the third structural score, and the fourth structural score may be summed for each derived model to calculate a structural score for each derived model.

A location score can be given to each of the derived models according to the number of times that other derived models and the locations where additional equipment is added overlap. In other words, since the location where additional equipment is mounted may vary depending on the structure of the derived model, a location score with a large value is given to the derived models in the order of the number of overlapping locations where other derived models and additional equipment are installed. , the smaller the number of overlapping, the smaller the position score can be given.

As for the load score, a load score may be given to each of the derived models according to an increase in electrical load due to the addition of additional equipment. The load difference is calculated by subtracting the maximum allowable electric load of each of the derived models from the sum of the electric loads of the on-board equipment and the additional equipment of each of the derived models, and the greater the load difference, the greater the load score is given to the derived models, The smaller the load difference, the smaller the load score can be given.

When the equipment score, the structure score, the location score, and the load score are calculated, the equipment score, the structure score, the location score, and the load score can be summed for each derived model. Accordingly, the summed score for each derived model can be calculated.

Meanwhile, before adding up the equipment score, the structure score, the location score, and the load score for each derived model, different weights may be applied to each of the equipment score, the structure score, the location score, and the load score according to a preset condition. For example, if the user determines that the equipment score is a relatively important factor and the load score is a relatively insignificant factor, a relatively large weight is applied to the equipment score to increase the value relatively, and the load score is It is possible to reduce the value relatively by applying a relatively low weight to . In this case, by adding up the weighted scores, a score for each derived model can be calculated.

When the summed score is calculated for each derived model, the scores of the derived models can be compared. Therefore, the order of the derived models can be sorted in the order of the largest score, and the derived model having the largest score can be selected as the tense.

In this case, after selecting the aircraft of the derived type having the highest score as the prototype, the ranking of the selected derived model and the derived models arranged in the order of the calculated scores may be visually displayed to the user. Accordingly, the user can easily check the selected derivative model. In addition, if the test and operation evaluation cannot be performed by mounting the on-board equipment to the first-priority derivative model due to the work schedule, etc., the second-priority selected derivative model is selected and the on-board equipment is mounted to perform the test and operation evaluation. may be

Then, after designing the performance improvement structure based on the prototype (or designing the mounting location or mounting structure for mounting the on-board equipment and unmounted components), the additional equipment is mounted on the selected prototype, and the test and Operational evaluation is performed (S140). At this time, airworthiness certification of the prototype may also be performed. Therefore, it is possible to check the stability of the performance improvement of the aircraft.

Then, when the prototype passes the test and operation evaluation, additional equipment is mounted on the aircraft not selected as the prototype (S150). At this time, since the prototype has higher complexity than other aircraft, the test and evaluation of other aircraft can be replaced by using the evaluation result of the prototype, and airworthiness certification of other aircraft can be obtained by using the airworthiness certification information of the prototype. Accordingly, since it is possible to rapidly improve the performance of the entire aircraft, it is possible to shorten the development schedule for the overall performance improvement of the aircraft.

As such, the aircraft with the highest complexity among the plurality of aircraft can be selected as the prototype. Therefore, since other aircraft have relatively lower complexity than the prototype, problems may not occur during operation even if the performance of other aircraft is improved based on the prototype. Accordingly, performance improvement of the entire aircraft can be stably performed. In addition, since the performance improvement structure of other aircraft is also included in the performance improvement design range of the aircraft with the highest complexity, it is possible to efficiently perform performance improvement by saving the resources (time or cost) required for the performance improvement design of other aircraft. can

As such, although specific embodiments have been described in the detailed description of the present invention, various modifications are possible without departing from the scope of the present invention, and various combinations between the embodiments are possible. Therefore, the scope of the present invention should not be limited to the described embodiments, but should be defined by the claims to be described below as well as the claims and equivalents.

100: prototype selection device 110: divider
120: calculator 130: structure analyzer
140: selector 141: scoring unit
142: selection unit 143: display unit

Claims (19)

a classifier for classifying aircraft of similar groups into different derived models according to mission characteristics;
a calculator for checking whether the components necessary to operate the additional equipment to be added to the aircraft are mounted for each derivative model, and calculating the number of unmounted components for each derivative model; and
Including; a selector for selecting a derivative model to be used as a prototype according to the number of non-mounted units;
The calculator is
A parts information input unit for inputting part information of each of the constituent parts and information on equipment mounted on each of the derivative models;
A parts comparison unit for comparing the component parts with the mounted equipment mounted on each of the derived models by using the information input to the parts information input unit, and
Prototype selection device including a calculation unit for summing the number of components not mounted in each of the derived models, and calculating the number of non-mounted parts for each derived model. The method according to claim 1,
The separator is
an aircraft information input unit for inputting shape information of each of the aircraft and information on equipment mounted on each of the aircraft; and
A prototype selection device comprising a; a derivative model definition unit for defining a derivative model according to the shape information and the on-board equipment information input to the aircraft information input unit. delete a classifier for classifying aircraft of similar groups into different derived models according to mission characteristics;
a calculator for checking whether the components necessary to operate the additional equipment to be added to the aircraft are mounted for each derivative model, and calculating the number of unmounted components for each derivative model; and
Including; a selector for selecting a derivative model to be used as a prototype according to the number of non-mounted units;
The selector is
A scoring unit for analyzing each of the derived models to calculate a score indicating the complexity for each derived model, and
and a selection unit for comparing scores calculated by the scoring unit and selecting a derivative model having the highest score as a tense tense. 5. The method according to claim 4,
The scoring unit,
an equipment scoring unit for calculating an equipment score for each derived model according to the number of the non-mounted number of each of the derived models and the number of equipment mounted on each of the derived models;
a structural scoring unit for modeling each of the derived models and calculating a structural score according to the structural analysis result for each derived model;
a location scoring unit for calculating a location score for each derived model according to the number of times that another derived model and the location at which the additional equipment is added overlap;
an electric load scoring unit for calculating a load score according to an increase in electric load due to the addition of the additional equipment for each derivative model; and
Prototype selection device comprising a; a summation unit for summing the equipment score, the structure score, the location score, and the load score for each derivative model. 6. The method of claim 5,
The scoring unit,
and a weight application unit for applying different weights to each of the equipment score, the structure score, the location score, and the load score according to a preset condition. 5. The method according to claim 4,
The selector is
The tense selection device further comprising a display unit for visually displaying the derived models selected by the selection unit and the rankings of the derived models arranged in the order of the calculated scores. 8. The method according to any one of claims 1, 2, and 4 to 7,
The aircraft were modified differently depending on the mission characteristics,
The aircraft of the similar group is a prototype selection device including aircraft of the same type. The process of classifying aircraft of similar groups into different derivative models according to mission characteristics;
The process of checking whether the components necessary for operating the additional equipment to be added to the aircraft are mounted for each derivative model, and calculating the number of unmounted components for each derivative model;
The process of selecting a derivative model to be used as a prototype according to the number of non-mounted units;
The process of loading additional equipment on the selected prototype and conducting tests and operational evaluations; and
When the prototype passes the test and operation evaluation, the process of loading additional equipment on the aircraft not selected as the prototype; Aircraft performance improvement method comprising a. 10. The method of claim 9,
The process of classifying the aircraft into different derivative models according to mission characteristics is,
obtaining shape information of each of the aircraft and information on on-board equipment mounted on each of the aircraft; and
Aircraft performance improvement method including; defining a derivative model according to the shape information and the on-board equipment information. 11. The method of claim 10,
The process of acquiring the shape information and the on-board equipment information is,
a process of three-dimensionally scanning the external appearance of each of the aircraft; and
Aircraft performance improvement method including; 10. The method of claim 9,
The process of calculating the number of non-mounted components that are not mounted for each derived model is,
obtaining part information of each of the constituent parts and information on equipment mounted on each of the derivative models;
a process of comparing a list of on-board equipment mounted on each of the derivative models with a list of the components; and
Aircraft performance improvement method comprising; summing the number of component parts not mounted in each of the derived models, and calculating the number of non-mounted parts for each derived model. 10. The method of claim 9,
The process of selecting a derivative model to be used as the tense is,
a process of analyzing each of the derived models and assigning a score indicating the complexity to each derived model; and
A method of improving aircraft performance, including a process of comparing the scores of the derived models, and selecting the derived model with the highest score as the tense. 14. The method of claim 13,
The process of assigning a score indicating the complexity to each derived model is,
a process of giving equipment points to each of the derived models according to the number of non-mounted models of each of the derived models and the number of equipment mounted on each of the derived models;
A process of modeling each of the derived models and assigning a structure score to each of the derived models according to the results of structural analysis;
a process of assigning a location score to each of the derived models according to the number of times that another derived model and the location at which the additional equipment is added overlap;
a process of assigning a load score to each of the derived models according to an increase in electric load due to the addition of the additional equipment; and
and adding the equipment score, the structure score, the location score, and the load score to each of the derived models. 15. The method of claim 14,
The process of giving the equipment points is,
a process of giving a first equipment score of a larger value in the order of the number of unmounted numbers;
a process of assigning a second equipment score having a larger value in the order in which a lot of on-board equipment capable of interworking with the additional equipment is mounted; and
Aircraft performance improvement method including; 15. The method of claim 14,
The process of giving the structure score is:
a process of giving a first structural score according to whether structural reinforcement is necessary for each of the derived models due to the additional equipment;
a process of giving a second structure score according to whether the weight balance of each of the derived models is changed due to the additional equipment;
a process of giving a third structure score according to a change in the total weight of each of the derived models due to the additional equipment; and
Aircraft performance improvement method including; 15. The method of claim 14,
The process of assigning the load score is
calculating a load difference by subtracting the maximum allowable electric load of each of the derived models from the sum of the electric loads of the on-board equipment mounted on each of the derived models and the additional equipment; and
Aircraft performance improvement method comprising a; the process of assigning a load score of a large value in the order in which the load difference is large. 15. The method of claim 14,
Before summing the equipment score, the structure score, the location score, and the load score for each derivative model,
and applying different weights to each of the equipment score, the structure score, the location score, and the load score according to a preset condition. 14. The method of claim 13,
After selecting the derivative model with the highest score as the tense,
Aircraft performance improvement method further comprising the process of visually displaying the selected derived model, and the ranking of the derived models sorted in the order of the calculated score.

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