KR101418479B1 - Fly-by-wire flight control system having an integrated ofp function using a flight type identity signal and method for controlling the same - Google Patents

Abstract

The present invention relates to an AIS block unit provided in an aircraft manufactured and controlled by a fly-by-wire (FBW) method and generating and outputting an aircraft identification signal according to an identification signal of each aircraft shape; A flight control computer for activating only the OFP corresponding to the aircraft type in the integrated OFP on which the aircraft identification signal is output from the AIS generating unit to execute the OFP function for the aircraft; A flight control system provided with an integrated OFP function using an aircraft type identification signal including a pilot sighting device installed in a cockpit of an aircraft operating a function of an aircraft operating device mounted on the aircraft in accordance with an OFP control signal of the flight control computer; Control method.
The present invention as described above integrates the flight control software for each aircraft type into one module, and loads it in common on the aircraft-mounted computer. Then, the integrated OFP activates only the operation software corresponding to the aircraft type through the corresponding aircraft type identification signal, Function, it is possible to activate only the flight control software applied to the corresponding aircraft type through the corresponding aircraft type identification signal in the integrated flight control software module, thereby significantly reducing the development cost and time of flight control software for each aircraft shape There is an effect that can be made.

Description

FIELD OF THE INVENTION The present invention relates to a flight control system having an integrated OFP function using an aircraft type identification signal,

The present invention relates to a flight control system having an integrated OFP function using an aircraft type identification signal and a control method thereof, and more particularly, to a system and method for controlling a flight control system in which a flight control software for each aircraft type is integrated into a single module, By using the aircraft type identification signal, the OFP function is activated by activating only the operating software corresponding to the corresponding aircraft type in the integrated OFP. By using the aircraft type identification signal, which can significantly reduce the development cost and time of flight control software To a flight control system equipped with an OFP function and a control method thereof.

In general, prior to the advent of modern aircraft, stable flight control and emergency landing were possible with only a very limited form of emergency power system in addition to the main power of the aircraft. In recent years, as a result of increased interest in increasing the maneuverability of an aircraft, a concept of a fly-by-wire flight control system capable of controlling devices such as an actuator and an electric actuator And today's aircraft have adopted it to demonstrate a higher level of flight capability. Here, the Fly-By-Wire (hereinafter referred to as FBW) system refers to a system that converts an aircraft control system into an electric signal device through a computer. In other words, the FBW controls a hydraulic device This is a control method that allows a computer to control using a motor. Recently, it has been applied FBL to control it with optical fiber.

The prior art related to the conventional aircraft FBW system described above is disclosed in Korean Patent Application No. 2010-0061946 filed by Korea Aerospace Research Institute, entitled " Detecting a normal displacement sensor of a steering input device for an electronic flight control system System; date of publication: June 10, 2010).

Referring to FIG. 1, the FBW system of the conventional aircraft as described above includes a steering input device 71 installed at one side of the body of the aircraft 70 and for inputting pilot signals of the pilots;

An operation flight program (hereinafter, referred to as OFP), which is connected to the control input unit 71 through a wire and separately manufactured for each type of aircraft, is mounted in the memory 72. A flight control computer 73 for automatically controlling the airplane 70 according to the OFP;

And an actuator 74A-N composed of various machines and electronic equipment of the aircraft 70 including the aircraft engine in accordance with the flight control signal of the flight control computer 73. [

When the FBW system of the conventional aircraft is manufactured according to the shape, when the T-50, the derivative trainer, the UAV derivative aircraft, or the like is manufactured, the flight control software And OFP are independently developed, implemented, verified and managed, and are installed in the memory 72 of the flight control computer 73, respectively. When the pilot of the aircraft 70 operates the buttons of the pilot input unit 71 for flight of the FBW after mounting the OFP as the flight control software for each aircraft shape via the above process, The flight control computer 73 connected via the device unit 71 and the wire drives the control electric signal provided from the control input device unit 71 by driving the flight control software OFP stored in the memory 72, And transmits the corresponding flight control signal to the corresponding actuator 74A-N of the aircraft 70 to be driven to automatically control the flight of the aircraft 70. [

However, in the conventional OFP system as described above, when the aircraft executing the FBW is manufactured, the flight control software (OFP) is separately manufactured for each type of the aircraft, so that even the same type of aircraft can be used at high cost In this paper, we propose an OFP system which can be applied to the design of OFP systems. In this paper, we propose a new design methodology for OFP system. And verification management must be executed. Therefore, there is a problem in that the engineer greatly increases the inconvenience of the operation.

SUMMARY OF THE INVENTION Accordingly, the present invention has been made keeping in mind the above problems occurring in the prior art, and it is an object of the present invention to provide an aircraft type identification signal in an integrated flight control software module without having to separately develop flight control software for each aircraft type at a high cost. The present invention provides a flight control system having an integrated OFP function using an aircraft type identification signal that activates and executes only flight control software applied to a corresponding aircraft type, and a control method thereof.

It is still another object of the present invention to provide a flight control system and a flight control system, which enables an engineer to easily integrate flight control software through a corresponding aircraft type identification signal without having to repeatedly design and implement flight control software every time an aircraft, And an integrated OFP function using the aircraft type identification signal.

According to an aspect of the present invention, there is provided a method of controlling an aircraft, the method comprising the steps of: receiving a corresponding aircraft identification (Discrete) signal according to an Aircraft_Identity signal for each shape of an aircraft provided in each aircraft manufactured and controlled by a flywheel (FBW) An AIS block unit for generating and outputting a signal;

(OFP) for each type of aircraft controlled by the genital FBW system are integrated into one module and mounted on the module. Then, through the corresponding aircraft identification signal outputted from the AIS generator, A flight control computer for activating only the OFP corresponding to the aircraft type and executing the OFP function for the aircraft;

And an integrated OFP function using an aircraft type identification signal including a pilot sighting device installed in a cockpit of an aircraft operating a function of a machine and electronic equipment mounted on the aircraft in accordance with the OFP control signal of the flight control computer Provides a flight control system.

Another aspect of the present invention is to provide a system and method for controlling a flight by using the FBW method. Whenever an aircraft is manufactured, the flight control software (OFP) A first step of mounting a flight control computer in a module;

Generating a corresponding aircraft identification signal (Discrete) according to an identification signal for each shape of the aircraft, and outputting the generated aircraft identification signal to the flight control computer;

And a third step of, after the second step, activating only the flight control software (OFP) corresponding to the aircraft type in the integrated OFP through the corresponding aircraft identification signal outputted from the AIS generating unit and executing the OFP function for the aircraft and;

After the third process, the flight control computer uses the OFP corresponding to the aircraft type selectively activated in the integrated OFP to synchronize the function of the machine and the electronic equipment including various engines mounted on the aircraft of the corresponding type with the pilot sight unit And an integrated OFP function using an airplane type identification signal including a fourth step of executing the airplane type identification signal.

In the present invention as described above, the flight control software (OFP) for each aircraft type is integrated into one module and loaded in common on the aircraft-mounted computer, and then the operation type software corresponding to the aircraft type in the integrated OFP And the OFP function is activated so that the flight control software for each type of aircraft can be easily and cost effectively applied to the corresponding aircraft type in the integrated flight control software module through the corresponding aircraft type identification signal, It is possible to considerably reduce the cost and time required for the development of the flight control software for each aircraft shape.

The present invention as described above can also be applied to an aircraft of the same type developed once without the need for engineers to perform design implementation or verification management every time when developing an aircraft to which the same technology is applied, Only the integrated flight control software needs to be selectively executed, thereby maximizing the convenience of the engineers concerned.

1 is an explanatory view for explaining an example of a conventional aircraft FBW system;
2 is an explanatory view schematically illustrating an example of a flight control system provided with an integrated OFP function using an aircraft type identification signal;
3 is an explanatory view schematically illustrating internal main configuration modules of a flight control computer provided in the system of the present invention;
4 is a flowchart of the present invention.

Hereinafter, preferred embodiments of a flight control system having an integrated OFP function according to the present invention will be described with reference to the accompanying drawings.

However, the present invention is not limited to the embodiments described herein but may be embodied in other forms. Rather, the embodiments disclosed herein are provided so that the disclosure can be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Like reference numerals designate like elements throughout the specification. It is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. In the present specification, the singular form includes plural forms unless otherwise specified in the specification. The term " comprises " And / or "comprising" does not exclude the presence or addition of one or more other elements, steps, operations, and / or elements.

Example

FIG. 2 is an explanatory view schematically illustrating an example of a flight control system provided with an integrated OFP function using an aircraft type identification signal, FIG. 3 is a schematic view illustrating a flight control computer provided in the system of the present invention, Fig. 4 is a flowchart illustrating the method of the present invention.

Referring to FIG. 2, a flight control system having an integrated OFP function using an aircraft type identification signal according to an embodiment of the present invention includes:

An identification signal generating block unit for each aircraft shape which is provided in each manufactured aircraft 1 and which generates and outputs a corresponding aircraft identification signal (Discrete) according to the Aircraft_Identity signal of each aircraft, 2: hereinafter referred to as an AIS block section);

The flight control unit 1 activates only the flight control or operation software corresponding to the aircraft type in the integrated OFP through the corresponding aircraft identification signal (Discrete) output from the AIS block unit 2 to execute the OFP function for the aircraft 1 A computer 3;

A pilot sighting device unit 4 installed in the cockpit of an aircraft for operating the functions of the aircraft and the electronic equipment mounted on the aircraft in accordance with the OFP control signal of the flight control computer 3, .

Here, the flight control computer 3 incorporates all the flight control software (OFP) for each type of aircraft capable of flight control by the FBW method, integrates them into one module, and mounts them in a memory (not shown).

The flight control computer 3 is a fly-by-wire (FBW) flight control system that includes all aircraft including training-derived aircraft (for training, tactical training and attack) and UAV- (For relaying, attacking) Each time an aircraft is manufactured, it is mounted on the aircraft 1.

3, the AIS block unit 2 implements an airplane identification signal (Aircraft_Identity signal) predefined on the aircraft wiring to identify the aircraft shape when the aircraft 1 is powered on To the flight control computer 3 on which the integrated OFP is mounted through the corresponding aircraft identification signal (Discrete) according to the aircraft-specific shape identification signal (Aircraft_Identity signal) so that the shape of the flight control software is defined according to the model .

3, the flight control computer 3 initializes an internal signal when the power is applied to the flight control computer 3 mounted on the aircraft 1, (PowerUp) that processes the aircraft identification signal (Discrete) to determine the definition of the current aircraft configuration, reconstructs the module according to the aircraft configuration in the integrated OFP based on the defined current aircraft configuration information, ) Module (6);

The airplane information defined by the power up module 6 and the OFP according to the reconfigured module are transmitted to the target / provisioning CSC (Common short code) module 7;

It monitors whether there is a signal defect in the corresponding flight control software (OFP) selected according to the corresponding aircraft identification signal of the AIS block unit 2, and outputs a normal determination signal or a defect determination signal according to the monitoring result A signal management module 8;

A BIT module for checking whether there is an abnormality of the corresponding aircraft discrete signal outputted from the power up module 6 and checking whether the function of the aircraft assigned to each shape is normally operated according to the aircraft identification signal 9);

An error situation corresponding to an operational error due to a defect or shape identification of the aircraft shape identification input signal for the currently executed OFP detected by the signal management module 8 or the BIT module 9 is displayed in the pilot's seat of the aircraft A failure management display module 10 for displaying an alarm on the instrument panel of the device unit 4 for alarming;

Related information such as an aircraft identification signal outputted from the failure management display module 10 or an operation function of each shape and records the source design data A failure information storage management module 11 for storing and managing the failure information;

The flight control signal based on the reconfigured corresponding flight control software (OFP) selected according to the aircraft identification signal (Discrete) output from the target / provisioning CSC module 7 is transmitted to the pilot sight device unit 4 in the aircraft cockpit. And an OFP interworking test module 12 for interfacing with the flight test instrument operated by the pilot so that the pilot can check whether the corresponding flight control software (OFP) is operating normally before the flight.

Here, the signal management module 8 receives an aircraft identification signal of the AIS block unit 2 and receives the signal defect of the flight control software (OFP) through the aircraft identification signal processing circuit in the flight control computer 3 And monitors the defects of the triple signal input system of the flight control computer 3, selects the optimum value of the signal when there is no defect, finally calculates the selected aircraft ID signal, and then outputs the selected aircraft ID signal to the BIT module 9 And if the defect of the aircraft shape identification signal is detected in the defect monitor process, the defect management display module 10 reports information on the defect.

In addition, the BIT module 9 is a built-in test module, which is a flight control inspection test performed before each flight, and determines whether or not the function assigned to each shape according to the aircraft shape identification signal is abnormal When an abnormal shape identification number or function is detected during the inspection, it is determined that there is a defect on the electrical interface of the AIS block unit 2 so that the pilot and the mechanic are aware of the defect, In the form of a defect lamp and a defect identification code.

Further, the failure management display module 10 is a module for processing defects detected by the signal processing module or the BIT module, and is capable of performing a flight control The flaws are handled and isolated to insure system safety and the facts of the flaws are displayed to the pilot and mechanic in the form of a caution lamp and a fault identification code on the pilot sighting unit 4 in the aircraft cockpit, And execute the action.

Here, the failure information storage management module 11 also stores and manages data for supporting a test function provided in the BIT module 9. [

In addition, the target / provisioning CSC module 7 not only operates the functions in the actual flight control computer, but also reconstructs the interfaced signals according to the aircraft shapes, according to the aircraft shape information defined in the module and the reconstructed OFP according to the reconstructed module After that, switching of the interlocking signal for each aircraft shape is performed, and then other modules are also implemented to reflect the provision so that they can be expanded to the same concept.

Next, the control method of the present invention having the above-described configuration will be described.

As shown in FIG. 4, the control method of the present invention system is a flight control by the FBW method in the initial state S1. Whenever an aircraft is manufactured, the flight control is performed by the FBW method in the corresponding aircraft. (S2) of integrating all OFPs and incorporating the flight control computer into a single module;

A second step (S3) of generating a corresponding aircraft identification signal (Discrete) according to an identification signal of each aircraft shape after the first step (S2) and outputting the generated aircraft identification signal to a flight control computer;

After the second step S3, the flight control computer activates only the flight control software (OFP) corresponding to the aircraft type in the integrated OFP through the corresponding aircraft identification signal outputted from the AIS block unit to execute the OFP function for the aircraft A third step S4;

After the third step S4, the flight control computer uses the OFP corresponding to the aircraft type selectively activated by the integrated OFP to perform functions of the machine and electronic equipment including various engines mounted on the aircraft of the corresponding type, And a fourth step (S5) of executing the program in cooperation with the program.

In the third step S4, the flight control computer processes the corresponding aircraft identification signal in the AIS block through the power-up module to determine a definition of the current aircraft shape, and determines, based on the defined current aircraft shape information, And a fourth step of reconstructing the module according to the shape of the aircraft in the initial operation of the predetermined function.

In the third step S4, the air control information defining the flight control computer and the OFP according to the reconfigured module operate the function of the flight control computer with the flight control information corresponding to the airplane shape, , 4-3 designing an interlocking signal for each aircraft shape after the step 4-2, switching interlocking signals for each of the designed aircraft shapes, and then provisioning the same module so that the same module can be expanded. .

Further, in the third step S4, it is determined whether there is a signal defect for the corresponding OFP selected according to the aircraft identification signal, and if the function of the aircraft assigned to each shape is normally operated according to the aircraft identification signal And outputting the checking result to the outside.

In addition, in the third step (S4), an error condition corresponding to an operation error due to a defect of the aircraft shape identification input signal or the shape identification of the OFP currently being executed by the flight control computer is displayed on the pilot sight detector unit in the cockpit of the aircraft And displaying the alarm on the instrument panel for alarming.

In other words, in order to execute the flight control system according to an embodiment of the present invention, first, the flight control is performed by the FBW (fly-by-wire) (For training, tactical training, attack) and UAV-derived (reconnaissance, relay, attack) aircrafts are manufactured on the aircraft, including the flight control computer 3 of the present invention, Respectively.

That is, every time the aircraft 1 is manufactured, the flight control software (OFP) for each model of the aircraft is integrated in the corresponding aircraft 1 by the FBW method, The flight control computer 3 of FIG. At this time, an AIS block unit 2 for generating and outputting an Aircraft_Identity signal according to the shape of the aircraft is installed on the pilot sight device unit 4 installed in the cockpit of the aircraft 1.

The AIS block unit 2 includes an AIS block unit 2 that determines whether the current aircraft 1 is an F-16, a T-50, a training derivative aircraft, or a UAV derivative type (Aircraft_Identity signal) according to the shape of the aircraft that determines whether or not the aircraft is an aircraft, and inputs the generated signal to the flight control computer 3.

Then, the flight control computer 3 activates only the operating software (OFP) corresponding to the aircraft type in the integrated OFP through the corresponding aircraft identification signal (Discrete) outputted from the AIS block unit 2, To perform the OFP function,

For example, if the aircraft 1 is assumed to be a T-50, the integrated OFP of the flight control computer 3 may include the T-50, including the F-16, and the training derived aircraft and the UAV derivative aircraft, OFP, the flight control computer 3 deactivates the OFPs for the remaining aircraft because the AIS block unit 2 has input the identification signal of the aircraft shape recognizing the " T-50 " Only the OFP corresponding to "-50" is activated.

The process of the embodiment of the present invention as described above will be described in more detail as follows.

That is, when the Aircraft_Identity signal for each shape of the aircraft is inputted from the AIS block unit 2 to the power-up module 6 and the signal management module 8 of the flight control computer 3 of the present invention, First, the power-up module 6 initializes an internal signal when the power is applied to the flight control computer 3 mounted on the aircraft 1, and outputs the corresponding aircraft identification signal (Discrete) of the input AIS block 2 And determines the definition of the current aircraft shape and reconstructs the module according to the shape of the aircraft in the integrated OFP based on the currently defined aircraft shape information so that the predetermined function is operated.

When the power-up module 6 of the flight control computer 3 is initially operated as described above, the target / provisioning CSC module 7 receives the air-shape information defined by the power-up module 6 and the reconfigured module The OFP according to the present invention operates the function of the flight control computer 3 with the flight control information corresponding to the shape of the aircraft. At this time, the target / provisioning CSC module 7 causes the reconfigured OFP to operate the functions in the actual flight control computer 3 according to the aircraft shape information defined in the power up module 6 and the reconfigured module. In addition, the target / provisioning CSC module 7 designates an interlocking signal for each aircraft shape in this process, performs switching of the interlocking signal for each of the aircraft shapes, and then extends other modules to the same concept It also carries out the function to reflect the provision.

Meanwhile, the signal management module 8, which receives the corresponding aircraft identification signal from the AIS block unit 2 at the same time as the above operation, also monitors whether there is a signal defect in the selected corresponding flight control software (OFP) . At this time, the signal management module 8 outputs a normal determination signal or a defect determination signal according to the monitoring result.

For example, the signal management module 8 receives an aircraft identification signal of the AIS block unit 2 and receives a signal defect of the flight control software (OFP) through the aircraft identification signal processing circuit in the flight control computer 3 In this case, if there is no defect after monitoring the defect of the triple signal input system of the flight control computer 3 at this time, the optimum value of the signal is selected to finally calculate the selected aircraft ID signal, and then the BIT module 9).

On the other hand, if a defect is detected in the aircraft shape identification signal during the defect monitor process, the signal management module 8 reports the defect information to the failure management display module 10.

In this process, the BIT module 9 receives the last selected aircraft ID signal from the signal management module 8 to check whether there is an abnormality in the corresponding aircraft identification signal outputted from the power up module 6, Check whether the function of the aircraft assigned to each shape according to the aircraft identification signal (Discrete) is operating normally.

That is, the BIT module 9 is a built-in test module, which is a flight control inspection test performed before each flight, and checks whether or not the function assigned to each shape operates normally according to the aircraft shape identification signal and the aircraft shape identification signal do. When an abnormal shape identification number or function is detected during the inspection, the BIT module 9 determines that there is a defect on the electrical interface of the AIS block unit 2 so that it is recognized by the pilot and the mechanic (4) on the instrument panel in the form of a defect lamp and a defect identification code.

Here, during the OFP execution process, if an error corresponding to an operation error due to a defect or shape identification is inputted to the aircraft shape identification input signal for the currently executed OFP detected by the signal management module 8 or the BIT module 9 When a situation occurs, the failure management display module 10 displays the alarm on the instrument panel of the pilot sight device unit 4 in the cockpit of the aircraft to alert the user.

That is, the failure management display module 10 is a module that processes defects detected by the signal management module 8 or the BIT module 9, and detects a defect of the aircraft shape identification input signal or an operation function Handle and isolate faults to ensure flight control system safety against faults. Then, the failure management display module 10 displays the fact of the defect to the pilot and the mechanic in the form of a caution lamp and a defect identification code on the pilot sighting device unit 4 in the aircraft cockpit, .

Meanwhile, during the defect monitoring for the selected OFP execution, the failure information storage management module 11 receives defect information related to an error such as an aircraft identification signal or an operation function for each shape from the failure management display module 10 And records the source design data in the DB so that failure analysis and fault investigation can be performed through such defect related information. In addition, the failure information storage management module 11 also stores and manages data for supporting a test function included in the BIT module 9.

In addition, during the above process, the flight control software (OFP) selected and reconfigured according to the corresponding aircraft identification signal (Discrete) output from the target / provisioning CSC module 7 of the OFP interworking test module 12, Signal is displayed on the pilot display unit 4 in the aircraft cockpit so that the pilot can interoperate with the flight test instrument of the pilot operation so that the flight control software (OFP) can be normally operated before the flight.

Therefore, according to one embodiment of the present invention as described above, the flight control software (OFP) for each aircraft model is integrated into one module and is commonly installed in the aircraft-mounted computer, By activating the OFP function by activating only the operating software corresponding to the aircraft type, the flight control software is not easily developed separately at the expense of the airplane type, Since only the flight control software applied to the aircraft type is activated and executed, it is possible to considerably reduce the cost and time for developing the flight control software for each aircraft shape.

1: Aircraft 2: AIS block section
3: Flight control computer 4: Pilot vision unit
5: Aircraft operation equipment 6: Power-up module
7: Target / Provisional CSC module 8: Signal management module
9: BIT module 10: Fault management display module
11: Fault information storage management module 12: OFP interworking test module

Claims (16)

An AIS block for generating and outputting a corresponding aircraft identification signal according to an airplane identification signal (Aircraft_Identity signal), which is provided in each airplane and is controlled by a flywheel (FBW) method;
A flight control computer for activating only the OFP corresponding to the aircraft type in the integrated OFP on which the aircraft identification signal is output from the AIS block unit and executing the OFP function for the aircraft;
A pilot sighting unit provided in the cockpit of the aircraft for operating the functions of the aircraft operating equipment mounted on the aircraft in accordance with the OFP control signal of the flight control computer;
The flight control computer processes the corresponding aircraft identification signal in the AIS block to determine a definition of the current aircraft shape and reconstructs the module in accordance with the aircraft shape in the integrated OFP based on the defined current aircraft shape information, A power-up module for operating,
A target / provision VCSC module for operating the function of the flight control computer with flight configuration information defined by the power up module and OFP according to the reconstructed module with flight control information corresponding to the aircraft configuration;
A signal management module for monitoring whether there is a signal defect for the corresponding OFP selected according to the aircraft identification signal of the AIS block and outputting a normal decision signal or a defect determination signal according to the monitoring result;
A BIT module for checking whether there is an abnormality in the corresponding aircraft identification signal output from the power up module and checking whether the function of the aircraft assigned to each shape is normally operated according to the aircraft identification signal;
A failure management display for displaying on the instrument panel of the pilot sighting device an error condition corresponding to an operation error due to a defect or shape identification of the aircraft shape identification input signal for the currently executed OFP detected by the signal management module or the BIT module Flight control system having an integrated OFP function using an aircraft type identification signal further comprising a module. The method according to claim 1,
Wherein the flight control computer is incorporated by incorporating all the flight control software (OFP) of each type of aircraft capable of flight control by the FBW system into one module and incorporating the integrated OFP function using the aircraft type identification signal Flight control system. delete The method according to claim 1,
The target / provisioning CSC module includes a provision for designing an interlocking signal for each aircraft shape, switching the interlocking signal for each designed aircraft shape, and then expanding the same module. A flight control system equipped with an integrated OFP function using an aircraft type identification signal. The method according to claim 1,
The signal management module monitors the defects of the triple signal input system of the flight control computer. If there is no defect, the signal management module selects the optimum value of the signal, calculates the final selected aircraft ID signal, and outputs the final selected aircraft ID signal to the BIT module. The fault management display module provides information on the corresponding fault to the fault management display module. The method according to claim 1,
Wherein the BIT module is a built-in test module, which is a flight control inspection test performed before every flight, and the flight control system includes an integrated OFP function using the aircraft type identification signal. The method according to claim 1,
The BIT module displays an abnormal shape identification number or function when the abnormal shape identification number or function is detected in the form of a defect lamp and a defect identification code on the instrument panel of the pilot sighting device unit so that it is recognized that there is a defect on the electrical interface of the AIS block unit Flight control system with integrated OFP function using aircraft type identification signal. The method according to claim 1,
Wherein the failure management display module displays an error of the operational function according to a defect of the reported aircraft shape identification input signal or the shape identification in the form of a caution lamp and a defect identification code on the pilot sighting device. Flight control system equipped with integrated OFP function using signal. The method according to claim 1,
The flight control computer records and manages the information related to the defect such as the aircraft identification signal outputted from the error management display module or the operation function according to the shape, and analyzes the source of the fault through the defect related information, And a failure information storage management module for storing and managing the data. The flight control system with integrated OFP function using the aircraft type identification signal. 10. The method of claim 9,
Wherein the fault information storage management module stores and manages data for supporting a test function provided in the BIT module. The method according to claim 1,
The flight control computer displays a flight control signal based on the reconfigured selected OFP according to the aircraft identification signal output from the target / provisioning CSC module on the pilot sighting unit in the aircraft cockpit, And an OFP interworking test module operable to interwork with the OFP interrogation module. FBW-based flight control Each time an aircraft is manufactured, it is controlled by the FBW method in the corresponding aircraft. A flight control computer incorporating all of the flight control software (OFP) of each aircraft type is installed in one module. 1;
A second step of generating an aircraft identification signal (Discrete) according to an identification signal of each aircraft shape after the first process and outputting the generated aircraft identification signal to a flight control computer;
A third step of, after the second step, activating only the flight control software (OFP) corresponding to the aircraft type in the integrated OFP through the corresponding aircraft identification signal output from the AIS block unit and executing the OFP function for the aircraft and;
And a fourth step of causing the flight control computer to execute the function of the corresponding type aircraft in cooperation with the pilot sightseeing device unit using the OFP corresponding to the aircraft type selectively activated in the integrated OFP after the third step, A method of controlling a flight control system equipped with an integrated OFP function. 13. The method of claim 12,
The third step is to determine the definition of the current aircraft shape by processing the corresponding aircraft identification signal inputted by the flight control computer and reconstruct the module according to the shape of the aircraft in the integrated OFP based on the defined current aircraft shape information, The method of claim 1, further comprising the step of: (4-1) initializing the function of the flight control system having the integrated OFP function using the aircraft type identification signal. 13. The method of claim 12,
The fourth step includes a step 4-2 of operating the function of the flight control computer with the flight control information defining the flight control computer and the OFP according to the reconstructed module as the flight control information corresponding to the aircraft shape,
The method further includes a step 4-3 of designing an interlocking signal for each aircraft shape after the step 4-2, switching interlocking signals for each of the designed aircraft shapes, and then including a countermeasure for expanding the same module Wherein the aircraft type identification signal is used to control a flight control system having an integrated OFP function. 13. The method of claim 12,
In the third step, the flight control computer checks whether there is a signal defect for the corresponding OFP selected according to the aircraft identification signal, whether the function of the aircraft assigned to each shape is normally operated according to the aircraft identification signal, And outputting the result to the outside. The method of controlling a flight control system having an integrated OFP function using an aircraft type identification signal. 13. The method of claim 12,
The third step is a step 4-5 of displaying on the instrument panel of the pilot sight unit an error condition corresponding to a fault in the aircraft shape identification input signal for the OFP currently being executed by the flight control computer, Further comprising the steps of: receiving the aircraft type identification signal;

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