KR101016812B1 - Avionics Integration Laboratory System for Test and Flight Simulation and Method of Thereof - Google Patents

Abstract

The present invention relates to an integrated avionic test system for flight simulation and test, and a method and a recording medium storing a program according to the method. It is implemented to freely add signal and add function.

The integrated avionic test method according to the present invention comprises the steps of: (a) booting the RTOS and the workstation to drive the system; (b) selecting a Simulation Control GUI window in the main menu program of the system; (c) loading a drag model, a simulated signal, and a monitoring signal database into the RTOS when a system loading button is input in the simulation control GUI window; (d) selecting one of a plurality of menus operated by the main menu program after the loading of the loading is completed; (e) operating a GUI associated with the selected menu to process corresponding signals and logic; And (f) repeating steps (d) and (e) when continuing the processing of the signal and logic, and terminating the system by unloading the system when terminating the program. Include.

Flight, aircraft, simulation, test, RTOS, GUI, simulation, software

Description

Avionics Integration Laboratory System for Test and Flight Simulation and Method of Thereof}

The present invention relates to an integrated avionic test system for flight simulation & test, and a method and a recording medium storing a program according to the method, and more specifically to existing foreign companies introduced equipment and software The present invention relates to an integrated avionic test system and method for flight simulation and test that has been newly developed to completely escape from the technology and implemented to freely add signals and add functions.

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.

There are three main functions of avionics integrated test equipment software. First of all, communication data between all avionics and simulation models should be monitored, stored and analyzed. Communication methods applied in the avionics field are classified into analog, discrete, MIL-STD-1553, and UART. The system was configured and software developed to monitor these signals. In particular, it is essential to have monitoring signal generation, monitoring, and storage / analysis functions for MIL-STD-1553 communication, which controls over 90% of all communication data.

Second, create a simulation model of all avionics. It is used when there is no use of real navigation equipment or when it is impossible to use the real navigation equipment to simulate the actual flight status. It is necessary to simulate the function of the navigation equipment and the simulated signal is realized as the actual physical signal. . We also need a flight model to simulate real flight conditions. In the case of a navigation system, the real navigation equipment cannot be used to perform the test of the mission computer logic or other navigation equipment in flight, so the flight model simulates the flight status and applies the data to simulate the navigation system. do.

Third, to implement the GUI (Graphic User Interface) that can operate the current system. It is to perform the startup and shutdown of the system, to operate the flight model, or to insert a virtual error to perform the test. In addition, it simulates the cockpit environment so that it can be operated without any real cockpit-related equipment or multi-function display (MFD) and integrated up-front control (UFF).

Conventional avionics integrated test equipment was introduced as a foreign company, imported without code, so that no modification could be made, so no signal or function could be added. In addition, since the operating system is Unix, it is inconvenient to use as a text-based program.

The present invention has been proposed in order to solve the above technical problem, flight simulation and test implemented so as to freely add signals and add functions by newly developing all the code so as to completely escape from the existing equipment and software technology introduced by foreign companies To provide an integrated avionic test system and method and a recording medium storing the program according to the method.

In addition, another object of the present invention is to provide a signal monitoring and analysis function and a hardware interface function, integrated flight test system and method and method and method for flight simulation and test that can implement all the functions of each anti-electric model The present invention provides a recording medium storing a program.

In addition, another object of the present invention is to develop a flight-based integrated test system for the flight simulation and test, and the method and the program according to the method to create a Windows-based program and to develop and use the operating program based on the graphic (Graphic) To provide a stored recording medium.

In addition, another object of the present invention is to provide an integrated avionic test system and method and method therefor for flight simulation and test having monitoring signal generation, monitoring, storage and analysis functions for communication signals applied in the avionics field. The present invention provides a recording medium storing a program.

As a means for solving the above problems, the integrated avionic test method according to the present invention comprises the steps of: (a) booting the RTOS and the workstation to drive the system; (b) selecting a Simulation Control GUI window in the main menu program of the system; (c) loading a drag model, a simulated signal, and a monitoring signal database into the RTOS when a system loading button is input in the simulation control GUI window; (d) selecting one of a plurality of menus operated by the main menu program after the loading of the loading is completed; (e) operating a GUI associated with the selected menu to process corresponding signals and logic; And (f) repeating steps (d) and (e) when continuing the processing of the signal and logic, and terminating the system by unloading the system when terminating the program. Include.

As described in claim 2, the system is operated in conjunction with an Operation GUI (Graphic User Interface) program that operates the entire system in a Windows environment and simulates a cockpit environment, and the operation GUI program. It includes software consisting of a real-time operating system (RTOS) based environment part that operates a simulation signal and monitoring database and a flight simulation model by interworking with a mission computer and a flight electronic system through a communication protocol.

The RTOS-based environment portion may include a direct I / O signal, an analog I / O signal, a differential I / O signal, a serial port (as described in claim 3). Serial Port signal is modeled, and the Operation GUI program is used for simulation control, data analysis, cockpit simulation, model control and patch in Windows environment. Characterized by operating a GUI program including.

The software may include an input portion for inputting a signal by manipulation of an aircraft pilot or via an operating program GUI window, as described in claim 4; A main software process portion for converting a signal input from the input portion into a database signal value and generating a result signal through an avionic model or GUI program logic; And an output part outputting the signal generated by the main software process part as a hardware interface signal.

The hardware interface signal, as described in claim 5, characterized in that it comprises a discrete (Discrete), analog (Analog), UART, MILBUT signal.

The operation GUI program is composed of Pythod, as described in claim 6.

As described in claim 7, the software configures a signal and a database to be applied to signal input / output based on an ICD (Interface Control Document) as described in claim 7, and is not a monitoring signal. The signal of is determined according to the logic of the simulation equipment model, and each model and signal is operated according to the RTOS scheduler.

In addition, as a means for solving the above-described problems, the integrated avionic test system according to the present invention, as described in claim 8, the method according to any one of claims 1 to 7. It is characterized by being operated by.

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According to the integrated avionic test system for flight simulation and test according to the present invention and a recording medium storing the method and the program according to the present invention, all avionics systems can be integrated to analyze each signal, If not, it is effective to apply the simulation model to perform the integrated test.

In addition, the entire code is newly developed to completely escape the existing equipment and software technology of foreign companies, and thus, it is possible to freely add signals and add functions.

In addition, the signal monitoring and analysis function and the hardware interface function is possible, and it is effective to implement all the functions of each model.

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.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. In describing the embodiments of the present invention, the same reference numerals will be used for components having the same functions and functions.

Software composition of the avionics integrated test system

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), which also operates 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.

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.

The signal input / output reference system converts a signal input from the input part 50 and a signal input from the input part 50 into a database signal value, and then outputs the result signal through the avionics model or the GUI program logic. The main software process (Main SW Process) portion 60 to generate a, and the output (70) output portion (70) for generating a signal generated in the main software process portion 60 as a hardware interface signal.

The input portion 50 may include a HOTAS side stick, a HOTAS throttle, an operation GUI input, a cockpit GUI panel, a patch, a real panel. Panel) program and input analog signal. The main software process portion 60 is composed of GUI software, Avionics model software, Flight Model, I / O Mapping program, and the like. The output part 70 is a part for outputting discrete, analog, UART, MILBUS signals, etc. to real hardware.

Input of the software consists of manipulating the aircraft pilot or entering the operating program GUI window. All of this data is converted into database signal values to generate the resulting signal through avionics model or GUI program logic. The signal generated in this way is generated as a hardware interface signal and passed to a real hardware input value, so that a physical signal is output. The actual output signal is represented by discrete, analog, UART, MILBUT, and details are the same as the input / output reference configuration of FIG. 3.

The program actually developed in the present invention is an operation model and a flight model that will implement an operation GUI program and simulated flight state and simulated avionics state. The operation GUI program is composed of Pythod, and the submenus of all menus are shown in FIG. 4.

Menu Configuration in STE Software

Figure 4 is a menu diagram of the flight simulation and test environment software developed by the present invention.

The STE software is software for avionic system integration test equipment. Software that controls and injects data and information of the actual flight environment and avionics model among the Operation Flight Program (OFP) in the avionics mission computer and the GUI (Graphic User Interface) software for conducting functional and performance tests of each avionics equipment. S / W).

The STE provides an interface with a mission computer, and provides a GUI (Graphic User Interface) of STEM capable of real-time verification of each equipment signal by monitoring signals between the interfaces.

The STE software provides an environment for independently testing the OFPs loaded on the MC and a simulated environment for performing avionic system-level tests. In addition, it provides a test function to solve a specific operation mode or a defect during operation of the OFP under test. The STE software also provides the ability to monitor controlled inputs and outputs for the OFP under test.

Simulation & Test Environment (STE) software for verifying Operation Flight Program (OFP) in the avionics mission computer is shown in FIG. 4, Simulation Setup (110), Mission Setup (120). , Cockpit Simulation (130), Data Analysis (140), Data Injection (150), Automatic Test (160), Utility (170), Admin (180) It is composed of details, etc., in each category. The parent frame, the STE, operates as a main window, and a child frame is configured through a drop-down menu of the main window.

Here, the simulation setup 110 is a menu for setting the entire STE environment, setting a section load / unload for simulation control, and various flight models. ) Set On (Model) / Off (Real), Flight Model (Avionics Configuration) Detail Settings (AVSR Settings, Flight Test), Loading IMDC OFP Settings, Operation Log Output Steps (All, Error) , Warning, Clear) settings are included.

The mission setup 120 is a menu for setting an aircraft mission of STE, and includes functions such as target setting (air-to-air, air-to-air), DTE setting (flight path, and armament information).

The cockpit simulation 130 simulates cockpit instrument clusters, mission computer power on / off simulations, MFDS simulations, IUFC simulations, and sidestick simulations. Features include settings, throttle simulations, and simulation of flight and mission instrument information.

The data analysis 140 may display, record, and retrieve all information of the STE, and includes functions such as setting a simulation of some functions for algorithm verification.

The data injection (150) is a menu for controlling all data of the STE environment, and forcibly through mux, word, analog, and discrete through a data patch. It also includes functions such as dynamic data injection and forced fault simulation via Mux.

The automatic test 160 includes a function of adjusting an aircraft through a signal simulator or an autopilot function.

The utility 170 is a menu for providing a utility related to STE, and includes functions such as a calculator, database access, and joystick settings.

The Admin 180 may check H / W signals, automatically generate a CVT / IOMAP conversion tool 100, resource information, administrator tool, database manipulation, and force patching. It includes functions such as (Patch).

The parent frame, STE, acts as the main window, and is composed of child frames through the drop-down menu of the main menu.

Figure 5 shows the data flow (Flow) between the currently simulated avionics and flight model. The data shown in the data flow is largely based on system global data used internally, MILBUS data connected to external equipment, panel discrete through external avail- ability equipment, and analog signals as database-based signal values. The output value of each model is sent to each device or MC (Mission Computer).

Avionics Integrated Test Software

6 is a flowchart illustrating the operation of the integrated avionic test software according to the preferred embodiment of the present invention.

In order to run the system, it is necessary to first boot the RTOS and the workstation (step S10). Thereafter, the main menu program is executed (step S10) and a simulation control GUI window (see FIG. 7) is selected (step S30).

Then, by pressing the System Loading button (see Fig. 7) in the simulation control GUI window (step S40), the currently configured electric power model, the simulated signal and the monitoring signal database are raised above the RTOS (step S50).

After loading is finished, if one of the menus (steps S30 to S120) operated by the main program is selected ('Y' in steps S30 to S120), the GUI associated with the selected menu is operated (steps S130 to S180). The signal and logic are processed (steps S190 to S240).

When the program is to be terminated, the system is unloaded (Y in step S60) and the main program is terminated (Y in step S310).

As described above, the avionics integrated test system according to the present invention and the recording medium storing the method and the program according to the present invention are developed using the ADS2, the Avionics Test program, to develop the Avionics Integration Laboratory. By doing so, the technical problem of the present invention can be solved.

Preferred embodiments of the present invention described above are disclosed to solve the technical problem, and those skilled in the art to which the present invention pertains (ie, those skilled in the art) various modifications, changes, and additions within the spirit and scope of the present invention. It should be understood that such modifications and the like fall within the scope of the following claims.

Although the present invention has been described using an aircraft embedded system for flight simulation and test as an example, the present invention is not limited thereto and may be applied to all software and systems.

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

Figure 4 is a menu diagram of the flight simulation and test environment software developed by the present invention

5 is a functional configuration diagram showing the data flow (Flow) between the current simulation equipment and flight model

6 is an operation flowchart for the integrated avionic test software according to a preferred embodiment of 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

50: Input part

60: Main SW Process

70: output part

110: Simulation Setup

120: Mission Setup

130: Cockpit Simulation

140: Data Analysis

150: data injection

160: Automatic Test

170: Utility

180: Admin

Claims (9)

delete In the integrated avionic test method for flight simulation and test, (a) booting the RTOS and the workstation to drive the system; (b) selecting a Simulation Control GUI window in the main menu program of the system; (c) loading a drag model, a simulated signal, and a monitoring signal database into the RTOS when a system loading button is input in the simulation control GUI window; (d) selecting one of a plurality of menus operated by the main menu program after the loading of the loading is completed; (e) operating a GUI associated with the selected menu to process corresponding signals and logic; And (f) repeating steps (d) and (e) when continuing the processing of the signal and logic, and terminating the system by unloading the system when terminating the program. But The system is: Operation Graphic User Interface (GUI) programs that run the entire system in a Windows environment and simulate the cockpit environment, The software consists of RTOS (Real-time Operating System) based environment part that operates with simulation computer and avionics model through interworking with operation GUI program and interworking with mission computer and avionics system through communication protocol. Avionics integrated test method comprising a. The method of claim 2, The RTOS-based environment part models a direct I / O signal, an analog I / O signal, a differential I / O signal, and a serial port signal. The Operation GUI program is for operating a GUI program including Simulation Control, Data Analysis, Cockpit Simulation, Model Control and Patch in a Windows environment. Avionics integrated test method characterized in that. The software of claim 2 wherein the software is: An input portion for inputting a signal by an aircraft pilot or through an operating program GUI window; A main software process portion for converting a signal input from the input portion into a database signal value and generating a result signal through avionics model or GUI program logic; And And an output portion for outputting the signal generated by the main software process portion as a hardware interface signal. The hardware interface signal of claim 4, wherein: An integrated avionic test method comprising discrete, analog, UART, and MILBUT signals. The method of claim 2, The operation GUI program is integrated flight test method, characterized in that composed of Pythod. The software of claim 2 wherein the software is: The signals and database to be applied to the signal input and output are configured based on the ICD (Interface Control Document) .The simulated signals, not the monitoring signals, determine the values according to the logic of the simulation equipment model, and operate each model and signals according to the RTOS scheduler. Avionics integrated test method, characterized in that. An integrated avionics test system, which is operated by the method according to any one of claims 2 to 7. delete

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