KR20110028823A - Method for character and function for store management system simulation model of avionics integration laboratory system, and system of the same and media that can record program for method the same - Google Patents

Abstract

PURPOSE: A method and system for realizing a characteristic and a function about a SMS simulation model of an aviation electronic integration test system and a recording medium storing a program by the method are provided to facilitate data input/output by interfacing a database with a data link between a system integration lab environment and equipment. CONSTITUTION: A SMS(Store Management System) simulation model of an aviation integration test system receives a command and armed data related to the command from a IMDC(Integrated Mission Design Center). Armed data mounted in an aircraft is inputted into a SMS(100) and analyzed. The flight state and armed mode state of the aircraft is determined and a change request of a pilot is checked through the IMDC. If a change request exists, corresponding data is changed into an input value and an armed list data is determined by setting a content which type and state of a current arm is determined or changed.

Description

Methods for implementing the characteristics and functions of the armed management computer simulation model of the avionics integrated test system, and a recording medium storing the system and the program according to the method.Method for Character and Function for Store Management System and System of The Same and Media that can Record Program for Method the same}

The present invention relates to a method for implementing characteristics and functions of a store management system (SMS) simulation model of an integrated avionics test system, and a recording medium storing the system and a program thereof. More specifically, the armed management computer of the avionics integrated test system, which has developed an armed management computer (SMS) simulation model that has been developed in a foreign country but has not had any technology transfer, and more accurately implements the operation logic that the existing model did not accurately implement. The present invention relates to a method for implementing characteristics and functions of a simulation model, a system, 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, Armed Management Computers (SMSs) are expensive equipment among aviation equipment and are very difficult to diagnose. By modeling this SMS in software, you can exchange data with other devices without the actual SMS device. And it is easy to diagnose the problem more easily than the actual equipment and implement the function to add in software.

However, the existing SIL (System Integration Lab) is one of the limited items of technology transfer, and many functions are missing when it is introduced in Korea, and only simple functions are supported.

Currently, SMS supports only some limited and simple functions: Air-to-Air (AA), Air-to-Ground (AG), Emergency Jettison (EJ), and Selective Jettison (SJ) modes.

In addition, there is no function of displaying input data and output data of an SMS on a specific screen in real time. Therefore, it is not possible to monitor the input / output of the SMS.

In addition, there is no way to modify the software if an internal logic change or signal is added.

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. As a result, software maintenance is difficult.

The technical problem to be solved by the present invention in order to solve the above-mentioned problems, AA (Air-to-Air), AG (mode) of the internal management mode (Store Management System (SMS)) that is currently limitedly supported For the armed management computer simulation model of the avionics integrated test system that can model all functions such as air-to-ground, emergency jettison (EJ), selective jettison (SJ), gun, and built-in test (BIT) The present invention provides a method of implementing features and functions, a system 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 facilitate data input (Input) / Output (Interfacing) by interfacing with the DB built for the data (Interworking) between the System Integration Lab environment and the equipment (Data). The present invention provides a method of implementing the characteristics and functions of the armed management computer simulation model of the avionics integrated test system, and a recording medium storing the system and the program according to the method.

In addition, another technical problem to be achieved by the present invention, the characteristics of the armed management computer simulation model of the avionics integrated test system that can implement the software so that the software execution environment in the window (Windows) and A method of implementing a function, a system thereof, and a recording medium storing a program according to the method are provided.

In addition, another technical problem to be achieved by the present invention, armed management computer simulation of the integrated avionic test system capable of monitoring the input / output data of the SMS through the GUI window (Window) The present invention provides a recording medium storing a feature and a function of a model, a system thereof, and a program according to the method.

In addition, another technical problem to be achieved by the present invention is to develop an armed management computer 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 method of implementing the characteristics and functions of the armed management computer simulation model of the avionics integrated test system, and a recording medium storing the system and the program by the method.

In addition, another technical problem to be achieved by the present invention, armed management of the avionics integrated test system that can freely add signals and add functions by newly developing all the code to completely escape the existing equipment and software technology introduced by foreign companies The present invention provides a method for implementing characteristics and functions of a computer simulation model, a system and a recording medium storing a program according to the method.

In addition, another technical problem to be achieved of the present invention, the characteristics of the armed management computer simulation model of the avionics integrated test system capable of signal monitoring and analysis function and hardware interface function, and can implement all the functions of each anti-electric model The present invention provides a recording medium storing a method for implementing a function and a system 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 armed management computer 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 method of implementing characteristics and functions of an armed management computer simulation model, a system and a recording medium storing a program according to the method.

As a means for solving the above-mentioned technical problem, the invention described in claim 1, "(a) command from the mission computer (IMDC) in the armed management computer (SMS) simulation model of the integrated aircraft test system and related armed information data Receiving an input; (b) analyzing the input armed information data and inputting the armed information data currently mounted on the aircraft to the SMS, determining whether the current aircraft is on the ground or in flight, determining the armed mode status, and performing the task. After checking the pilot's change request through the computer, if there is a change request, it receives the input value and changes the data, and sets the determined or changed information as the armed list data to determine the type and status of the current arming. Determining a master mode (air-to-air, air-to-ground, emergency drop, selective drop, gun) of the SMS by determination, and checking an armed state according to the master mode to determine an operation mode; (c) when the operation mode is determined, entering a corresponding AA, AG, emergency jet, selective jet, Gun mode; (d) updating the list data after performing the operation mode, initializing a setting value of the corresponding mode, writing the result data as a message and storing the result data in a DB; And (e) transmitting the message to the mission computer. ≪ / RTI >

According to the invention of claim 2, "The input of the armed information data in the step (a) is: In the case of a real SMS, the communication is performed by a protocol called MIL-STD-1553 to receive data. In the case of the model SMS, the characteristics and functions of the armed management computer simulation model of the avionics integrated test system are received.

According to the invention described in claim 3, "Archival management computer simulation of the integrated avionic test system according to claim 1, wherein in the step (c), the sub-mode according to each master mode is determined according to the type of weapon. How to implement features and functionality for the model. ”

According to the invention of claim 4, "The avionics integrated test according to claim 1, wherein the input / output data of the SMS can be monitored through a GUI window. How to implement the features and functions for the computer simulation model of the armed management system of the system.

In addition, as a means for solving the above-described technical problem, the invention described in claim 5 is characterized in that "the operation of the avionics integrated test system characterized in that it operates by the method according to any one of claims 1 to 4. Satellite inertial navigation system simulation model implementation system.

In addition, as a means for solving the above-described technical problem, the invention described in claim 6, "The recording medium characterized in that the program stored in the method according to any one of claims 1 to 4. to provide.

According to the present invention, the current mode of the currently supported SMS (Air-to-Air), Air-to-Ground (AG), Emergency Jettison (EJ), Selective Jettison (SJ), Gun In addition, all functions of BIT (Built In Test) were modeled.

In addition, a DB is established for interoperation with the Operational Flight Program (OFP) and the System Integration Lab (SIL), and the input / output data of the SMS (Store Management System) is stored in the DB through the established DB. Read / Write is available in real time, and monitoring is possible in real time.

In addition, the configuration of input / output data of the SMS can be confirmed by a GUI window.

In addition, it is possible to develop an armed management computer 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 armed management computer 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, signal monitoring and analysis functions and hardware interface functions are possible, and all functions of each model can be implemented.

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.

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 the drawings, parts irrelevant to the description are omitted in order to clearly describe the present invention, and like reference numerals designate like parts throughout the specification.

First, the present invention is a simulation model for simulating a satellite inertial navigation system as part of an avionics model constituting an equipment (SIL: System Integration Lab) for performing the avionics system integration test. 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 an armed management computer simulation model, which is an important factor in developing the avionics system integrated test equipment composed only of 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.

Hereinafter, specific technical contents to be implemented in 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 interworks with a mission computer and Avionics system 20 (real equipment) through a communication protocol, and also interoperates with the operation GUI program portion 30. Models the direct I / O signal, analog I / O signal, differential I / O signal, and serial port signal. 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 environmental model, satellite inertial navigation system, etc.), and this simulation model is also operated in 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 of the armed management computer (SMS) 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 generates an IOMAP for monitoring communication data between an armed management computer (SMS) simulation model and a mission computer (IMDC) and inputs and outputs an I / O to a real hardware device. It is configured to.

The mission computer (IMDC) communicates with the integrated test equipment using a protocol called 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 an armed management computer (SMS) simulation model of the present invention.

The Store Management System (SMS) simulation model includes an unpacking step 110 for receiving a command and related data from an IMDC, and the unpacking step 110. In the processing step 120 to process the data received from the processing (120), and the packing (130) step of delivering the data processed in the internal processing (120) to the mission computer (IMDC) Consists of.

[Unpacking Step]

The unpacking step 110 is a step of receiving data of a mission computer (IMDC). In the case of a real armed management computer (SMS), the unpacking step 110 is directly input through a 1553 mux. In case of armed management computer (SMS), input is from database of test equipment. In other words, if the model (IMDC) writes the relevant data to the DB, the Armed Management Computer Model (SMS Model) uses the Unpacking routine to unpack the relevant data in the DB. Bring to

[Internal Processing Step]

Internal processing (SMS) of the armed management computer (SMS) can be divided into the pre-mode operation mode, the mode operation stage and the mode operation stage.

Mode before operation

Before determining the mode, the unpacked data of the mission computer IMDC is analyzed to determine the initial value of the armed management computer SMS. Each step proceeds as follows. In the model functional block diagram of FIG. 4, "Power Control" and "SMS Mode Control" are shown.

1. DTE Data Input Processing

First, armed information data is read from a data transfer equipment (DTE) device and the armed information currently mounted on an aircraft is inputted to an armed management computer (SMS) for the first time. The type and characteristics of the armament will be input.

2. SMS Condition and Status Determination

It determines whether the aircraft is on the ground or in flight, and determines the status of armed mode.

3. Confirm Change Request of IMDC

If the pilot changes the setting up to step 2, the change can be made through a change request. The pilot's change request comes from the mission computer (IMDC). If there is a CR, the input value is received in step 3 and the corresponding data is changed.

4. Armed Inventory Data Settings

In the inventory data setting step, the contents of the previous step (including CR change values) are finally written to the inventory. At this point, the inventory determines the type and status of the current weapon, and reflects this result in the operational mode phase.

5. Operation Mode

The operation mode decision step is based on the Master Mode (Air to Air (AA), Air to Ground (AG), Emergency Drop (EJ), Selective Drop (SJ) of the Armed Management Computer (SMS). ), Gun, self test (BIT). Sub-modes are also determined according to each master mode according to the type of arming.

6. System Status Update

The System Status Update step checks the armed status (Ready, Blank, Mal, Hung) according to the master mode of the previous stage, and maintains the information until the armed firing.

Mode of operation

When the operation mode is determined, the air to air (AA), air to ground (AG), emergency release (EJ), selective delivery (SJ), gun (Gun) mode is entered. Each step does not overlap and only the corresponding mode is entered / exited.

1.Air to Air Mode (Air to Air: AA)

a. Weapon Select

b. Station Select

c. Determine Cooling Options (determining the unique characteristics of the missile)

d. FOV determination (determination of the unique characteristics of the missile)

e. LOS determination (determining the unique characteristics of the missile)

f. Threshold Determination (Missile's Unique Characterization)

g. Uncage Mode Determination (Missile's Unique Characterization)

h. Acquisition Lambda Determination (Missile's Unique Characterization)

i. Release Sequence

The above steps are executed sequentially. If an unsatisfied condition occurs in the routine, it does not go to the release sequence. The decision of each stage sets the options for AA AA.

2. Air to Ground (AG)

a. AG Weapon Select

b. EO Processing / Spring Rocket Processing Processing

c. In case of EO Processing

A. Station Select

B. Power On Select

C. Determine Maverick Operation Mode

D. Determination of Release Pulse

E. Manual Sequence Command (determining the unique characteristics of the missile)

F. Track Command (determining the unique characteristics of the missile)

G. Uncage Command (determining the unique characteristics of the missile)

H. FOV Determination (Missile's Unique Characterization)

I. Boresight Determination (Missile's Unique Characterization)

J. Determination of Tracking Polarity (determining the unique characteristics of the missile)

K. Los Azimuth Elevation Determination (Missile's Unique Characterization)

L. Release Sequence

b. In the case of boom rocket processing

A. Determine Weapon Category

B. Weapon Profile Determination

C. Determine Pair Option

D. Determine Pair Station

E. Rocket Fuze Determination (Missile's Unique Characterization)

F. Impact Separation Determination (Missile's Unique Characterization)

G. Determine Release Interval

H. Determination of Release Quantity

I. Release Release Determination (Missile's Unique Characterization)

J. Release Sequence

Air to ground (AG) mode is divided into EO (Electric Optical) mode and boom (Bomb) / Rocket mode according to the type of weapon selected. The determining step of the selected mode selects the arming option.

1. Emergency Jettison (EJ) mode

a. Select All Station

b. Jettison Sequence

During the EJ, you will select all of the air to ground (AG) weapons, except AA, and immediately release them.

2. Selective Jettison (SJ)

a. Station selection

b. Jettison Type Decision

c. Jettison Sequence

Selective drop (SJ) is dropped by conditions (Station, jettison type) according to the pilot's choice.

3. Gun Mode

a. Fire Sequence

In Gun mode, the number of loaded and shot fired is calculated to show the remaining quantity.

Mode after operation

After performing the selected operation mode (Operation Mode) to update the inventory data (Inventory Data). And initialize the setting value of the relevant mode. Write maintenance message of DB to send result data to mission computer (IMDC).

And if necessary, it performs BIT (Built In Test) to diagnose SMS failure.

[Packing stage]

The packing step sends various results from the internal operation of the SMS to the mission computer IMDC. As with unpacking, SMS's model writes the result to DB, and the packing routine sends the data to the mission computer (IMDC).

The present invention implements the characteristics and functions of the Armed Management Computer (SMS) Simulation Model operated in the avionics system integrated test equipment. The armed management computer (SMS) simulation model is implemented as a real electrical signal, so it is driven by a real time operation system (RTOS) to perform real time operation because it must be linked with real equipment. The operation of the model will give the necessary information to the actual mission computer as shown in the attached model operation diagram. At this time, the mission computer communicates with the Armed Management Computer (SMS) simulation model and the protocol of MIL-STD-1553 to exchange 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, model logic as shown in FIG. 4 is performed.

Next, the function of the armed management computer (SMS) simulation model of the present invention will be described with reference to the flowchart of FIG. 5.

First, in the armed management computer (SMS) simulation model of the avionics integrated test system, an initial value is set by receiving a command and related arming information data from the mission computer (IMDC) (step S110).

Then, it is determined whether model execution is ON (step S120), and if model execution is ON ("YES" in step S120), the input data is processed (step S140), and model execution is ON. ) State (step S120), the initialization function is executed (step S130), and then the process returns to the step S120.

When the input data processing (step S140) is completed, the power logic is processed (step S150), and then it is determined whether model operation is ready (step S160).

When the model operation is ready in step S160 (YES in step S160), the SMS mode and the SMS sub-mode are sequentially controlled (steps S170 and S180), and the corresponding operation mode (air to air (AA)). , Air to ground AG, emergency jet EJ, selective jet SJ, Gun mode} (steps S190 to S230).

Then, after performing the operation mode, the output data is processed (step S240) and the process returns to the previous step S120. At this time, the output data processing includes updating the list data, initializing the setting value of the corresponding mode, writing the result data into a message, storing the result data in a DB, and transmitting the message to the mission computer (IMDC). Include.

6 to 8 are screens outputting the result data of the armed management computer (SMS) simulation model according to the present invention. In fact, this data is delivered to each avionics and mission computer via MIL-STD-1553.

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.

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 an armed management computer (SMS) simulation model of the present invention;

5 is an operation flowchart for the armed management computer simulation model of the present invention

6 to 8 are screens outputting the result data of the satellite inertial navigation apparatus 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: armed management computer (SMS)

110: Input part

120: main SW process

130: Output part

Claims (6)

(a) receiving a command from the mission computer (IMDC) in the armed management computer (SMS) simulation model of the avionics integrated test system and related armed information data; (b) analyzing the input armed information data and inputting the armed information data currently mounted on the aircraft to the SMS, determining whether the current aircraft is on the ground or in flight, determining the armed mode status, and performing the task. After checking the pilot's change request through the computer, if there is a change request, it receives the input value and changes the data, and sets the determined or changed information as the armed list data to determine the type and status of the current arming. Determining a master mode (air-to-air, air-to-ground, emergency drop, selective drop, gun) of the SMS by determination, and checking an armed state according to the master mode to determine an operation mode; (c) when the operation mode is determined, entering a corresponding AA, AG, emergency jet, selective jet, Gun mode; (d) updating the list data after performing the operation mode, initializing a setting value of the corresponding mode, writing the result data as a message and storing the result data in a DB; And (e) sending the message to the mission computer; Features and functions for the armed management computer simulation model of the avionics integrated test system comprising a. The method of claim 1, wherein the input of the armed information data in step (a) is: Armed management computer simulation of the avionics integrated test system characterized by receiving data by performing communication using the protocol of MIL-STD-1553 in case of real SMS and receiving data from database of test equipment in case of model SMS. How to implement the features and functionality for the model. The method of claim 1, wherein in step (c): Characteristic and function implementation method for the armed management computer simulation model of the avionics integrated test system, characterized in that it determines the sub-mode according to each master mode according to the type of weapon. The method of claim 1, Characterization and function implementation method for the armed management computer simulation model of the integrated flight test system, characterized in that the input / output data of the SMS can be monitored through a GUI window (Monitoring) . A system for implementing a satellite inertial navigation system simulation model for an integrated avionics test system, which is operated by the method according to any one of claims 1 to 4. A recording medium which stores a program by the method according to any one of claims 1 to 4.

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