KR101658563B1 - External Tactician for verifying Embedded Computer of Aircraft and Operation Method thereof - Google Patents

Abstract

An external device simulator system for an embedded computer verification of an aircraft of the present invention includes a computing module 11, an interface module 15, and a power supply module 16, which communicate with each other without degradation of performance, A scenario for verifying the external device simulator 10 and the aircraft embedded computer 30 having the system software 10-1 and the application software 10-2 together with the external A monitoring computer 20 for verifying the performance of the hardware and software of the aircraft embedded computer 30 is included in the device simulator 10 so that the S / W module (H / W initialization, communication function, etc.) And accurately verify some of the S / W modules mounted on the actual external device when interworking with the aircraft embedded computer 30 through this.

Description

[0001] The present invention relates to an external device simulator system for verifying an embedded computer of an aircraft,

The present invention relates to an embedded computer verification of an aircraft, and more particularly, to an external device simulator system for an embedded computer verification of an aircraft using an H / W (HardWare) board and a S / W (SoftWare) And operating methods.

Generally, among the equipments mounted on an aircraft, some of the embedded computers, which are avionics devices, manage separate external devices attached to the outside of the aircraft. Since the external device is managed by the embedded computer, the aircraft can perform a variety of tasks by attaching a POD external device or smart mount for electronic warfare.

To do this, the embedded computer functions installed on the aircraft must be verified.

For example, an external device simulator main body for verifying an embedded computer function includes a communication function with an aircraft, a communication simulating function with an external device internal subsystem, a discrete input / output signal to be interlocked, and an analog input / output signal. In particular, the external device simulator main H / W, which is in charge of communication with an aircraft, executes a specific algorithm according to the purpose of the external device or performs signal processing and command processing from the aircraft. This process is interlocked with the embedded computer mounted on the aircraft, so that the final function of the embedded computer is verified. To this end, the H / W (Hardware) specification of the external device simulator is the same as the H / W specification of the external device.

Korean Patent Publication No. 10-2010-0066124 (June 17, 2010)

However, if the embedded computer of the aircraft is verified as an external device simulator having the same or similar H / W specification as its own, even an embedded computer normally operating at the time of verification will have difficulty in normal real-time processing of an external device actually mounted on the aircraft platform There is no other choice.

The fundamental reason for this is that the H / W specification of the aircraft's embedded computer is superior to the H / W specification of the external device mounted on the aircraft platform, and the external device simulator has the same or similar H / W specification as the aircraft's embedded computer , There is a difference in H / W specification between the embedded computer and the external device simulator and the external device for mounting the aircraft platform.

Therefore, the difficulty of normal real-time processing between the embedded computer of the aircraft and the external device for mounting the platform of the aircraft can not be solved without modification of the simulation method of the embedded computer and the external device of the aircraft.

In view of the above, the present invention can be applied to an S / W module (H / W initialization) used in an actual external device by configuring the H / W board and the S / , Communication function, etc.), and to verify the performance of some S / W modules mounted on actual external devices when interfacing with an embedded computer of an aircraft, an external device simulator system for the verification of the embedded computer of the aircraft and its operation The purpose of the method is to provide.

According to another aspect of the present invention, there is provided an external device simulator system for verifying an aircraft embedded computer, which includes an embedded computer hardware and software for managing an external device, An external device simulator with system software and application software with modules and power supply modules; A monitoring computer that establishes a scenario for verifying an aircraft embedded computer and transmits the scenario to the external device simulator and executes a scenario in which the external device simulator is set to verify the performance of hardware and software of the embedded computer of the aircraft; Is included.

Wherein the operation module and the interface module of the external device simulator have the same specifications as the hardware of the external device of the aircraft, and the system software and the application software of the external device simulator are executed in the same manner as the software operating the external device of the aircraft do.

The system software includes a real time operating system and firmware, and the application software functions as an external device communication simulation model, a discrete signal simulation model, an analog signal simulation model, and a monitoring computer communication interface module Respectively.

The monitoring computer includes GUI software, which functions as simulator internal function monitoring, simulator state monitoring and fault simulation GUI, discrete signal setting and monitoring, and analog signal setting and monitoring, respectively .

The embedded computer includes embedded software and embedded hardware. The embedded software and the embedded hardware are used for communication simulation function between the aircraft and an external device internal subsystem, and other interlocked discrete input / output Signal, and analog input / output signal generation, respectively.

According to another aspect of the present invention, there is provided a method of operating an external device simulator system for verifying an aircraft embedded computer, the method comprising the steps of: (A) (B) a monitoring computer that communicates with the external device simulator sets a simulated item, transfers the set simulated item to the external device simulator, and executes a scenario based on the simulated item set; (C) transmitting and receiving data discrete signals and analog signals to and from an aircraft embedded computer operating in a scenario based on simulated items in which the external device simulator is set; (D) When the scenario is suspended by the monitoring computer, an external device simulator operating procedure is performed in which the monitoring computer analyzes the execution result of the scenario.

In the external device simulator operating procedure, (a) whether or not an IBIT instruction is present in the IBIT simulation is determined; (b) if the IBIT instruction is present, it is determined whether or not the internal module BIT value set by the monitoring computer is faulty; c) When the internal module BIT value is faulty, the internal module BIT result is set to Fault, and then the external device error BIT result is transmitted. (d) If there is no fault of the internal module BIT value, it is determined after setting the IBIT response time Fault set by the monitoring computer, and then the BIT result response time Fault is set when the IBIT response time fault is set.

And is configured to transmit an error to the IBIT result value or not to perform a limited IBIT execution time according to the scenario setting when transmitting the IBIT command or transmitting the IBIT command execution result.

The IBIT simulation is stopped after the absence of the IBIT command in (a), the transmission of the external device error BIT result in (c), or the transmission of the BIT result response time fault setting in (d).

The present invention not only verifies the function of an aircraft embedded computer through an external device simulator using a main H / W board used in an actual external device, but also real-time processing and some functions of the software It can be verified at the same time.

In addition, the present invention simulates various error situations as well as normal interlocking with an aircraft embedded computer through setting various error scenarios through an external monitoring PC of an external device simulator, thereby performing detailed functional verification of the aircraft embedded computer .

In addition, the external device simulator main body of the present invention is characterized in that all communication messages, discrete signals and analog signals between platforms are logged together with time information, and real-time or post-analysis is possible through an external monitoring PC Especially, it is possible to interwork with the fiber channel communication method which will be applied to the inside of the aircraft in the future because the speed is high and the wiring is simple.

FIG. 2 is a software block configuration of an external device simulator used in the present invention, and FIG. 3 is a block diagram of an external device simulator system for an aircraft embedded computer verification according to the present invention. FIG. 4 is an IBIT processing flowchart of the external device simulator used in the present invention, and FIG. 5 is an example of an IBIT setting UI of the external device simulator used in the present invention.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings, which illustrate exemplary embodiments of the present invention. The present invention is not limited to these embodiments.

1 shows a configuration of an external device simulator system for verifying an aircraft embedded computer according to the present embodiment.

As shown, the external device simulator system is configured for performing various functions and checking and post-analysis of the aircraft embedded computer (Embedded Computer) 30. The aircraft embedded with the performance verification function includes Embedded Software 30-1 and Embedded Hardware 31 (hereinafter, referred to as Embedded H / W).

The external device simulator system for verifying the aircraft embedded computer includes an external device simulator 10 composed of a computing module 11, an interface module 15 and a power supply module 16, a monitoring computer 20).

Specifically, the external device simulator 10 uses a communication function with an aircraft, a communication simulating function with other systems in the external device, and other interlocked discrete input / output signals and analog input / output signals. In addition, the external device simulator 10 logs all communication messages, discrete signals, and analog signals between the platforms as time information, and can perform real-time or post-analysis through the monitoring computer 20.

The calculation module 11 includes a communication board 12, a signal processing board 13, and a power board 14 using an H / W board that actually enters an external device. In particular, the computing module 11 may perform specific algorithms or signal and command processing from the aircraft according to its purpose.

The interface module 15 provides a communication protocol between the monitoring computer 20 and the aircraft embedded computer 30. Particularly, since the 1553 bus is used between the avionic electronic devices inside the aircraft, the 1553 bus and the discrete signal are applied between the external device simulator 10 and the aircraft embedded computer 30, but this is merely an example of implementation of the present invention There is no restriction on the communication method. Therefore, the external device simulator 10 has a scalability that can be interlocked with a fiber channel communication method in which the speed applied to the interior of an aircraft is fast and the wiring is simple in the future.

The power supply module 16 is connected to the power supply board 14 of the computing module 11 to supply external power to the external device simulator 10.

The monitoring computer 20 not only confirms data exchanged with the platform but also sets various scenarios of the external device simulator 10 for verifying the aircraft embedded computer 30.

2 illustrates a software block configuration of the external device simulator 10 and the monitoring computer 20. In FIG.

As shown in the figure, a system software 10-1 (hereinafter referred to as a system S / W) and application software 10-2 (hereinafter referred to as an application S / W).

The system S / W 10-1 is composed of an RTOS / firmware. Here, the RTOS is a real time operating system, which is a built-in system development support tool that supports various development environments required for program development such as debugging, input / output, time division processing, and multitasking functions. Firmware refers to software that does not need to be changed in order to speed up the information processing and simplify the circuit by writing it as hardware by fixing it to ROM (ROM) or the like.

The application S / W 10-2 includes an external device communication simulation model 12-1 for controlling the communication board 12, a discrete signal simulation model 13-1 for controlling the signal processing board 13, A signal simulation model 13-2, and a monitoring computer communication interface module 15-1 for controlling the interface module 15.

Especially. The system S / W 10-1 and the application S / W 10-2 also utilize an S / W module (H / W initialization, communication function, etc.) And verifies some of the S / W modules mounted on the actual external device in conjunction with the S / W module (30).

The monitoring computer 20 includes GUI software (Graphic User Interface Software) 20-1 (hereinafter referred to as GUI software). The GUI S / W 20-1 includes simulator internal function monitoring 22-1, simulator state monitoring and fault simulation GUI 22-2, discrete signal setting and monitoring 23-1, And monitoring (23-2).

 Therefore, the monitoring computer 20 can provide user convenience in setting various scenarios of the external device simulator 10 for verifying the data exchanged with the platform and the aircraft embedded computer 30.

3 and 4 are diagrams for explaining the scenario implementation of the external device simulator 10 for performing various functions and monitoring and analyzing various functions associated with the monitoring computer 20 and the aircraft embedded computer 30 Fig. That is, a method of operating an external device simulator system for verifying an embedded computer of an aircraft will be described below.

3 is an operating procedure of the external device simulator 10. When the power of the external device simulator 10 is turned on (S10), the external device simulator 10 is set to a standby state after being booted (S20). Next, the monitoring computer 20 sets a simulation item and transmits it to the external device simulator 10 (S30), and then executes a scenario based on the simulated item set (S40). Then, the external device simulator 10 operates to transmit and receive data discrete signals and analog signals to and from the aircraft embedded computer 30 (S50-1) (S50-1). Thereafter, the monitoring computer 20 suspends the execution of the scenario (S60) and analyzes the result of executing the scenario (S70).

FIG. 4 is an IBIT processing procedure of the external device simulator 10 when the external device simulator 10 is operated. When simulation of an Initiated Built In Test (IBIT) starts as in S100, whether an IBIT instruction exists . If there is no IBIT instruction, the flow advances to step S150 to stop the IBIT simulation. If the IBIT instruction is present, the flow advances to step S120 to determine whether the internal module BIT (Built In Test) value set by the monitoring computer is faulty.

If there is a fault of the internal module BIT value in S120, the internal module BIT fault setting is performed by entering S121, and then the external device error BIT result is transmitted as shown in S122. Then, S150 is entered to stop the IBIT simulation.

On the other hand, if there is no Fault of the internal module BIT value in S120, the process goes to S130 to determine the IBIT response time Fault setting set by the monitoring computer.

If the IBIT response time Fault is set in S130, the BIT result response time Fault is set by entering S131, and the external device BIT result is transmitted after the external device BIT result response time as in S132. Then, S150 is entered to stop the IBIT simulation.

However, if the IBIT response time Fault is not set in S130, the external device normal BIT result is transmitted by entering S140. Then, S150 is entered to stop the IBIT simulation.

On the other hand, FIG. 5 shows an example of an IBIT setting UI (User Interface) of the external device simulator 10. As shown in the figure, the IBIT result Fault is turned on and off (ON and OFF) for each internal module (modules 1, 2, 3, 4 and 5) . ≪ / RTI > Here, the internal modules 1, 2, 3, 4, 5 mean an internal subsystem of the external device simulator 10 or an external device associated with the aircraft embedded computer 30.

Therefore, it can be seen that the external device simulator 10 is capable of verifying the aircraft embedded computer 30 with dynamic data simulations that change over time by the monitoring computer 20. In addition, the external device simulator 10 verifies the aircraft embedded computer 30 in the same environment as the actual external device while performing real-time communication with the aircraft embedded computer 30 while simultaneously executing the algorithm applied to the actual external device You can do it.

As described above, the external device simulator system for aircraft embedded computer verification according to the present embodiment is implemented in various scenarios of the external device simulator 10. As an example of such a scenario, it is possible to set up to perform a normal communication function with the aircraft embedded computer 30, and to set an error function to the external device simulator 10 to deliberately check whether the aircraft embedded computer 30 is operating correctly Do it.

If the IBIT command is transmitted to the external device in the aircraft embedded computer 30 and the external device transmits the IBIT command execution result, the external device may transmit an error to the IBIT result value according to the scenario setting, It is also possible to set not to keep the IBIT execution time. Especially, in these two cases, the S / W function is verified by confirming whether the aircraft embedded computer 30 operates with the designed logic. As described above, in response to the communication response with the aircraft embedded computer 30, the platform generates an error for the response value and time described in the design document such as ICD (Interface Control Document) ) To verify all of the software functions.

 In addition, the external device simulator system for verifying the aircraft embedded computer 30 according to the present embodiment and its operation method may perform periodic communication with the aircraft embedded computer 30 after power is applied according to the characteristics of the external device And performs communication for a given time interval or under specific conditions, the external device simulator proposed in the present invention includes all of these cases. In particular, in the case of periodic communication, the external device simulator 10 performs a normal operation at first, and then generates error data only for a certain time region and generates normal data again. In addition, the external device simulator 10 of the present invention also has a function of generating data that changes dynamically during a specific time period.

10: External device simulator 10-1: System software
10-2: Application Software
11: Operation module
12: Communication board 12-1: External device communication simulation model
13: Signal processing board 13-1: Discrete signal simulation model
13-2: Simulation model of analog signal
14: Power board 15: Interface module
15-1: Monitoring computer communication interface module
16: power supply module 20: monitoring computer
20-1: GUI Software (Graphic User Interface Software)
20-2: Simulator Utility 22-1: Monitoring Simulator Internal Function
22-2: Simulator status monitoring and fault simulation GUI
23-1: Discrete signal setting and monitoring
23-2: Analog signal setting and monitoring
30: Aircraft Embedded Computer
31: Embedded Hardware
30-1: Embedded Software

Claims (14)

delete delete delete delete (A) An external device simulator booted by power on (ON) enters a setting standby state;
(B) a monitoring computer that communicates with the external device simulator sets a simulated item, transfers the set simulated item to the external device simulator, and executes a scenario based on the simulated item set;
(C) transmitting and receiving data discrete signals and analog signals to and from an aircraft embedded computer operating in a scenario based on simulated items in which the external device simulator is set;
(D) when the scenario is suspended by the monitoring computer, an external device simulator operating procedure is performed in which the monitoring computer analyzes the execution result of the scenario;
In the external device simulator operating procedure, (a) whether or not an IBIT instruction is present in the IBIT simulation is determined; (b) if there is the IBIT instruction, whether the internal module BIT value set by the monitoring computer is faulty is determined; c) When the internal module BIT value is faulty, the internal module BIT result fault is set and then the external device error BIT result is transmitted. (d) if there is no fault of the internal module BIT value, the IBIT response time Fault set by the monitoring computer is determined and then the BIT result response time Fault is set when the IBIT response time fault is set; (f) And if it is determined that there is no response time fault setting, a normal BIT result of the external device is transmitted to the external device simulator.
delete 6. The method of claim 5, wherein, when transmitting the IBIT command or transmitting the result of the IBIT command, an error is transmitted to the IBIT result value according to the scenario setting, A method for operating an external device simulator system for an embedded computer verification of an aircraft.
The method according to claim 7, wherein, after the transmission of the external device error BIT result in the absence of the IBIT command in (a), the transmission of the external device error BIT result in (c), or the transmission of the BIT result response time fault setting in (d) Wherein the simulator system is configured to simulate an embedded computer simulation of an aircraft.
The method of claim 5, wherein in the external device simulator operating procedure, the external device simulator verifies the aircraft embedded computer by simulating dynamic data varying with time by the monitoring computer. A method for operating an external device simulator system for verifying an embedded computer.
The method according to claim 5, wherein in the external device simulator operating procedure, the external device simulator simultaneously executes an algorithm applied to an actual external device, and performs communication in real time with the aircraft embedded computer, A method for operating an external device simulator system for an embedded computer verification of an aircraft, characterized by verifying an aircraft embedded computer.
An external apparatus simulator system for verifying an embedded computer of an aircraft according to any one of claims 5 and 7 to 10. An external apparatus simulator and an external apparatus simulator system using a monitoring computer As a result,
The external device simulator includes system software and application software together with an operation module, an interface module, and a power supply module, which communicate with the aircraft embedded computer hardware and software for managing an external device without degrading performance Equipped; The monitoring computer sets a scenario for verifying the aircraft embedded computer and transmits the scenario to the external device simulator and executes a scenario in which the external device simulator is set to verify the hardware and software performance of the aircraft embedded computer And an external device simulator system for an embedded computer verification of an aircraft.
12. The method of claim 11, wherein the computing module and the interface module of the external device simulator are of the same specification as the hardware of the external device of the aircraft, and the system software and the application software of the external device simulator An external device simulator system for an embedded computer verification of an aircraft. The system of claim 12, wherein the system software includes a real-time operating system and firmware, the application software including an external device communication simulation model, a discrete signal simulation model, an analog signal simulation model, And an interface module for performing the functions of the external device simulator for the embedded computer verification of the aircraft.
12. The system of claim 11, wherein the monitoring computer comprises GUI software, the GUI software including simulator internal function monitoring, simulator condition monitoring and fault simulation GUI, discrete signal setting and monitoring, Monitoring functions of the external device simulator for the embedded computer verification of the aircraft.

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