KR102056812B1 - Test bench system for electronic engine control unit of airplane gas turbin engine and test method using the same - Google Patents

Abstract

The present invention relates to a test bench system of an electronic engine control unit of an aircraft gas turbine engine and a test method using the same, by simulating a physical signal related to the engine of the gas turbine by an engine simulator connected to the test bench console unit, and cockpit simulator Generate a physical signal for operating the engine simulator, generate an engine model to be embedded in the engine simulator by the software simulator, and verify the operation of the software or control the components by the host unit and the control unit. .

Description

TEST BENCH SYSTEM FOR ELECTRONIC ENGINE CONTROL UNIT OF AIRPLANE GAS TURBIN ENGINE AND TEST METHOD USING THE SAME}

The present invention relates to a test bench system of an electronic engine control unit of an aircraft gas turbine engine and a test method using the same, and more particularly, to simulate a control operation state of an electronic engine control unit for electronically controlling an aircraft gas turbine engine. The present invention relates to a test bench system of an electronic engine control unit of an aircraft gas turbine engine and a test method using the same.

The present invention is derived as a result of the EECU platform development project of the aircraft gas turbine engine FADEC among the aerospace parts technology development project hosted by the Korea Institute of Industrial Technology Evaluation and Management from October 1, 2012 to September 30, 2017.

The electronic control unit (hereinafter referred to as 'EECU'), which is a controller of a gas turbine engine of an aircraft, is an electronic control engine of an aircraft gas turbine engine. It is the heart of the full authority Digital Engine Controller (FADEC).

The EECU for the aircraft undergoes a full verification process for control algorithms, hardware interfaces, and performance through a test bench before being applied to an actual engine during development.

In order to go through this verification process, it is necessary to use a simulator that generates the same virtual signal as the actual engine because it can be expensive and time-consuming to test with a real engine and can damage expensive engines or cause safety risks. Can be.

Virtual engine simulators, which replace real engines, should be able to simulate engine behavior in real time, almost identical to real life. Therefore, the simulation speed must be as fast as the actual system speed so that input, operation, and output can be performed within the time range set by the user.

Therefore, in order to perform such a real-time simulation, it can be said that a real-time engine model capable of performing a calculation close to real-time and hardware suitable for it are required.

However, these simulation devices and EECU devices are the core technologies of aircraft engines, so they are difficult to receive technology transfer in developed countries because they are classified as developer and national protection items.

Therefore, it is urgent to develop and disseminate the simulation apparatus that is required to develop the related equipment as described above.

Korean Laid-Open Patent No. 2016-7017263 Korean Patent Publication No. 2014-0180545

The present invention is to solve such a conventional problem, an object of the present invention to provide a system for simulating a signal to simulate the virtual situation in the EECU of the aircraft gas turbine engine and to test whether the engine is operating steady state. It is to.

According to a feature of the present invention for achieving the above object, the present invention is a system for testing an electronic engine control unit (EECU) of an aircraft gas turbine engine, the test bench console unit; An engine simulator for simulating a physical signal associated with the aircraft gas turbine engine and measuring a state value of the engine by the physical signal; A cockpit simulator interworking with the test bench console unit and generating and transmitting a physical signal for operating the engine simulator to the EECU; A software simulator for generating an engine model to be embedded in the engine simulator; And a host unit for verifying the operation of the software embedded by the software simulator; and a control unit for monitoring the test results and controlling the components.

The engine simulator of the present invention includes an engine signal central processing unit; A rotational speed value output unit for outputting a rotational speed of the physical signal as an analog signal and outputting a state value inside the engine as a digital signal; A temperature value output unit configured to output a temperature value inside the engine as an analog signal; A pressure value output unit which outputs the pressure value inside the engine as an analog signal; It is preferable to include a rotation speed output unit for outputting the rotation speed of the pump motor, the starter, and the generator in PWM.

Cockpit simulator of the present invention comprises a cockpit central processing unit; An interface unit; An input-output controller for transmitting and receiving analog and digital signals; Digital signal transceiver; Cockpit communication unit equipped with a communication module for aviation; and a relay unit for transmitting and receiving a related signal to control the relay preferably.

A test method using a system for testing an electronic engine control unit (EECU) of an aircraft gas turbine engine of the present invention, the method comprising: embedding an engine model in an engine simulator by uploading software to the EECU; A signal generation step of generating an engine signal by the engine simulator in which the engine model is embedded; A control command output step of generating a cockpit command in the cockpit simulator and outputting an engine control command in the EECU; An expected value determining step of determining whether the test result according to the engine control command is consistent with the expected result; and preferably, a result derivation step of deriving the final result by the determination step.

In the control command output step of the present invention, it is preferable to generate a cockpit signal by pre-stored simulation to output an engine control command, or to generate a cockpit signal by a user's arbitrary adjustment to output an engine control command.

The predictive value determining step of the present invention outputs a test result if the output data matches the expected result, and if the output data does not match the expected result, corrects the software or tests lower requirements depending on whether there is a difference in the requirements from the software. It is desirable to carry out.

In the predicted value determining step of the present invention, if the output data does not match the expected result and there is a difference in the demand from the software, the software is repeated by outputting the engine control command again by modifying and uploading the software, and repeating the test. If it is not consistent with the expected result and there is no difference between the software and the requirement, it is desirable to perform a test on the lower demand to derive the result.

According to the test bench system of the electronic engine control unit of the aircraft gas turbine engine and the test method using the same according to the present invention, the EECU is tested by testing the extreme flight situation without installing and testing the EECU directly in the aircraft gas turbine engine. There is an advantage in that it can be tested for operation and the cost can be reduced by reducing the number of tests.

1 is a perspective view showing the appearance of a test bench system of an electronic engine control unit of an aircraft gas turbine engine according to the present invention;
Figure 2 is a block diagram showing the configuration of a test bench system of the electronic engine control unit of the aircraft gas turbine engine according to the present invention.
Figure 3 is a block diagram showing the engine simulator of the test bench system of the electronic engine control unit of the aircraft gas turbine engine according to the present invention.
Figure 4 is a block diagram showing a cockpit simulator of the test bench system of the electronic engine control unit of the aircraft gas turbine engine according to the present invention.
5 is a configuration diagram sequentially showing the operating state of the test bench system of the electronic engine control unit of the aircraft gas turbine engine according to the present invention.
Figure 6 is a flow chart sequentially showing a test method using a test bench system of the electronic engine control unit of the aircraft gas turbine engine according to the present invention.

Description of the present invention is only an embodiment for structural or functional description, the scope of the present invention should not be construed as limited by the embodiments described in the text. That is, since the embodiments may be variously modified and may have various forms, the scope of the present invention should be understood to include equivalents for realizing the technical idea. In addition, the objects or effects presented in the present invention does not mean that a specific embodiment should include all or only such effects, the scope of the present invention should not be understood as being limited thereby.

On the other hand, the meaning of the terms described in the present application should be understood as follows.

Terms such as "first" and "second" are intended to distinguish one component from another component, and the scope of rights should not be limited by these terms. For example, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component.

When a component is referred to as being "connected" to another component, it should be understood that there may be other components in between, although it may be directly connected to the other component. On the other hand, when a component is referred to as being "directly connected" to another component, it should be understood that there is no other component in between. On the other hand, other expressions describing the relationship between the components, such as "between" and "immediately between" or "neighboring to" and "directly neighboring", should be interpreted as well.

Singular expressions should be understood to include plural expressions unless the context clearly indicates otherwise, and terms such as "comprise" or "have" refer to a feature, number, step, operation, component, part, or portion thereof that is implemented. It is to be understood that the combination is intended to be present and does not exclude in advance the possibility of the presence or addition of one or more other features or numbers, steps, actions, components, parts or combinations thereof.

In each step, an identification code (e.g., a, b, c, etc.) is used for convenience of description, and the identification code does not describe the order of the steps, and each step is clearly contextual. Unless stated otherwise, they may occur out of the order noted. That is, each step may occur in the same order as specified, may be performed substantially simultaneously, or may be performed in the reverse order.

The present invention can be embodied as computer readable code on a computer readable recording medium, and the computer readable recording medium includes all kinds of recording devices in which data can be read by a computer system. . Examples of computer-readable recording media include ROM, RAM, CD-ROM, magnetic tape, floppy disk, optical data storage device, and the like, and are also implemented in the form of a carrier wave (for example, transmission over the Internet). It also includes. The computer readable recording medium can also be distributed over network coupled computer systems so that the computer readable code is stored and executed in a distributed fashion.

All terms used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. The terms defined in the commonly used dictionary should be interpreted to coincide with the meanings in the context of the related art, and should not be interpreted as having ideal or excessively formal meanings unless clearly defined in the present application.

The test bench system of the electronic engine control unit of an aircraft gas turbine engine according to the present invention is a device for verifying an electronic engine control unit (EECU) that is a controller of an aircraft gas turbine engine. The EECU is a device that controls aircraft gas turbine engines with digital electronic signals to ensure optimal engine efficiency under given flight conditions.

Therefore, the testbench system of the present invention is to perform the safety and performance verification required for the EECU to be applied to the actual engine in the development stage, and not only the safety and performance verification of the EECU but also virtually similar tests can be performed. By reducing the number of test cycles applied to the actual engine and simulating extreme situations that are difficult to implement with a real engine, it is possible to replace the engine damage and dangerous tests that may occur during the actual engine test.

More specifically, the EECU, which is verified by the present invention, was developed for the avionics field certification of DO-178C, which is issued by the American Aeronautical and Communications Technical Committee (RCTA) and issued by the Federal Aviation Administration (FAA). Means the adopted software airworthiness certification document.

The overall appearance of a test bench system for an electronic engine control unit of an aircraft gas turbine engine according to the present invention is shown in FIG. 1.

As shown in FIG. 1, the testbench system according to the present invention provides an interface for mounting and operating an EECU, and is equipped with a control panel for inputting command values to the EECU.

In addition, the test bench system of the present invention is equipped with a real-time engine simulator capable of simulating the same physical signal as an actual engine, and using the real-time engine simulator for normal operation of the engine, fault input, and operation under extreme conditions. Can be tested. All input and output signals generated in this verification test are monitored and recorded in the test bench system of the present invention.

2 to 5 show the configuration of the test bench system of the electronic engine control unit of the aircraft gas turbine engine according to the present invention, respectively.

As shown in FIG. 1, a test bench system of an electronic engine control unit of an aircraft gas turbine engine according to the present invention includes a test bench console unit 100; An engine simulator 200 for generating a physical signal related to the target engine to be tested; A cockpit simulator 300 interlocked with the test bench console unit 100 to generate a physical signal for operating the engine simulator 200 by software and to transmit the physical signal to the EECU; A software simulator 400 for generating an engine model to be embedded in the engine simulator 200; A host unit 500 for verifying the operation of the software embedded by the software simulator 400; A control unit 600 for controlling each component of the test bench system and monitoring the test results; It includes a power supply unit 700.

As shown in FIG. 1, the test bench console unit 100 includes a desk unit 110, a monitor unit 120, and a steering unit 130. And, as shown in Figure 2, the test bench console unit 100 has a terminal structure for connecting each component unit included in the test bench system, in particular so that the EECU 10 to be tested can be connected It may be composed of a mapping box in which wiring and terminals are arranged.

The engine simulator 200 is a device capable of generating the same physical signal as the engine under test and measuring an engine state value by the corresponding physical signal. The engine simulator 200 is embedded and operated independently. In addition, the engine simulator 200 may input and output analog and digital signals and may use a module capable of generating pulse width modulation (PWM).

The engine simulator 200 includes an engine signal central processing unit 210; A rotation speed value output unit 220 for outputting a rotation speed as an analog signal and outputting a state value of a sensor inside the engine as a digital signal; A temperature value output unit 230 for outputting a temperature value (fuel, oil, atmospheric temperature, etc.) inside the engine as an analog signal; A pressure value output unit 240 for outputting a pressure value (fuel, oil, atmospheric pressure, compressor, etc.) inside the engine as an analog signal, and outputting the temperature of the exhaust gas as an analog signal; It includes a rotation speed output unit 250 for outputting the rotational speed of the pump motor to the starter and the generator in PWM.

The cockpit simulator 300 is to generate and transmit a physical signal for operating the engine simulator 200 to the EECU 10 and is operated in conjunction with the test bench console unit 100. The cockpit simulator 300 may exchange engine related information, flight data, and HUMS data from the EECU 10 through communication.

Cockpit simulator 300 and the cockpit central processing unit 310; An interface unit 320; An input-output controller 330 for transmitting and receiving analog and digital signals; A digital signal transceiver 340; A cockpit communication unit 350 equipped with an aviation communication module; It includes a relay unit 360 for transmitting and receiving a related signal to control the relay.

The software simulator 400 is for generating an engine model to be embedded in the engine simulator 200 and may generate a specific signal to the engine simulator 200 by generating a specific signal from the outside.

The software simulator can generate an engine simulator model by Matlab / Simulink, which is a model that is loaded into the virtual engine by adding fuel quantity calculation model to the thermodynamic engine performance model.

The host unit 500 is for verifying whether the software embedded by the software simulator 400 is normally operated. The host unit 500 may be configured as a general PC.

Verification of normal operation of the host unit 500 may be performed by requirement-based verification and structural coverage analysis.

Requirement-based verification can be based on two requirements documents, Software Requirement Data (SRD) and Software Design Data (SDD), created at the design stage.

The SRD is a document describing the higher requirements, which are the functions to be implemented in the software, and the SDD solves the requirements of how to develop the SW source code in order for the higher requirements to be implemented.

In the test bench of the present invention, verification is performed based on upper and lower demands, and the determination of whether the software satisfies all the requirements may be made as a result of the structural coverage analysis.

Structural coverage analysis is the analysis of whether all source code of SW has been executed. For example, the coverage analysis items presented in the above-described DO-178C include syntax coverage, branch coverage, and MC / DC coverage.

After testing all the requirements, this structural coverage analysis identifies parts of the source code that have not been executed. The final goal of the DO-178C verification phase is to add additional requirements or test cases for this area to ensure 100% structural coverage.

The host unit 500 performs structure coverage analysis to check the degree of execution of the software. Dedicated tools are needed to analyze the structural coverage, and an environment is needed to put additional probe codes (codes for calculating the structural coverage) in the verification target S / W. For this purpose, the host unit 500 and the debugger are used. Works.

The host unit 500 may be equipped with a user tool (software called “COVER”) for structural coverage analysis, and the debugger may dump data on a probe code added to the software by copying a memory value. To allow for structural coverage analysis.

The data dumped from the debugger is analyzed by the structure coverage analysis dedicated tool (COVER) to display the structure coverage results.

The host unit 500 also performs sub-requirement based testing. Monitoring at the source code level is required to perform sub-request-based testing. The host unit 500 is provided with software for controlling the debugger ("Trace32 PowerView for PowerPC"), and can grasp the source code executed by the program. Identify the function or branch of the source code that has not been executed, and identify the execution condition in the subordinate diagram. Test cases are created with the identified conditions and finally run through the debugger control software.

Hereinafter, a test method using a test bench system of an electronic engine control unit of an aircraft gas turbine engine according to the present invention will be described in detail.

First, when power is supplied to the console unit 100 by the power unit 700, the EECU software generated by the software simulator 400 is uploaded. When the software simulator 400 executes Simulink, the engine model is embedded in the engine simulator 200.

When the engine model is embedded in the engine simulator 200, various types of engine signals are formed in the engine simulator 200. In this case, the cockpit simulator 300 may transmit the cockpit command according to a pre-programmed scenario, or may transmit the cockpit command according to an operation command directly input by a user.

The cockpit command in a typical scenario is for checking test results for normalized engine operation, and the cockpit command for direct input is for checking test results for abnormal engine operation.

When the cockpit command is generated in the cockpit simulator 300 as described above, the software of the EECU is operated and the engine control command is output from the EECU. This output result is visualized through the monitor 120.

If the data according to the monitoring does not match the expected result, it is determined whether there is a difference between the software and the demand. If there is a difference between the software and the requirements, this is because the configuration of the EECU software was incorrectly performed. Then, modify the EECU software again and re-upload it to the EECU software to perform the cockpit command.

However, if there is no difference between the software and the requirements, the host unit 500 and the debugger are used to perform the test on the lower requirements to derive the test result through the structural coverage analysis.

The order of verification for the requirements test is to (1) derive higher requirements, (2) derive lower needs, (3) higher needs based tests, (4) structural coverage analysis (60%), and (5) additional higher needs. Derivation or test addition, (6) Structural Coverage Analysis (80%), (7) High Demand Based Test End and Lower Demand Based Test Start, (8) Structural Coverage Analysis (90%), (9) Additional Lower This can be done in order of derivation or addition of tests, (10) structural coverage analysis (100%), and (11) termination of verification.

First, a requirement-based test is performed on the pre-written high-level requirements document. If it is determined that all the tests for the higher demand level have been completed, the structural coverage analysis result is performed. The structural coverage analysis results are reviewed by the designers and developers to identify the requirements for the unimplemented parts. The verifier uses the debugger to test the identified subrequirements. Finally, the verification ends when the structural coverage reaches 100%.

Although described above with reference to a preferred embodiment of the present application, those skilled in the art various modifications and changes to the present application without departing from the spirit and scope of the invention described in the claims below I can understand that you can.

100: console unit 200: engine simulator
300: Cockpit Simulator 400: Software Simulator
500: host unit 600: control unit
700: power supply unit

Claims (7)

A test bench system for testing an electronic engine control unit (EECU) of an aircraft gas turbine engine,
Test bench console unit;
An engine simulator for simulating a physical signal associated with the aircraft gas turbine engine and measuring a state value of the engine by the physical signal;
A cockpit simulator interworking with the test bench console unit and generating and transmitting a physical signal for operating the engine simulator to the EECU;
A software simulator for generating an engine model to be embedded in the engine simulator;
A host unit for verifying the operation of the software embedded by the software simulator; and
A control unit for controlling the test bench console unit, an engine simulator, a cockpit simulator, a software simulator, and a host unit and monitoring test results;
The engine simulator
An engine signal central processor;
A rotational speed value output unit for outputting a rotational speed of the physical signal as an analog signal and outputting a state value inside the engine as a digital signal;
A temperature value output unit configured to output a temperature value inside the engine as an analog signal;
Pressure value output unit for outputting the pressure value in the engine as an analog signal; And
A pump motor, a starter, and a rotation speed output unit for outputting the rotation speed of the generator in PWM
Test bench system for electronic engine control unit of aircraft gas turbine engine.
delete The method of claim 1,
The cockpit simulator
Cockpit central processing unit;
An interface unit;
An input-output controller for transmitting and receiving analog and digital signals;
Digital signal transceiver;
Cockpit communication unit equipped with a communication module for aviation; And
It includes a relay unit for transmitting and receiving a related signal to control the relay
Test bench system for electronic engine control unit of aircraft gas turbine engine.
In a test method using a test bench system according to any one of claims 1 and 3 for testing an electronic engine control unit (EECU) of an aircraft gas turbine engine,
An embedded step of uploading software to the EECU and embedding an engine model in an engine simulator;
A signal generation step of generating an engine signal by the engine simulator in which the engine model is embedded;
A control command output step of generating a cockpit command in the cockpit simulator and outputting an engine control command in the EECU;
An estimated value determining step of determining whether a test result according to the engine control command is consistent with an expected result; and
A result derivation step of deriving a final result by the determination step;
Test method using test bench system of electronic engine control unit of aircraft gas turbine engine.
The method of claim 4, wherein
The control command output step
Generates cockpit signals based on pre-stored simulations and outputs engine control commands,
It generates the cockpit signal by user's arbitrary adjustment and outputs the engine control command.
Test method using test bench system of electronic engine control unit of aircraft gas turbine engine.
The method of claim 4, wherein
The estimated value determination step
If the output data matches the expected result, the test result is output.
If the output data does not match the expected results, the software may be modified or a lower demand test may be performed depending on whether there is a difference in the requirements from the software.
Test method using test bench system of electronic engine control unit of aircraft gas turbine engine.
The method of claim 6,
The estimated value determination step
If the output data does not match the expected result and there is a difference in the demand from the software, the software is modified and uploaded again, and the engine control command is output again to repeat the test.
If the output data does not match the expected result and there is no difference between the software and the demand, a test is performed on a lower demand to derive a result.
Test method using test bench system of electronic engine control unit of aircraft gas turbine engine.

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