KR101145577B1 - Method for Character and Function for Store Management System Simulation Model of Avionics Integration Laboratory System, and Media that can Record Program for Method the same - Google Patents

Abstract

The present invention records the characteristics and function of the fire control radar simulation model of the integrated avionic test system capable of simulating the function of the actual fire control radar (FCR) mounted on the aircraft, and the program stored therein. The medium relates to (a) a mission computer (IMDC), a satellite inertial navigation system (EGI), a flight control computer (FCS), a radio altimeter (RALT) in a fire control radar (FCR) simulation model of an integrated avionics test system. An unpacking step of receiving and processing data generated from a target model and a command related thereto; (b) Cursor control by receiving the data processed in the unpacking step and operating in an operation mode (standby mode, air-to-air mode, air to ground mode) according to the values of a radar mode request and a radar submode request. A processing step of implementing target acquisition, coordinate system transformation, antenna control, target detection, and the like; And (c) after performing the processing step, update the list data, initialize the setting value of the corresponding mode, write the result data as a message, store it in the DB, and send the message to the mission computer. (Packing) step; provides a characteristic and function implementation method for the thermal control radar simulation model of the integrated avionic test system.

Thermal Control Radar (FCR), Simulation, Model, System Integration Lab (SIL), Mission Computer (IMDC), Satellite Inertial Navigation System (EGI), Flight Control Computer (FCS), Radio Altimeter (RALT)

Description

Method for character and function for store management system simulation model of avionics integration laboratory system, and media that can Record Program for Method the same}

The present invention relates to a method for implementing the characteristics and functions of a fire control radar simulation model of an integrated avionics test system, and a recording medium storing a program according to the method. Development of Armed Management Computer (SMS) simulation model with no technology transfer and implementation of characteristics and functions for the fire control ladder simulation model of the avionic integrated test system with more accurate implementation of operation logic that the existing model did not accurately implement. And a recording medium storing a program according to the method.

In general, avionics are simulated on the ground before being mounted on a real aircraft and are installed after conducting an avionics integrated test. In order to perform this test, all avionics equipment should be able to be integrated, and a model that simulates the avionics equipment to cope with the absence of any avionics or to simulate the flight situation is required. It should be possible to monitor and analyze the entire signal. The present invention is software in integrated test equipment that performs this function.

System Integration Lab (SIL) is a system that configures each individual device according to the purpose and method of using the system, and processes and analyzes data between each individual device to analyze and verify the result. The individual equipment used here can be very expensive and difficult to equip, depending on the purpose of use. If a particular piece of equipment is missing or malfunctions during the operation of the SIL and cannot be operated (difficulty in maintenance), the system will not function.

Therefore, when individual equipment is written in software and modeled in real time, it has many advantages in terms of configuration, installation, and operation of equipment. In particular, the thermal control radar mounted on the aircraft is expensive equipment among aviation equipment and is very difficult to diagnose the failure. Modeling this fire control radar with software allows you to exchange data with other equipment without the actual fire control radar equipment. And it is easy to diagnose the problem more easily than the actual equipment and implement the function to add in software.

However, in the past, foreign equipment called RTB (Radar Test Bench) was used to perform OFP (Operation Flight Program) test and system integration test. As a result, simulation models of actual fire control radar equipment were developed with foreign technology. Therefore, there was no way to modify the software when OFP changes, internal logic changes, or signals were added or changed.

In addition, since the execution environment is a Unix environment, it is difficult to set the environment that needs to be modeled, and the interface configuration is difficult to configure, which makes it difficult to maintain the software.

Therefore, the necessity of developing a new model has appeared because there is no information or source code of the simulation model.

The technical problem to be solved by the present invention to solve the above problems, the characteristics and function of the fire control radar simulation model of the integrated avionic test system capable of simulating the function of the actual fire control radar mounted on the aircraft And a recording medium storing a program according to the method.

In addition, another technical problem to be achieved by the present invention is to provide a primary mode (primary mode), air-to-air (air-to-air) and air-to-ground mode (mode) of the actual power control radar The present invention provides a recording medium storing characteristics and functions of a fire control radar simulation model of an avionic integrated test system and a program according to the method.

In addition, another technical problem to be achieved by the present invention is to simulate the thermal control radar simulation model of the avionics integrated test system that can be applied to the maintenance of the model and the addition of new functions, changes to other aircraft and other thermal control radar device The present invention provides a recording medium storing a feature and a function thereof, and a program stored therein.

In addition, another technical problem to be achieved by the present invention is to facilitate data input (Input) / output (Interfacing) by interfacing with the DB built for the data (Interworking) between the System Integration Lab environment and equipment. The present invention provides a recording medium storing the characteristics and functions of the thermal control ladder simulation model of the integrated avionic test system and a program stored therein.

In addition, another technical problem to be achieved by the present invention is to implement the software so that the execution environment of the software (Software) can be executed in the window (Window), the input (Input) / Output (Output) data to the GUI window ( The present invention provides a recording medium storing characteristics and functions of a fire control radar simulation model of an integrated avionic test system that can be monitored through a window, and a program according to the method.

In addition, another technical problem to be achieved by the present invention is to develop a thermal control radar simulation model that has been developed in a foreign country, but the technology has not been transferred at all, and more accurately implement the operation logic that the existing model did not accurately implement. The present invention provides a recording medium storing the characteristics and functions of the thermal control radar simulation model of the integrated avionic test system.

In addition, another technical problem to be achieved by the present invention is to control the firepower of the integrated avionic test system that can freely add signals and add functions by newly developing all the codes so as to completely escape the existing equipment and software technology introduced by foreign companies The present invention provides a recording medium storing a characteristic and a function of a radar simulation model and a program by the method.

In addition, another technical problem to be achieved of the present invention is to provide a signal monitoring and analysis function and a hardware interface function, and for the thermal control radar simulation model of the integrated avionic test system capable of implementing all the functions of each anti-electric model The present invention provides a recording medium storing a feature and a function and a program according to the method.

In addition, another technical problem to be achieved of the present invention is to simulate the function and operation of the thermal control radar simulation model operating in actual T-50 of the integrated avionic test system that can cope with the situation occurring in the actual flight situation as it is The present invention provides a recording medium storing characteristics and functions of a thermal control radar simulation model and a program by the method.

As a means for solving the above-described technical problem, the invention described in claim 1, "(a) a mission computer (IMDC), satellite inertial navigation system (EGI) in the fire control radar (FCR) simulation model of the integrated aircraft test system; An unpacking step of receiving and processing data generated from a flight control computer (FCS), a radio altimeter (RALT), and a target model; (b) receives the data processed in the unpacking step and operates in one of an operation mode consisting of a standby mode, an air-to-air mode, and an air-to-air mode according to a value of a radar mode request and a radar submode request. (Cursor) processing to implement control, target acquisition, coordinate system transformation, antenna control or target detection; And (c) a packing step of writing the result data performed after the processing step into a message, storing the result data in a DB, and transmitting the message to the mission computer; To provide the characteristics and functions for the thermal control radar simulation model of the integrated avionics test system, including.

The invention as set forth in claim 2, wherein, in the unpacking step of step (a): navigation data is input from the satellite inertial navigation system (EGI) and the flight control computer (FCS) is input. Calculate the velocity data by receiving the air data at, and receive the symbol data from the mission computer (IMDC) and process it according to the fire control radar (FCR), and receive the target data from the target model. And a method for implementing the characteristics and functions of the thermal control radar simulation model of the integrated avionics test system characterized by calculating the position.

According to the invention of claim 3, "The input of the data in the step (a) is: the integrated avionics test system, characterized in that the communication by the protocol of MIL-STD-1553 receives data; And how to implement the characteristics and functions of the thermal control radar simulation model.

The invention as set forth in claim 4, wherein, in the step (b), the operation mode comprises: a primary mode of a standby function; Air to air (Range While Search, RWS (Velocity Search), TWS (Track While Scan), ASM (Adaptive Search Mode), ACM (Air Combat Maneuver), Sit (Awareness Mode), STT (Single Target Track) Air-to-Air mode; And air to ground ranging (AGR), ground map (GM), ground moving target indication (GMTI), surface moving target track (SMTT), sea search, and air-to-ground mode of BEACON. Features and Functions of Fire Control Radar Simulation Model for Integrated Avionics Testing System.

The invention according to claim 5 is characterized in that the input / output data of the thermal power control radar FCR can be monitored through a GUI window. To implement the characteristics and functions of the thermal control radar simulation model of the integrated avionic test system.

In addition, as another means for solving the above-described technical problem, the invention described in claim 6 is a recording medium characterized in that "a computer program produced by the method according to any one of claims 1 to 5 is stored. .

According to the present invention, modeling all functions such as AA (Air-to-Air), AG (Air-to-Ground), Primary (primary), which is an internal mode of the currently limited SMS It was.

In addition, a DB is established for interoperation with OFP (Operational Flight Program) and SIL (System Integration Lab), and the input / output data of the thermal control radar is real-time in the DB through the built DB. Read / Write is available by Time, and monitoring is possible in real time.

In addition, the configuration of input / output data of the thermal control radar can be confirmed and monitored by a GUI window.

In addition, it is possible to develop a fire control radar simulation model that has been developed in a foreign country but has not been transferred to the technology at all, and more accurately implements an operation logic that the existing model does not accurately implement.

In addition, by simulating the function and operation of the fire control radar simulation model operating in the actual T-50, it is possible to cope with the situation occurring in the actual flight situation.

In addition, it is possible to analyze each signal by integrating all avionics systems. In the absence of live combat equipment, integrated tests can be performed by applying simulation models.

In addition, the entire code is newly developed to completely escape the existing equipment and software technology of foreign companies, thereby freeing the addition of signals and additional functions.

In addition, it is convenient to use by writing as a Windows-based program and developing an operating program based on a graphic.

In addition, it is possible to generate a monitoring signal for all communication signals applied in the avionics field, there is an effect that can be monitored, stored and analyzed.

It can also be applied to maintenance of models, addition of new features, and changes to other aircraft and other fire control radar devices.

DETAILED DESCRIPTION Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings so that those skilled in the art may easily implement the present invention. As those skilled in the art would realize, the described embodiments may be modified in various different ways, all without departing from the spirit or scope of the present invention. In order to clearly explain the present invention in the drawings, parts not related to the description are omitted, and similar parts are denoted by similar reference numerals throughout the specification.

First, the present invention is a simulation model that simulates a fire control radar mounted on an aircraft as part of the avionics model constituting the equipment for performing the avionics system integration test (SIL: System Integration Lab). The avionics system integrated test equipment, which is the equipment to which this model is applied, is required to test the function of mission computer and other avionics equipment by providing the environment similar to the actual flight environment on the ground and includes various avionics equipment and equipment simulation models. Doing.

The present invention is to develop a thermal control radar simulation model which is an important factor in developing the avionics system integrated test equipment consisting of only foreign technology as described above. By developing this, it is possible to develop a model that can be applied to future maintenance and addition of new functions, changes to other aircraft and other weapons management computers.

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

Avionics integrated test system of the present invention is based on the hardware and interworking, the software configuration of the entire system jurisdiction of the various systems are shown in FIG.

The software of the avionics integrated test system is divided into two parts. One is the real-time operating system (RTOS) based environmental segment (10) that will run the simulation signal and monitoring database and the avionics simulation model, and one is to run the current system and simulate the cockit cockpit environment. Operation A graphical user interface (GUI) program portion 30.

The RTOS environment portion 10 is interworked with a mission computer and Avionics system 20 (real equipment) through a communication protocol, and directly in conjunction with the operation GUI program portion 30. (Discrete) Models I / O signals, analog I / O signals, differential I / O signals, and serial port signals. The operation GUI program portion 30 may include simulation control, data analysis, cockpit simulation, model control and patch in a window environment. Run a GUI program. Here, the simulation control (Simulation Control) functions to load, unload, run, stop, etc. the signal, the data analysis (Data Analysis) is a monitor (monitor), The recording function, the cockpit simulation (Cockit Simulation) functions such as the display (Display), the display signal control, etc., the model control and patch (Medel Control & Patch) is the model ON / Performs functions such as OFF, Patch & Release.

2 is a block diagram of a signal and a database to be applied to signal input and output in the software of the integrated avionic test system of the present invention.

Signals and databases to be applied to signal input and output are configured based on the ICD (Interface Control Document). This signal is operated as a database (CVT signal database) in the RTOS environment, and is converted into a real hardware output value into a physical signal. The simulated signal, which is not a monitoring signal, is determined by the logic of the avionics simulation model (eg, aircraft model, flight and environment model, satellite inertial navigation system, etc.), and the simulation model is also operated in the RTOS environment. Each model and signal operates on the RTOS scheduler that makes up the system. Signal Database Build Tool, Data Analysis / Error Injection (Cockpit Panel, Error Injection, Data Analysis, etc.) and Operation GUI Environment (Simulation Control, System Operating Panel, System Status, etc.) It simulates data analysis and cockpit environments.

Here, the present invention relates to the implementation of the characteristics and functions for the thermal control radar simulation model 100 as part of the avionics model constituting the equipment (SIL) for performing the avionics system integration test.

3 is a conceptual diagram of an IOMAP connection according to the present invention, which includes a fire control radar (FCR) simulation model, a mission computer (IMDC), a satellite inertial navigation system (EGI), a flight control computer (FCS), a radio wave altimeter (RALT), and a target. (Target) It is configured to generate IOMAP for monitoring communication data between models and input and output to I / O Real Hardware Device (MIL-STD-1553).

The mission computer (IMDC), the satellite inertial navigation system (EGI), the flight control computer (FCS), and the radio altimeter (RALT) communicate with the integrated test equipment under the protocol of MIL-STD-1553 to exchange data. In the middle, IOMAP and signal DB are the parts performed by the integrated test equipment and convert the electrical signals into logical signals and convert them into variables that can be used in the actual model. After receiving the input data, the model logic shown in FIG. 4 is performed.

4 is a functional block diagram of a thermal control radar (FCR) simulation model of the present invention.

The fire control radar (FCR) simulation model inputs commands and related data from a mission computer (IMDC), a satellite inertial navigation system (EGI), a flight control computer (FCS), a radio altimeter (RALT), and a target model. Receiving unpacking step 110, an internal processing step 120 for processing data received in the unpacking step 110, and the internal processing step 120 Is configured as a packing step (130) for transferring the data processed in the mission computer (IMDC).

1. Unpacking stage (Input Processing stage)

The unpacking step 110 receives and processes input data of a mission computer (IMDC), a satellite inertial navigation system (EGI), a flight control computer (FCS), a radio altimeter (RALT), and a target model. Each input data is unpacked in an appropriate form and used for operating. The unpacked data is analyzed to determine the initial value of the thermal control radar (FCR).

① Speed Data Input Processing

② Symbol Data Input Processing

③ Target Data Pressure Processing

④ Determination of each mode parameter

First, navigation data is inputted from the satellite inertial navigation system (EGI), and flight data is calculated from the flight control computer (FCS). The controller receives a mission computer (IMDC) symbol input and processes it according to a flight control radar (FCR) model, and receives target data to calculate a target position. After that, basic parameter values are set for each mode.

2. Internal Processing Steps

Depending on the values of the Radar Mode Request and Radar Submode Request, the Operation Mode, that is, Standby Mode, Air to Air Mode, Air to Air Mode (Air) to Ground Mode).

① Standby mode

The RF signal is not emitted and is set as a default value of the antenna and the standby mode.

② Air to Air Mode

a. Velocity Search Mode

i) Check STT (Single Target Tracking) mode

Ii) Basic parameter setting and target tracking calculation when entering STT mode

Ⅲ) Tracked target reset and target reset when releasing after entering STT mode

Target) Target cursor setting, parameter setting and target detection calculation in VS mode

b. ACM (Air Combat Maneuvering) Mode

i) Target cursor setting

Ii) STT mode check

Parameter) Basic parameter setting and target tracking calculation when entering STT mode

Ⅳ) Tracked target reset and target reset when releasing after entering STT mode

Parameter) Parameter setting for each submode

Target) Target cursor setting, parameter setting and target detection calculation in ACM mode

c. TWS (Track While Scan) Mode

i) Target cursor setting

Ii) TWS parameter setting and STT mode entry

Tracking) Target tracking calculation

Detection) Target detection calculation when STT mode is released

Multi) Multi target track calculation

d. Range While Scan (RWS) Mode

i) Target cursor setting

Ii) Parameter setting and target tracking calculation when entering STT mode

SAM) Enter SAM mode

Ⅳ) Parameter setting and target tracking calculation in RWS mode

e. Adaptive Search Mode (ASM) Mode

i) Parameter setting by Cursor range

Ii) Target cursor setting

SAM) Enter SAM mode

Parameter) Parameter setting and target tracking calculation in ASM mode

③ Air to Ground Mode

a. Air to Ground Ranging Mode

i) Ground antenna parameter setting

Ii) AGR parameter setting

b. GM (Ground Map) Mode

i) Freeze mode setting

Ii) Enter FTT Mode

Parameter) Parameter setting and ground map cursor setting

Tracking) Target tracking calculation

해제) Tracked target reset when FTT mode is released

DB) DBS mode setting

c. SEA Mode

i) SEA mode state setting

Ii) Freeze mode setting

Ⅲ) Enter FTT mode

Parameter) Parameter setting and ground map cursor setting

Tracking) Target tracking calculation

해제) Tracked target reset when FTT mode is released

Parameter) Parameter setting and ground map cursor setting

Iii) Target detection

d. GMTI (Ground Moving Target Indication) Mode

i) Freeze mode setting

Ii) Enter FTT mode

Parameter) Parameter setting and ground map cursor setting

Tracking) Target tracking calculation

해제) Tracked target reset when FTT mode is released

Parameter) Parameter setting and ground map cursor setting

Iii) Target detection

e. BEACON Mode

i) BEACON Parameter Setting

Ii) Enter FTT mode

Parameter) Parameter setting and ground map cursor setting

Tracking) Target tracking calculation

해제) Tracked target reset when FTT mode is released

Parameter) Parameter setting and ground map cursor setting

Iii) Target detection

[Packing stage]

The packing step sends various results from the internal processing step of the thermal control radar (FCR) to the mission computer (IMDC). As with unpacking, the model of the thermal control radar (FCR) writes the result to the DB, and the packing routine sends the data to the mission computer (IMDC).

The present invention is a model that simulates a fire control radar required for operating the avionics system integrated test equipment (SIL). The model receives inputs from the mission computer (IMDC), satellite inertial navigation system (EGI), flight control computer (FCS), radio altimeter (RALT) and target models to operate the fire control radar. The model is largely divided into BIT, Standby, Air-to-Air, and Air-to-Ground modes, and starts processing by receiving a ready signal from the mission computer. Obtain speed data from satellite inertial navigation system (EGI) / flight control computer (FCS), receive input from mission computer (IMDC) symbol, transfer to FCR model, generate target GUI, radar mode Handle routines very often.

For each mode, the cursor is generated from the cursor control logic and the target is detected by calculating the radar detection distance. Detected targets are calculated internally and displayed on the screen for each mode when the target enters the cursor.

The present invention embodies the characteristics and functions of a fire control radar (FCR) simulation model operating in an integrated avionic test system. The thermal control radar (FCR) simulation model is driven by a real time operation system (RTOS) to perform real time operation because it is implemented as a real electrical signal and must be linked with real equipment. The operation of the model is shown in the attached model operation diagram. The information required for the actual mission computer (IMDC), satellite inertial navigation system (EGI), flight control computer (FCS), radio altimeter (RALT) and target model is provided. Is given. At this time, the mission computer (IMDC), the satellite inertial navigation system (EGI), the flight control computer (FCS), the radio altimeter (RALT) and the target model are the fire control radar (FCR) simulation model and MIL-STD- It communicates with the protocol 1553 to send and receive data. In the middle, IOMAP and signal DB are part of the armed management computer (SMS) simulation model, which converts electrical signals into logical signals and converts them into variables that can be used in real models. After receiving the input data, the model logic shown in FIG. 4 is performed.

Next, a function of the thermal control radar (FCR) simulation model of the present invention will be described with reference to the flowchart of FIG. 5.

First, from the mission control (IMDC), satellite inertial navigation system (EGI), flight control computer (FCS), radio altimeter (RALT) and target models in the FCR simulation model of the avionics integrated test system An initial value is set by receiving a command and data related thereto (step S100).

Then, it is determined whether model execution is ON (step S120), and if model execution is ON ("YES" in step S110), the input data is processed (step S130), and model execution is ON. ) State (step S110), the initialization function is executed (step S120), and then the process returns to the step S120.

When the input data processing (step S130) is completed, the power logic is processed (step S140), and then it is determined whether model operation is ready (step S150).

When the model operation is ready in step S150 (" YES " in step S150), the FCR mode is controlled (step S160) to process the corresponding operation modes (steps S170 to S270). At this time, the offset mode includes a standby mode processing (step S170), a VS mode processing (step S180), an ACM mode processing (step S190), and a TWS mode processing (step S200). ), RWS mode processing (step S210), ASM mode processing (step S220), AGR mode processing (step S230), GM mode processing (S240), SEA mode (Mode ) Processing (step S250), GMTI mode processing (step S260), BEACON mode processing (step S270), and the like.

Then, after performing the operation modes S170 to S270, the output data is processed (step S280), and the process returns to the previous step S110. At this time, the output data processing includes updating the list data, initializing the setting value of the corresponding mode, writing the result data as a message, storing the result data in the DB, and transmitting the message to the mission computer (IMDC). do.

6 to 9 are screens outputting the result data of the thermal control radar (FCR) simulation model according to the present invention. In fact, this data is delivered to each avionics and mission computer via MIL-STD-1553.

The technical principle of the present invention is to simulate the function of the real power control radar to simulate the radar mode through the information of the target simulated in the simulation model of the fire control radar. The modes of the developed model are Primary mode with Build in Test and Standby, Range While Search (RWS), Velocity Search (VWS), Track While Scan (TSW) and Adaptive ASM (Adaptive). Search Mode (ACM), Air Combat Maneuver (ACM), Situation Awareness Mode (SAM), Single Target Track (STT) Air-to-Air mode, GM (Ground Map), GMTI (Ground Moving Target Indication), SMTT It offers Air-to-Ground modes such as Surface Moving Target Track and Sea Search.

The thermal control layer simulation model of the present invention is a navigation system generated from other equipment, namely, a mission computer (IMDC), a satellite inertial navigation system (EGI), a flight control computer (FCS), a radio altimeter (RALT), and a target model. Navigation) receives data, air data, altitude data, and target data and processes them according to the environment in which the real power control radar is being used.These data can be used to control the cursor and obtain targets from the internal logic of the model. Implement coordinate system transformation, antenna control, target detection, and more.

It will be apparent to those skilled in the art that various modifications and changes can be made in the present invention without departing from the spirit or scope of the present invention as defined by the appended claims. It will be appreciated that such modifications and variations are intended to fall within the scope of the following claims.

The present invention, through the avionics system integration test equipment (SIL: System Integration Lab) through the actual equipment or model of the other anti-vibration system without the actual fire control radar equipment to simulate the functions described above almost the same as the actual equipment functions It can be used for the Operation Flight Program (OFP) test in the computer and the integration test of the electronic system.

1 is a configuration diagram of the software of the integrated avionic test system according to a preferred embodiment of the present invention

2 is a block diagram of a signal and a database to be applied to the signal input and output in the software of the integrated avionic test system of the present invention

3 is a block diagram of a signal input and output reference system in the software of the integrated avionic test system of the present invention

4 is a functional block diagram of a thermal control radar simulation model of the present invention

5 is an operation flowchart for the thermal control radar simulation model of the present invention

6 to 9 are screens outputting the result data of the thermal power control radar simulation according to the present invention

[Description of Code for Major Parts of Drawing]

10: Real-time Operating System (RTOS) Environment Part

20: Mission Computer & Avionics System

30: Operation GUI (Graphic User Interface) program

40: GUI program

100: thermal control radar

110: Input part

120: main SW process

130: Output part

Claims (6)

(a) Mission computer (IMDC), satellite inertial navigation system (EGI), flight control computer (FCS), radio altimeter (RALT) and target model in the fire control radar (FCR) simulation model of the avionics integrated test system; An unpacking step of receiving and processing the data generated by the; (b) receives the data processed in the unpacking step and operates in one of an operation mode consisting of a standby mode, an air-to-air mode, and an air-to-air mode according to a value of a radar mode request and a radar submode request. (Cursor) processing to implement control, target acquisition, coordinate system transformation, antenna control or target detection; And (c) a packing step of writing the result data performed after the processing step as a message, storing the result data in a DB, and transmitting the message to the mission computer; Characteristic and function implementation method for the thermal control radar simulation model of the integrated avionics test system comprising a. The method of claim 1, wherein in the unpacking step of (a): The navigation data is input from the satellite inertial navigation system (EGI), the air data is input from the flight control computer (FCS), the speed data is calculated, and the symbol data is input from the mission computer (IMDC). Characteristic and function of the thermal control radar simulation model of the integrated avionic test system, characterized in that the processing to meet the FCR (FCR) and input the target data from the target model to calculate the target position How to implement. The method of claim 1, wherein the input of data in the step (a) is: A method for implementing characteristics and functions of a fire control radar simulation model of an avionics integrated test system, characterized in that data is inputted by communicating with a protocol of MIL-STD-1553. The method of claim 1, wherein the operation mode in step (b) is: A primary mode of a standby function; Air to air (Range While Search, RWS (Velocity Search), TWS (Track While Scan), ASM (Adaptive Search Mode), ACM (Air Combat Maneuver), Sit (Awareness Mode), STT (Single Target Track) Air-to-Air mode; And Air to Ground Ranging (AGR), Ground Map (GM), Ground Moving Target Indication (GMTI), Surface Moving Target Track (SMTT), Sea Search, BEACON Air-to-Ground (Air-to-Ground) mode; Characteristic and function implementation method for the thermal control radar simulation model of the integrated avionics test system comprising a. The method of claim 1, Input / output data of the thermal control radar (FCR) for the thermal control radar simulation model of the integrated avionic test system, characterized in that for monitoring (Monitoring) through a GUI window (Window) How to implement the features and functions. A recording medium storing a computer program produced by the method according to any one of claims 1 to 5.

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