KR102376362B1 - System and method for designing optimization algorithm for determining integrity of aircraft structural - Google Patents

Abstract

Disclosed are a system and method for designing an optimization algorithm for judging the soundness of an aircraft structure. The present invention can design and provide an optimized algorithm capable of determining the structural integrity of an aircraft using flight tests and learning.

Description

SYSTEM AND METHOD FOR DESIGNING OPTIMIZATION ALGORITHM FOR DETERMINING INTEGRITY OF AIRCRAFT STRUCTURAL

The present invention relates to a system and method for designing an optimization algorithm for determining the soundness of an aircraft structure, and more particularly, designing an optimization algorithm for determining the soundness of an aircraft structure using flight tests and learning to determine the soundness of an aircraft structure It relates to systems and methods.

Recently, structural development using composite materials is rapidly advancing centered on the development of aircraft, where weight reduction is the most important, and is in the stage of being applied to other ground vehicles and infrastructure as a ripple effect.

As a recent research trend for securing reliability in structural design using composite materials, technical research is being conducted that can check and monitor reliability whenever necessary throughout the entire operating period using direct sensors rather than an approach based on theoretical predictions. there is.

This field is called Health and Usage Monitoring System (HUMS, health and operability monitoring system), and in particular, the system technology in which sensors are installed and integrated in structures limited to structures is called Structural Health Monitoring (SHM, structural health monitoring system). do.

Domestic aircraft development is being actively carried out in various fields such as weight reduction, modularization, and localization of parts.

In particular, since the weight reduction of the aircraft has a very large effect on the operation of the aircraft, it is a field of great utility.

In order to realize the weight reduction of the aircraft, a method to apply a composite material with superior specific strength and specific stiffness compared to the existing metal is being studied. The gas structure is being developed using

However, for structures made of composite materials, it is essential to evaluate the quality of the finished product along with deterioration of physical properties due to defects that may occur during manufacturing.

For example, the Boeing 787 is being used in manufacturing by conducting a full inspection of parts for composite materials.

In addition, delamination and debonding can easily occur due to various causes such as repeated loads generated during operation and impacts from external objects.

In addition, heterojunctions between composites and metals are classified as structural hot spots, where damage is always predicted as a member of an innovative joining method.

Moreover, damage to the composite material is difficult to distinguish with the naked eye, and there is no damage in the impacted part and serious damage to the inside or the opposite side often occurs. In many cases, the existing non-destructive testing methods for metal materials are ineffective due to their nature.

Accordingly, there is a need for an optimization program for selecting and acquiring data necessary for determining the structural integrity of an aircraft among data sensed by a structure during flight of an aircraft, analyzing the acquired data, and determining the same.

Korean Patent Publication No. 10-1586039 (Title of the Invention: Aircraft Complex Structure Diagnosis System and Method)

In order to solve this problem, an object of the present invention is to provide an optimization algorithm design system and method for judging the soundness of an aircraft structure by using flight tests and learning to determine the soundness of the aircraft structure.

In order to achieve the above object, an embodiment of the present invention is an optimization algorithm design system for determining the soundness of an aircraft structure, the flight form of the aircraft obtained based on a preset scenario, and the flight form and the aircraft structure during the flight. When the flight test data required to determine the soundness of the applied aircraft structure is input, the input flight test data is stored, the input flight test data is classified according to preset data using an artificial intelligence model, and the classified It includes an algorithm modeling unit that synchronizes flight test data according to the flight state and flight type of the aircraft to generate an algorithm for determining the soundness of the aircraft structure.

In addition, the scenario according to the embodiment includes damage data, impact data and deformation data required for determining the soundness of an aircraft structure in an algorithm for determining the soundness of a structure, navigation data including flight posture, position, and speed, and aircraft data. It is characterized in that it is design information for acquiring at least one or more.

In addition, the embodiment is at least one or more of damage data, impact data and deformation data required for soundness determination of an aircraft structure in an algorithm for determining the soundness of a structure, navigation data including flight posture, position, and speed, and aircraft data a design data input unit for setting a scenario including; a sensor management unit that is installed in the aircraft and acquires flight test data based on the scenario; and storing the obtained flight test data, classifying the flight test data by preset data using an artificial intelligence model, and synchronizing the classified data according to the flight status of the aircraft and the flight type to ensure the health of the aircraft structure and an algorithm modeling unit that generates an algorithm for determination.

In addition, the algorithm according to the embodiment synchronizes the classified flight test data according to the flight state and flight form of the aircraft, and based on the deformation size of the wing, cracks, bolt loosening, impact size, impact location, and impact time data, aircraft structure It is characterized by judging the soundness of

In addition, an embodiment of the present invention provides an optimization algorithm design method for determining the soundness of an aircraft structure, comprising: a) designing a scenario required for the soundness determination of the aircraft structure by a design data input unit; b) obtaining, by the algorithm modeling unit, flight test data based on the designed scenario from the sensor management unit installed in the aircraft; c) learning based on the flight test data obtained by the algorithm modeling unit; and d) designing an algorithm based on the learning result by the algorithm modeling unit.

In addition, the above embodiment is characterized in that the scenario designed in step a) sets data acquisition information based on the flight status and flight form of the aircraft to obtain data necessary for designing the structure soundness algorithm.

In addition, the flight test data of step b) according to the above embodiment is data obtained through flight conducted according to the flight status and flight type of the aircraft set in the scenario to obtain data necessary for designing the structure soundness algorithm. do it with

In addition, the learning of step c) according to the above embodiment is characterized in that the learning model is built and learned according to the flight state of the aircraft and the flight form in order to acquire data necessary for designing the structure soundness algorithm.

In addition, in the embodiment, the algorithm generated in step d) stores the obtained flight test data, classifies the flight test data by preset data using an artificial intelligence model, and divides the classified data into flight of the aircraft. It is characterized in that the soundness of the aircraft structure is determined by synchronizing it according to the state and the flight type.

In addition, in the above embodiment, e) the algorithm modeling unit additionally acquires flight test data from the aircraft in which the algorithm generated in step d) is installed, and supplementing the algorithm through analysis and learning based on the additionally acquired flight test data It is characterized in that it further includes;

In addition, the embodiment is characterized in that it further comprises; changing the scenario based on the algorithm supplemented by the algorithm modeling unit.

The present invention has the advantage of being able to provide an optimization algorithm for determining the health of an aircraft structure that uses flight tests and learning to determine the health of the aircraft structure.

1 is a block diagram illustrating an optimization algorithm design system for determining the soundness of an aircraft structure according to an embodiment of the present invention.
FIG. 2 is a block diagram illustrating a configuration of a sensor management unit of an optimization algorithm design system for determining the soundness of an aircraft structure according to the embodiment of FIG. 1 .
3 is an exemplary view for explaining the operation of the optimization algorithm design system for determining the soundness of the aircraft structure according to the embodiment of FIG.
4 is a flowchart illustrating an optimization algorithm design process for determining the soundness of an aircraft structure according to an embodiment of the present invention.
5 is a flowchart illustrating a scenario design process in the optimization algorithm design process for determining the soundness of an aircraft structure according to the embodiment of FIG. 4 .
6 is a flowchart illustrating a learning process in the design process of an optimization algorithm for determining the soundness of an aircraft structure according to the embodiment of FIG. 4 .
7 is a flowchart illustrating an algorithm design process in an optimization algorithm design process for determining the soundness of an aircraft structure according to the embodiment of FIG. 4 .

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, the present invention will be described in detail with reference to preferred embodiments of the present invention and the accompanying drawings.

Prior to describing the specific content for carrying out the present invention, it should be noted that components not directly related to the technical gist of the present invention are omitted within the scope of not disturbing the technical gist of the present invention.

In addition, the terms or words used in the present specification and claims have meanings and concepts consistent with the technical idea of the invention based on the principle that the inventor can define the concept of an appropriate term to best describe his invention. should be interpreted as

In the present specification, the expression that a part "includes" a certain element does not exclude other elements, but means that other elements may be further included.

Also, terms such as “… unit”, “… group”, and “… module” mean a unit that processes at least one function or operation, which may be divided into hardware, software, or a combination of the two.

In addition, the term "at least one" is defined as a term including the singular and the plural, and even if the term at least one does not exist, each element may exist in the singular or plural, and may mean the singular or plural. will be self-evident.

In addition, that each component is provided in singular or plural may be changed according to an embodiment.

Hereinafter, a preferred embodiment of an optimization algorithm design system and method for determining the soundness of an aircraft structure according to an embodiment of the present invention will be described in detail with reference to the accompanying drawings.

1 is a block diagram illustrating an optimization algorithm design system for determining the soundness of an aircraft structure according to an embodiment of the present invention, and FIG. 2 is an optimization algorithm design system for determining the soundness of an aircraft structure according to the embodiment of FIG. It is a block diagram showing the configuration of the sensor management unit, and FIG. 3 is an exemplary diagram for explaining the operation of the optimization algorithm design system for determining the soundness of the aircraft structure according to the embodiment of FIG. 1 .

1 to 3 , the optimization algorithm design system for determining the soundness of an aircraft structure according to an embodiment of the present invention includes the flight form of an aircraft acquired based on a preset scenario, the flight form and during the flight. When the flight test data required to determine the soundness of the aircraft structure applied to the aircraft structure is input, the input flight test data is stored, and the input flight test data is classified according to preset data using an artificial intelligence model, A design data input unit 100, a sensor management unit 200, and an algorithm modeling unit 300 to synchronize the classified data according to the flight state and flight form of the aircraft to generate an algorithm for determining the soundness of the aircraft structure. is comprised of

The design data input unit 100 sets a scenario including at least one of damage data, impact data and deformation data required for determining the soundness of the aircraft structure, navigation data including flight posture, position, and speed, and aircraft data As a configuration to do so, it may be composed of a desktop PC, a notebook PC, a tablet PC, or a terminal capable of installing an application program for setting a scenario.

In the above scenario, the algorithm for determining the soundness of the structure determines how to fly the aircraft in order to obtain the necessary data required to determine the soundness of the aircraft structure, and accordingly, the Make it possible to properly acquire the necessary data from among the data.

That is, the scenario includes damage data, impact data, and deformation data detected during flight from a user or administrator, navigation data including flight posture of the aircraft, aircraft position, and aircraft speed, and all other aircraft signals, such as For example, it is data design information for acquiring aircraft data including altitude, bearing, engine condition, temperature, and the like.

In addition, the scenario is applied to the flight test process of the aircraft based on the designed information so that data necessary for determining the structural integrity of the aircraft can be obtained.

In addition, in the scenario, additional data design may be supplemented according to the analysis result of the data acquired through the sensor management unit 200 and the algorithm generated by the algorithm modeling unit 300 , and when the data design is completed, the aircraft can be applied to the next flight test of

The sensor management unit 200 is installed in the aircraft 400 and is configured to acquire flight test data based on a scenario designed by the design data input unit 100, and includes a structure health sensor 210, a navigation sensor 220, and an aircraft. It may be configured to include a data sensor 230 and a storage unit 240 .

The structure health sensor 210 is installed on the body portion 410 and the wing portion 420 of the aircraft, and damage data generated in the damage detection area 430 between the body portion 410 and the wing portion 420 . And, the impact data generated in the impact sensing area 440 of the wing unit 420 and the deformation data generated in the deformation sensing area 450 of the wing unit 420 are obtained.

The navigation sensor 220 is installed in the body portion 410 to obtain navigation data including the flight posture of the aircraft, the position of the aircraft, the speed of the aircraft, and the like.

The aircraft data sensor 230 is installed in the body portion 410 to obtain aircraft data including all signals of the aircraft including, for example, altitude, bearing, engine state, temperature, and the like.

The storage unit 240 stores the scenario, data obtained from the structure health sensor 210 , the navigation sensor 220 , and the aircraft data sensor 230 , and the stored data is stored in the algorithm modeling unit 300 after the flight test is completed. ) is sent to

The algorithm modeling unit 300 stores the obtained flight test data, classifies the flight test data by preset data using an artificial intelligence model, and divides the classified data according to the flight state of the aircraft and the flight type. As a configuration for generating an algorithm for determining the soundness of an aircraft structure by synchronizing, it may be configured as a server system.

Here, the artificial intelligence model can be seen as a type of analysis model created through a method called deep learning among machine learning.

Therefore, an artificial intelligence model may also be used as a representation of a deep learning model or a deep learning analysis model.

Machine learning is also an application of artificial intelligence that enables complex systems to learn and improve automatically from experience without being explicitly programmed.

Also, the accuracy and validity of machine learning models may depend in part on the data used to train those models.

In addition, the artificial intelligence model compares and analyzes the flight test data received from the sensor management unit 200 with each other based on a plurality of flight test data accumulated through the previous flight.

In addition, the artificial intelligence model may be repeatedly learned by using the flight test data received from the sensor management unit 200 through comparison and analysis as learning data, and learning may be performed by building an appropriate learning model through the repeated learning. there is.

In addition, the algorithm modeling unit 300 is the flight test data through the artificial intelligence model, damage data, impact data, deformation data detected during flight, and navigation data including the flight posture of the aircraft, the position of the aircraft, and the speed of the aircraft And, all other aircraft signals, such as aircraft data including altitude, bearing, engine condition, temperature, etc., are classified according to preset data.

In addition, the algorithm modeling unit 300 calculates the classified flight test data with flight states such as flying in place, stationary flight, ascending flight, descending flight, rotational flight, horizontal flight, and manually controlled flight, autopilot flight, programming flight, etc. An algorithm is created to determine the soundness of the aircraft structure by synchronizing the flight test data obtained according to the flight type of the aircraft.

That is, the algorithm is a program for determining the soundness of an aircraft structure, and by synchronizing the flight state and flight form of the aircraft, the damage detection area 430 and the impact detection area 440 of the body portion 410 and the wing portion 420 . , deformation and deformation size of the body detected in the deformation detection area 450, deformation and deformation size of the wing, crack generation of the body portion 410 and the wing portion 420, bolt loosening, the body portion 410 and the wing portion The soundness of the aircraft structure is determined based on the impact size, impact location, and impact time data applied to the 420 .

In addition, when the algorithm modeling unit 300 additionally acquires flight test data from the aircraft in which the generated algorithm is installed, analysis and learning are performed using an artificial intelligence model based on the additionally acquired flight test data, and the Algorithms that determine the health of aircraft structures based on analysis and learning results can be supplemented.

In addition, the algorithm modeling unit 300 changes the initially designed scenario based on the supplemented algorithm and outputs it to be reflected in the flight test. can create

The following describes a method for designing an optimization algorithm for determining the soundness of an aircraft structure according to an embodiment of the present invention.

4 is a flowchart illustrating an optimization algorithm design process for determining the soundness of an aircraft structure according to an embodiment of the present invention, and FIG. 5 is a scenario in the optimization algorithm design process for determining the soundness of an aircraft structure according to the embodiment of FIG. It is a flowchart illustrating a design process, and FIG. 6 is a flowchart illustrating a learning process in the design process of an optimization algorithm for determining the soundness of an aircraft structure according to the embodiment of FIG. 4 , and FIG. 7 is the soundness of the aircraft structure according to the embodiment of FIG. This is a flowchart showing the algorithm design process in the optimization algorithm design process for judgment.

1 to 7 , a user or manager designs a scenario by defining necessary data required to determine the soundness of an aircraft structure through the design data input unit 100 ( S100 ).

In the step S100, the design data input unit 100 selects and inputs the necessary data required to determine the soundness of the aircraft structure input by the user or the manager (S110), and creates a scenario based on the input necessary data (S120), the generated scenario is installed in the aircraft to be reflected in the flight test (S130).

Scenarios designed in steps S110 and S120 include damage data, impact data, and deformation data sensed during flight from a user or administrator, and navigation data including flight posture of the aircraft, the position of the aircraft, and the speed of the aircraft, and other aircraft It is data design information for acquiring aircraft data including all signals of, for example, altitude, bearing, engine condition, temperature, and the like.

In addition, in step S100 , when a request to change a scenario initially designed based on the algorithm supplemented by the algorithm modeling unit 300 is input, the design data input unit 100 analyzes the requested scenario change information to be reflected in the scenario. Additional can be performed (S140).

After performing step S100, when flight test data based on the designed scenario is obtained from the sensor management unit 200 installed in the aircraft (S200), the algorithm modeling unit 300 is based on the flight test data obtained in step S200. Learning (S300) is performed.

That is, in the step S300, the algorithm modeling unit 300 receives the flight test data obtained in the flight test from the sensor management unit 200 (S310),

The algorithm modeling unit 300 uses an artificial intelligence model to convert flight test data into flight test data, damage data, impact data, deformation data, and navigation data including flight posture of the aircraft, the position of the aircraft, and the speed of the aircraft, All other aircraft signals, such as aircraft data including altitude, bearing, engine condition, temperature, etc., are classified according to preset data ( S320 ).

In addition, the algorithm modeling unit 300 calculates the classified flight test data with flight states such as flying in place, stationary flight, ascending flight, descending flight, rotational flight, horizontal flight, and manually controlled flight, autopilot flight, programming flight, etc. Synchronize the flight test data obtained according to the flight form (S330).

In addition, the algorithm modeling unit 300 can compare and analyze a plurality of flight test data accumulated through a previous flight using an artificial intelligence model and the flight test data received from the sensor management unit 200 with each other, and the The artificial intelligence model repeatedly learns the flight test data received from the sensor management unit 200 as learning data through comparison and analysis (S340).

Subsequently, the algorithm modeling unit 300 performs the step (S400) of designing an algorithm based on the learning result.

In step S400, the algorithm modeling unit 300 converts the flight test data classified in step S300 to flight states such as flying in place, stationary flight, ascending flight, descending flight, rotational flight, horizontal flight, and manually controlled flight, automatically controlled flight. , an algorithm for determining the soundness of the aircraft structure is generated by synchronizing the flight test data obtained according to the flight type such as programming flight (S410).

The algorithm generated in step S410 is a program for determining the soundness of the aircraft structure, and by synchronizing the flight state and flight form of the aircraft, the damage detection area 430 and the impact detection area of the body 410 and the wing 420 are (440), deformation and deformation size of the body detected in the deformation detection area 450, deformation and deformation size of the wing, crack generation of the body portion 410 and the wing portion 420, loosening the bolt, the body portion 410 And the soundness of the aircraft structure is determined based on the impact size, impact location, and impact time data applied to the wing portion 420 .

In addition, the algorithm modeling unit 300 may additionally acquire flight test data from the aircraft in which the algorithm generated in step S410 is installed, and perform analysis and learning (S420) based on the additionally acquired flight test data. .

Also, the algorithm modeling unit 300 may additionally perform the algorithm supplementation step S430 by changing the scenario based on the algorithm supplemented through re-learning in step S420 .

That is, by reflecting and changing the supplementary algorithm generated in step S430 to the initially designed scenario, and configuring the changed scenario to be reflected in the flight test, to determine the optimal flight test data based on the changed scenario and the soundness of the aircraft structure Allows you to create algorithms.

Accordingly, it is possible to provide an optimization algorithm for determining the health of an aircraft structure that uses flight tests and learning to determine the soundness of the aircraft structure.

As described above, although described with reference to preferred embodiments of the present invention, those skilled in the art can variously modify and change the present invention within the scope without departing from the spirit and scope of the present invention described in the claims below. You will understand that it can be done.

In addition, the reference numbers described in the claims of the present invention are provided only for clarity and convenience of explanation, and are not limited thereto, and in the process of describing the embodiment, the thickness of the lines shown in the drawings or the size of components, etc. may be exaggerated for clarity and convenience of explanation.

In addition, the above-mentioned terms are terms defined in consideration of functions in the present invention, which may vary depending on the intention or custom of the user or operator, so the interpretation of these terms should be made based on the content throughout this specification. .

In addition, even if it is not explicitly shown or described, a person of ordinary skill in the art to which the present invention pertains can make various modifications including the technical idea according to the present invention from the description of the present invention. Obviously, this still falls within the scope of the present invention.

In addition, the above embodiments described with reference to the accompanying drawings have been described for the purpose of explaining the present invention, and the scope of the present invention is not limited to these embodiments.

100: design data input unit
200: sensor management unit
210: structure health sensor
220: navigation sensor
230: aircraft data sensor
240: storage
300: algorithm modeling unit
400: aircraft
410: body part
420: wing
430: damage detection area
440: impact detection area
450: deformation detection area

Claims (11)

Damage data, impact data, and deformation data required to determine the health of an aircraft structure in the algorithm for determining the integrity of a structure, navigation data including flight posture, position, and speed, and aircraft data including altitude, bearing, engine condition, and temperature a design data input unit 100 configured to set a scenario including data design information for acquiring at least one or more of the data;
A sensor management unit 200 that is installed in the aircraft 400 and acquires flight test data including damage data, impact data, deformation data, navigation data, and aircraft data based on the scenario; and
Storing the acquired flight test data, and classifying the flight test data by preset damage data, impact data, deformation data, navigation data, and aircraft data using an artificial intelligence model,
By synchronizing the classified data according to the flight status of any one of hover flight, stationary flight, ascending flight, descending flight, rotational flight, and level flight, and the flight form of any one of manually controlled flight, autopilot flight, and programming flight, The soundness of the aircraft structure based on damage data, deformation data and impact data detected in the damage detection area 430 , the impact detection area 440 , and the deformation detection area 450 of the body portion 410 and the wing portion 420 . An optimization algorithm design system for determining the soundness of an aircraft structure, including; an algorithm modeling unit 300 for generating an algorithm for determination. delete delete The method of claim 1,
The algorithm converts the classified flight test data into a flight state of any one of spot flight, stationary flight, ascending flight, descending flight, rotational flight, and level flight of the aircraft, and any one of manually controlled flight, autopilot flight, and programming flight. Optimization algorithm design system for judging the soundness of aircraft structures, characterized by judging the soundness of aircraft structures based on wing deformation size, cracks, bolt loosening, impact size, impact location, and impact time data by synchronizing according to flight shape . a) The design data input unit 100 includes damage data, impact data and deformation data required for determining the soundness of the aircraft structure, navigation data including flight attitude, position, and speed, and aircraft including altitude, bearing, engine condition, and temperature designing a scenario including data design information for acquiring at least one or more data among data;
b) acquiring, by the algorithm modeling unit 300, flight test data including damage data, impact data, deformation data, navigation data, and aircraft data based on the designed scenario from the sensor management unit 200 installed in the aircraft;
c) Any of flight in place, flight stop, ascend flight, descend flight, rotation flight, and level flight of the aircraft in order to obtain data necessary for designing the structure soundness algorithm based on the flight test data obtained by the algorithm modeling unit 300 Building and learning a learning model suitable for one flight state and a flight form that is any one of a manually-controlled flight, an automatically-controlled flight, and a programming flight; and
d) the algorithm modeling unit 300 designing an algorithm based on the learning result; including,
The algorithm designed in step d) classifies the flight test data by preset damage data, impact data, deformation data, navigation data, and aircraft data using an artificial intelligence model, and classifies the classified data by flying in place and flying in place. , the body part 410 and the wing part 420 by synchronizing according to the flight state of any one of ascending flight, descending flight, rotational flight, and level flight, and the flight form of any one of manually controlled flight, autopilot flight, and programming flight ) of the aircraft structure, characterized in that the soundness of the aircraft structure is determined based on the damage data, deformation data and impact data detected in the damage detection area 430, the impact detection area 440, and the deformation detection area 450 of Optimization algorithm design method for soundness judgment. 6. The method of claim 5,
The scenario designed in step a) includes a flight state that is any one of hover flight, stationary flight, ascending flight, descending flight, rotational flight, and level flight of the aircraft in order to obtain data necessary for designing the structure health algorithm, and manually controlled flight. , an optimization algorithm design method for determining the soundness of an aircraft structure, characterized in that the data acquisition information is set based on a flight form that is any one of an autopilot flight and a programming flight. 6. The method of claim 5,
The flight test data of step b) includes the flight status of any one of spot flight, stationary flight, ascending flight, descending flight, rotation flight, and level flight of the aircraft set in the scenario to obtain the data necessary for designing the structure health algorithm; , an optimization algorithm design method for judging the soundness of an aircraft structure, characterized in that it is data acquired through a flight performed according to a flight form that is any one of a manually-controlled flight, an automatically-controlled flight, and a programming flight. delete delete 6. The method of claim 5,
e) the algorithm modeling unit 300 additionally acquires flight test data including damage data, impact data, deformation data, navigation data, and aircraft data from the aircraft in which the algorithm generated in step d) is installed, and additionally acquired flight Complementing the algorithm through analysis and learning based on the test data; Optimization algorithm design method for determining the soundness of an aircraft structure, characterized in that it further comprises a. 11. The method of claim 10,
The optimization algorithm design method for determining the soundness of an aircraft structure, characterized in that it further comprises; the algorithm modeling unit 300 changing the scenario based on the supplemented algorithm.

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