RU2780244C1 - Flight information collection and processing system for aircraft digital twin validation during flight tests - Google Patents

Abstract

FIELD: flight information collection systems.

SUBSTANCE: system for collecting and processing flight information for validating the digital twin of an aircraft during flight tests contains: a system for preparing for a test flight, including a ground-based complex for preparing flight tasks, a removable storage medium; on-board system of an aircraft, including an information modeling unit, a removable storage medium, a sample of the equipment under test, an on-board meter, a storage device, a unit for identifying and primary processing of flight information, an event waiting unit, a mode recognition unit, a mode processing and registration unit, a multifunctional frame formation unit "Test mode" indicator, "Validation" information storage unit, "Tests" information storage unit, "Results" information storage unit; a processing and analysis system, including a ground-based complex for processing flight information, a matching unit, a unit for generating a report on the results of validation, a unit for processing and analyzing the results of validation, a removable storage medium.

EFFECT: expansion of the functionality of systems for collecting and processing flight information during flight tests of aircraft is provided.

1 cl, 1 dwg

Description

The invention relates to the field of aviation technology testing and allows validation of the digital twin of an aircraft during test flights.

Digital twin (DT) - a system consisting of a digital model of a product and two-way information links with the product (if the product is available) and (or) its components. The CD is developed and applied at all stages of the product life cycle.

The purpose of creating a CD is to meet the technical and tactical-technical requirements for the product, reduce the cost and development time of prototypes of the product, increase the manufacturability of the product, as well as increase the reliability and efficiency of the product.

Digital product model - a system of mathematical and computer models, as well as electronic documents of the product, describing the structure, functionality and behavior of a newly developed or operated product at various stages of the life cycle, for which, based on the test results in accordance with GOST 16504, an assessment was made of compliance with the requirements for the product.

Validation of the mathematical model - confirmation of the compliance of the mathematical model with the object being modeled by parametric comparison of the results of mathematical modeling with reliable results of full-scale (ground and flight) tests of the developed sample of aviation equipment and its components.

Validation of the CD is the process of determining the correspondence of the digital model included in the CD to the real world. Validation provides a justification for the fact that the digital data in the declared field of application allows you to correctly and with a certain accuracy simulate real processes.

The closest analogue of the claimed invention is an on-board information recording system (invention patent RU 2285241), which contains an information collection unit, a remote control, a secure drive, an audio unit, a digital converter, an auto-control module included in the console, a secure drive controller containing memory modules, a module comparison and counter of mismatches, an information pickup unit containing memory cards and a mismatch module, an information port, the first and second video blocks, the first and second switches, as well as a status indicator, appropriately connected into a single electronic circuit. The disadvantage of this solution is that the system, due to limited functionality in terms of obtaining flight information in real time, makes it difficult to quickly obtain an assessment of the technical condition of the control object and cannot be used to solve the problem of validating the digital twin of an aircraft.

The technical objective of the claimed invention is to expand the functionality of systems for collecting and processing flight information during flight tests of aircraft.

The solution of the technical problem is achieved by the fact that the system for collecting and processing flight information for validating the digital twin of the aircraft during flight tests includes: which is connected to the on-board meter, and the second output is connected to the ground-based flight information processing complex; the first output of the on-board meter is connected to the input of the drive, the output of which is connected to a matching unit, the output of which is connected to the second input of the ground-based flight information processing complex; the second output of the on-board meter is connected to the input of the block for identification and primary processing of flight information, the information from the output of which is fed to the input of the event waiting block, the output of which is connected to the input of the mode recognition block; the output of the mode recognition unit is connected to the input of the mode processing and registration unit; the first output of the block for processing and registering modes is connected to the block for forming a frame of the multifunctional indicator "Test mode", the second output of the block for processing and registering modes is connected to the input of the information storage block "Results"; the first output of the Validation information storage block is connected to the second input of the event waiting block, the second output of the Validation information storage block is connected to the second input of the mode recognition block; the first output of the "Test" information storage unit is connected to the third input of the event waiting block, the second output of the "Test" information storage unit is connected to the third input of the mode recognition unit; information is written to the information storage block "Validation" from the output of the removable storage medium, the input of which is connected to the output of the information modeling block; the output of the "Results" information storage unit is connected to the input of the removable storage medium, the output of which is connected to the first input of the block for processing and analyzing the validation results of the digital twin, the output of which is connected to the input of the block for generating a report on the results of the validation, and the output of the block for generating the report on the results of the validation is connected with the second input of the block for processing and analyzing the results of validation of the digital twin; the third output of the digital twin validation results processing and analysis unit is connected to the third input of the ground-based flight information processing complex, and the output of the ground-based flight information processing complex is connected to the third input of the digital twin validation results processing and analysis unit.

The technical result achieved by the set of features of the claimed invention is to provide the possibility of automated collection and processing of flight information to validate the digital twin of the aircraft during flight tests.

The operation of the invention is illustrated by the figure, which indicates:

Circuit A - system components used at the stage of preparation for a test flight;

Circuit B - system components involved in a test flight on board an aircraft (LA);

Circuit C - system components involved at the stage of processing and analysis of materials;

Circuit B1 - on-board validation system (blocks 8-15);

1 - ground complex for the preparation of flight tasks;

2 - removable media;

3 - information modeling block;

4 - removable media;

5 - sample of the tested equipment;

6 - onboard meter;

7 - drive;

8 - block of identification and primary processing of flight information;

9 - event waiting block;

10 - mode recognition block;

11 - block processing and registration modes;

12 - frame formation unit of the multifunctional indicator "Test mode";

13 - block of information storage "Validation";

14 - block for storing information "Tests";

15 - block of information storage "Results";

16 - ground complex for processing flight information;

17 - matching block;

18 - block for generating a report on the results of validation;

19 - block for processing and analyzing the results of validation of the CD;

20 - removable storage medium.

Block 1 - ground preparation of flight tasks (1) is a personal computer with a set of special software that generates a flight task and flight data for the on-board radio-electronic equipment of the aircraft in accordance with the tasks of the flight. The flight task prepared by the test team contains all the information necessary for the crew to achieve the goals of the test flight, including the modes and flight parameters that are mandatory for the flight crew.

Block 2 is a removable storage medium (2) with non-volatile memory, made in a metal protected case with a USB 2.0 standard connector. The unit is designed to transfer the generated flight task from (1) to the on-board electronic equipment of the aircraft (5).

Block 3 - information-modeling block (3), is a computer that ensures the operation of the AC LA. In (3), the initial data is prepared for solving the problem of validating the AC of the aircraft and a list of flight modes is formed that is necessary to solve the problem of validation. The flight modes required for validation and the list of parameters are entered into the “Validation” information storage unit (13).

Block 4 is a removable storage medium (4) with non-volatile memory, made in a metal protected case with a USB 2.0 standard connector. The block is designed to transfer information from (3) to the "Validation" information storage block (13).

Block 5 - a sample of the equipment under test (5), is a test object. The state and operation of the aircraft equipment to be assessed is carried out by obtaining measurement information by the onboard meter (6).

Block 6 - on-board meter (6), is an information-measuring system designed to obtain measurement information in flight conditions that characterizes the state and operation of aircraft units and assemblies, the interaction of aircraft components with each other and the environment. The on-board meter includes the following elements:

primary measuring transducers (PMT) that perceive physical influences from (5) and convert them into an electrical signal;

a matching device that converts the PIP signals into the form required for registration;

a recording device that provides the collection and accumulation of information;

means of synchronization, providing binding to a single time of all flows of registered information;

communication lines transmitting measurement information.

Block 7 - drive (7), is a removable storage medium with non-volatile memory, made in a metal protected case. The block is designed to store the test flight parameters received from the block (6) and transfer the information to the ground-based information processing device.

Block 8 - block for identification and primary processing of flight information (8), made in the form of a microprocessor board, with a RAM module and a matching device. The block receives and coordinates parameters from the onboard meter (6) using the 1000Base-TX protocol.

Block 9 - event waiting block (9) is made in the form of a microprocessor board with a RAM module and a matching device. The block provides the operation of the event recognition algorithm proposed in Adgamov R.I., Berkheev M.M., Zalyaev I.A. Automated testing in aircraft construction, M.: Mashinostroenie, 1989. 232 p. The event recognition algorithm is based on the implementation of the operation of waiting and detecting from a certain group of events specified in the “Validation” information storage block (13) and in the “Test” information storage block (14) coming from (8) in real time, after which the information for further processing enters the block (10).

Block 10 - mode recognition block (10) is made in the form of a microprocessor board with a RAM module and a matching device. The block ensures the operation of the mode recognition algorithm proposed in Adgamov R.I., Berkheev M.M., Zalyaev I.A. Automated testing in aircraft construction, M.: Mashinostroenie, 1989. 232 p. The mode recognition algorithm is based on the pattern recognition system. The algorithm provides for preliminary recognition of the subset to which the given test mode belongs, and then the final mode recognition is carried out in order to find the mode identification from the database of validation modes located in the information storage block "Validation" (13), or from the database of test modes, placed in the block of information storage "Tests" (14). The algorithm provides for the control of making false decisions in the event of gross measurement errors or in case of small temporal excess of the parameter fluctuation over its average statistical value.

Block 11 - block for processing and recording modes (11) is made in the form of a microprocessor board with a RAM module and a matching device, based on the information coming from the block (10) about the current flight mode of the aircraft and its corresponding parameters, writes values to the information storage block " Results” (15). To increase the information awareness of the crew about the test modes being performed and create conditions for the integration of test flights, information about the recognized flight mode with the main parameters enters the framing unit of the multifunctional indicator "Test mode" (12).

Block 12 - the block for forming a frame of the multifunctional indicator "Test mode" (12) is a microprocessor board with a RAM module and a matching device, which provides, through the on-board equipment system of the aircraft, the formation of the results obtained in the block (11) in the information field of the crew.

Block 13 - information storage block "Validation" (13) is made in the form of a board with a solid state drive and a controller. The block provides recording, storage and access to the database of validation modes.

Block 14 - information storage unit "Tests" (14) is made in the form of a board with a solid state drive and a controller. The block provides recording, storage and access to the database of test modes.

Block 15 - information storage block "Results" (15) is made in the form of a board with a solid state drive and a controller. The block provides storage and access to the results database.

Block 16 - ground processing unit of flight information (16), is a PC with special software and mathematical software for complex processing of measurement information during flight tests of aviation equipment, which performs automated processing of on-board measurement system materials.

Block 17 - matching block (17) is a device in a metal case, with a controller and various types of connectors. The unit provides connection of the storage device (7) via the 1000 Base - TX, 100Base-T protocol and via the USB bus for transferring flight information to (16).

Block 18 - a block for generating a report on the results of validation, is a computer with a printing device and access to the Internet. The block is designed to generate a report on the results of the CSD validation in electronic and printed form.

Block 19 - a block for processing and analyzing the results of the validation of the CD (19) is a computer. Special computer software provides automated processing and analysis of the flight data obtained from (15) and forms the data necessary for (18) on the results of the validation of the aircraft CL. To ensure comparison of simulation data with the results of a test flight at all stages of the flight, information is exchanged between block (19) and block (16) via the Ethernet protocol.

Block 20 is a removable storage medium (20) with non-volatile memory, made in a metal protected case with a USB 2.0 standard connector built into the case. The block is designed to transfer data from block (15) to block (19).

The operation of the claimed invention is as follows.

In accordance with GOST R 57700.37-2021, the introduction of digital twin technology at the product development stage will improve the quality of product design, ensure that technical and performance requirements are met, reduce the number and increase the effectiveness of prototype testing and the development of product design documentation for manufacturability. At the stage of ground and flight tests, mathematical models are refined, and after passing the validation procedure, i.e. confirmation of the reliability of the results of mathematical modeling by the results of a full-scale experiment, can become the basis for the creation of a digital center for the stage of aircraft operation.

In order to realize the possibility of solving the problem of validating the AC of an aircraft without performing special flights on the test aircraft, but in combination with the implementation of the test program, an on-board validation system (BSV, circuit B1) is installed on board the aircraft

A - the stage of preparation for the test flight The task of assessing the characteristics of the aircraft is carried out in flight tests in accordance with the current regulatory and technical documentation: the test program and methodology. Based on these documents, an aircraft test program is being developed, each item of the program provides for the performance of one or more test flights. In each test flight, the crew must perform strictly defined flight modes. To develop a flight task, a ground-based flight data preparation complex is used (block 1). The flight task prepared by the test team contains all the information necessary for the crew to achieve the goals of the test flight, including the modes and flight parameters that are mandatory for the flight crew. Thus, the aircraft crew performs the flight task prepared in (1), which is loaded through the onboard equipment of the aircraft on a removable storage medium (2) through the onboard equipment of the aircraft, which ensures that the parameters of the equipment under test (5) are obtained during the flight.

Also, at stage A, preparations are made for solving the problem of validating the AC of an aircraft, for which in block 3 a list of flight modes is formed that is necessary to solve the problem of validating the AC of an aircraft.

Taking into account the degree of development of the aircraft CSD and the mathematical models included in its composition, the flight modes necessary for validation are entered into the Validation information storage unit (13) using a removable storage medium (4). In (13), the storage and access to the database of validation modes is organized.

B - test flight stage

Flight tests of aviation complexes (AK) represent the final stage in the complex process of aircraft production. During this stage, multifaceted measurements are carried out on board the aircraft, the results of which assess the state of the aircraft and its systems. The experimental data obtained are also used in drawing up a conclusion on the tactical and technical capabilities of AK, which determines the feasibility of their mass production and the start of mass operation. A special place in the complex of onboard measurements is occupied by the system of onboard measurements (SBI), designed to obtain measurement information under flight conditions that characterizes the state and operation of aircraft units and assemblies, the interaction of the aircraft components with each other and the environment.

When performing a flight under the test program, the aircraft crew performs a flight task for a test flight in order to obtain objective information about the sample of the equipment under test (5).

At the stage of flight tests, the aircraft is equipped with an onboard meter (6), which: provides the necessary reliability and accuracy of measuring parameters; has a fairly wide interval of the frequency of measurement of parameters, and the frequency of measurement can be different even for the same parameter and range from several units to several hundred measurements per second; provides measurement of product parameter values at random times upon the occurrence of some event; provides measurement of various groups of parameters that vary in quantitative composition from several units to several thousand parameters. These possibilities (6) make it possible to use it to solve the problem of validating the AC of an aircraft.

The values of the flight parameters recorded (6) are fed to the input of the flight information storage device (7), where the test flight parameters are recorded.

In parallel, information from (6) is fed to the input of the BSV (B1, blocks 8-15). BSV is an on-board electronic computer in which several blocks and databases are implemented in hardware and software. The BSV receives information from (6) and, in parallel with the performance of the flight task by the crew, processes flight information in real time.

The block of identification and primary processing of flight information (8) provides connection and coordination of the parameters coming from (6).

The operation of the BSV is based on the operation of the event waiting algorithm implemented in the event waiting block (9) and the operation of the mode recognition algorithm implemented in the mode recognition block (10) by real-time processing of information from (6) and its identification based on the data located in storages (13) and (14).

The operation of the event waiting block (9) is based on the implementation of the operation of waiting and detecting a certain group of specified events and timely transmission of the relevant information to the control algorithms in the mode recognition block (10).

The operation of the mode recognition block (10) is based on the pattern recognition system. The information processing algorithm implemented in (10) provides for preliminary recognition of the subset to which this test mode belongs, and then the final mode recognition is carried out in order to find the mode identification from the database of validation modes stored in block (13) or from the database of test modes stored in block (14).

The algorithms implemented in blocks (9, 10) provide for the control of making false decisions in the event of gross measurement errors or in case of small temporal excess of the parameter fluctuation over its average statistical value.

In the block for processing and recording modes (11), according to the information received from (10) about the current flight mode of the aircraft and the corresponding parameters, the values are written to the information storage block “Results” (15), where the database of results is formed.

In order to increase the information awareness of the crew about the test modes being performed and create conditions for the integration of test flights, information about the recognized flight mode with the main parameters comes from block (11) to the framing block of the multifunctional indicator "Test mode" (12). Block (12) forms a frame of a multifunctional indicator, which is displayed in the information field of the aircraft crew.

C - stage of processing and analysis of materials

In accordance with the requirements of regulatory documents for the test work, after the test flight, it is necessary to process the flight information recorded by the onboard meter (6), recorded in the drive (7), which is transferred to the ground-based flight information processing complex with the help of a matching unit (17). (16). In (16), the analysis group summarizes the received information with the data of the crew report on the completion of the flight task (output of block (5)).

The results of the BSW operation, accumulated in the results database of the block (15), are also subject to post-flight processing in the block for processing and analyzing the results of the CL validation (19). The transfer of information from (15) to (19) is carried out through a removable storage medium (20).

After automated processing in (19), information about the validation results is supplemented with data in all flight modes from (16). For the exchange of information between specialists of the test results analysis group processing data in (16) and specialists of the validation results analysis group processing data in (19), information exchange via the Ethernet protocol is provided.

The result of the work of the BSV and ground processing is a report on the results of the validation. The report is generated in the block for generating a report on the results of validation (18), which receives information from (19). Based on the results of the validation, if necessary, changes are made to the AC CL.

Claims (11)

A system for collecting and processing flight information for validating the digital twin of an aircraft during flight tests, which includes: a ground-based complex for preparing flight tasks, the output of which is connected to the input of a removable information carrier, the output of which is connected to a sample of the equipment under test, the first output of which is connected to the on-board meter, and the second output is connected to the ground-based flight information processing complex; the first output of the on-board meter is connected to the input of the drive, the output of which is connected to a matching unit, the output of which is connected to the second input of the ground-based flight information processing complex; the second output of the on-board meter is connected to the input of the block for identification and primary processing of flight information, the information from the output of which is fed to the input of the event waiting block, the output of which is connected to the input of the mode recognition block; the output of the mode recognition unit is connected to the input of the mode processing and registration unit; the first output of the block for processing and registering modes is connected to the block for forming a frame of the multifunctional indicator "Test mode", the second output of the block for processing and registering modes is connected to the input of the information storage block "Results"; the first output of the Validation information storage block is connected to the second input of the event waiting block, the second output of the Validation information storage block is connected to the second input of the mode recognition block; the first output of the "Test" information storage unit is connected to the third input of the event waiting block, the second output of the "Test" information storage unit is connected to the third input of the mode recognition unit; information is written to the information storage block "Validation" from the output of the removable storage medium, the input of which is connected to the output of the information modeling block; the output of the "Results" information storage unit is connected to the input of the removable storage medium, the output of which is connected to the first input of the block for processing and analyzing the validation results of the digital twin, the output of which is connected to the input of the block for generating a report on the results of the validation, and the output of the block for generating the report on the results of the validation is connected with the second input of the block for processing and analyzing the results of validation of the digital twin; the third output of the digital twin validation results processing and analysis unit is connected to the third input of the ground-based flight information processing complex, and the output of the ground-based flight information processing complex is connected to the third input of the digital twin validation results processing and analysis unit.

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