KR100969231B1 - Signal Interface System for Launch Vehicle HILS - Google Patents

Abstract

According to the present invention, a projectile HILS test signal interface system for evaluating a flight simulation of a projectile, comprising: an inertial navigation module for calculating a navigation and attitude control algorithm such that the projectile is guided to a preset reference coordinate; An induction control drive module that receives information calculated from an inertial navigation module or an RTS module and controls a flight path of the projectile by controlling posture control, gas thrust, and aerodynamic pin of the projectile; A DSC module for selecting a valid drive command A among the diskette drive command signals received from the inertial navigation induction module and transferring the selected drive command A to the induction control drive module; An ASC module which selects an effective drive command B among analog drive command signals inputted from an inertial navigation module and transfers it to an induction control drive module; A TBB module which is an inertial navigation module, an induction control module and an external connection device, and an interface connection module for connecting the DSC module and the ASC module to each other; Electrically connected between the inertial navigation induction module and the induction control drive module, it provides data on the flight environment and disturbance conditions for flight simulation, and the command of the inertial navigation induction module and the feedback of the induction control drive module. A signal interface system for a projectile HILS test is disclosed that includes an RTS module for measuring a value.

Projectile, interface, system

Description

Signal Interface System for Launch Vehicle HILS

The present invention relates to a signal interface system for a HILS test, and more particularly, to a signal interface system for a projectile real-time simulation that optimizes a universal interface of electrical signals between subsystems during a hardware in the loop simulation (HILS). It is about.

In the real-time simulation of conventional projectiles, a real-time computer, an inertial navigation guidance unit (INGU), a gas thrust control system (RCS), a thrust vector control system (TVCS) and aerodynamic Each subsystem, such as the AFCS (Aerodynamic Fin Control System), was tested by directly connecting a pre-made wire harness.

However, in order to describe various flight environments that can occur between actual flight of the projectile, it is essential to apply the flight environment and disturbance conditions of the projectile by changing the HILS test scenario, and to change the HILS test scenario, Since the harness connection condition of each subsystem had to be changed in real time, the economical and time wasted when the harness was replaced.

In addition, the signals output from the real-time computer and the inertial navigation apparatus are processed in the process of processing a discrete signal and an analog signal. The operating reference voltage levels were different and a separate compensation circuit had to be fitted to counteract this.

In the case of the analog signal, a noise signal is generated due to the addition of additional circuits for simulation tests other than the on-board circuit mounted on the actual projectile, such as a harness for connecting each subsystem including the real-time computer. There was a potential problem that could occur and the drive system malfunctions.

The present invention was created to solve the above problems,

The diskette signal converting unit (DSC) for processing the diskette signal is output to the diskette so that the inputted diskette signal is output in a state where it is selectively converted to an operation reference voltage level by an internal jumper circuit according to a subsystem in which the input diskette signal is transmitted. The output signal converting unit is provided, and the analog signal converting unit (ASC) for processing the analog signal is provided with a noise removing filter for filtering the input analog signal based on a preset frequency band, thereby projectiles that can respond to various signal characteristics The aim is to provide a universal signal input / output interface system for HILS testing.

The projectile HILS test signal interface system according to the present invention for achieving the above object, in the projectile HILS test signal interface system for evaluating the flight simulation of the projectile, so that the projectile is guided to a predetermined reference coordinate, navigation and An inertial navigation induction module for calculating a posture control algorithm; An induction control drive module that receives information calculated from the inertial navigation module or an RTS module, and controls flight paths of the projectile by controlling posture control, gas thrust, and aerodynamic pins of the projectile; A DSC module which selects an effective driving command A among the diskette driving command signals inputted from the inertial navigation module and transfers it to the induction control driving module; An ASC module that selects an effective drive command B from the analog drive command signals received from the inertial navigation module and transfers it to the induction control drive module; A TBB module which is an interface connection module for connecting the inertial navigation module, the inductive control drive module, the external connection device, and the DSC module and the ASC module to each other; It is electrically connected between the inertial navigation module and the induction control drive module to provide data on the flight environment and disturbance conditions for the flight simulation test, and drive command value and induction control drive module of the inertial navigation module. RTS module for measuring the feedback command value of the.

Here, the RTS module may measure the control efficiency of the system by comparing the measured driving command value of the inertial navigation module and the feedback command value of the induction control driving module with each other.

In addition, the TBB module is electrically connected between the inertial navigation induction module and the induction control drive module, and the drive command value transmitted from the inertial navigation induction module and the feedback command value transmitted from the induction control drive module. In comparison with each other, it may further include an external measurement module for measuring the control efficiency of the system.

In addition, of the diskette driving commands generated from the inertial navigation module and the RTS module, the valid driving command A is selected through the diskette signal selection unit provided in the DSC module, and the selected valid driving command A is selected from the DSC module. It is preferable to drive the induction control drive module via a diskette output signal conversion unit provided in the controller, or to be transferred to the external measurement module for processing.

In addition, the effective drive command B of the analog drive commands generated from the inertial navigation module and the RTS module is selected through an analog signal selector provided in the ASC module, and the selected valid drive command B is provided to the ASC module. It is preferable to drive the induction control drive module via the analog output signal conversion unit or be transferred to the external measurement module for processing.

In addition, the induction control drive module is driven by the selected effective drive command B and generates a TVC nozzle angle and RCS nozzle thrust measurement pressure, and the generated TVC nozzle angle and RCS nozzle thrust measurement pressure are provided in the TBB module. It is preferable that the input signal is input to the noise removing filter provided in the ASC module via the analog input unit and filtered according to a signal characteristic of a preset channel.

On the other hand, the noise removal filter unit, but filtering according to the predetermined signal characteristics of the channel, it is preferable to filter by dividing the transmitted analog signal into one frequency band selected by the internal circuit jumper of 50HZ, 100Hz and 200Hz.

The apparatus may further include a timer control module configured to drive a timer display by receiving a synchronization signal from the RTS module.

In addition, the timer control module includes a mode change switch for setting whether to operate the operation mode of the timer display unit indicating the operation start time of the system in the manual mode or the auto mode, and in the manual mode. It may include a start time setting switch for setting the operating time of the system, and a start time start / stop switch for setting whether to start or stop the start time when the start time is set through the start time setting switch.

In addition, when the mode switching switch is switched to the automatic mode, the timer synchronizing signal generated from the RTS module and the mode switching switch may be synchronized to drive the timer display unit.

In addition, the TBB module may have a form of a terminal block aggregate.

According to the signal interface system for a projectile HILS test according to the present invention,

First, there is no need to change the connection conditions of the harnesses connected to each other in order to describe the various flight environments of the projectile HILS test, which has the advantage of increasing economic and time utility value.

Second, since the operating reference voltage level of the diskette signal transmitted to each subsystem through the diskette signal conversion module (DSC) is automatically converted, it is necessary to install a compensation circuit for compensation of an additional additional operating reference voltage level. It is unnecessary.

Third, each module constituting the projectile HILS signal interface system is standardized and provided to be mounted in a rack cabinet, and the connection to the external connection device is connected through a terminal block assembly (TBB) so that no harness wiring work is required. The noise added to the analog signal is minimized, and the analog signal conversion module (ASC) is equipped with a noise removing filter for dividing and filtering frequency bands to meet various analog signal input conditions, thereby preventing the driving system from malfunctioning. There are advantages to it.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. Prior to this, terms or words used in the present specification and claims should not be construed as being limited to the common or dictionary meanings, and the inventors should properly explain the concept of terms in order to best explain their own invention. Based on the principle that it can be defined, it should be interpreted as meaning and concept corresponding to the technical idea of the present invention.

Therefore, the embodiments described in the specification and the drawings shown in the drawings are only the most preferred embodiment of the present invention and do not represent all of the technical idea of the present invention, various modifications that can be replaced at the time of the present application It should be understood that there may be equivalents and variations.

1 is a block diagram of a discrete signal input and output control block of the projectile HILS test signal interface system according to an embodiment of the present invention, Figure 2 is a block diagram of an analog signal input and output control block of the projectile HILS test interface system of Figure 1, 3 is a block diagram illustrating a timer control module included in the projectile HILS test signal interface system of FIG. 1, and FIG. 4 is a schematic diagram illustrating a rack cabinet equipped with the projectile HILS test signal interface system of FIG. 1.

First, the projectile HILS test signal interface system of the present invention provides a projectile real-time simulation signal interface system for an electrical signal interface between sub-systems during a real time simulation (HILS) of the projectile.

As shown in Figures 1 to 3, the projectile HILS test signal interface system according to the present invention is the inertial navigation module 200, induction control drive module 220, DSC module 110, ASC module 120 , A TBB module 140, an RTS module 150, an external measurement module 210, and a timer control module 130 are provided.

Hereinafter, the configuration of a signal interface system for a projectile HILS test according to the present invention will be described with reference to FIGS. 1 to 3.

The Inertial Navigation Guidance Unit module (INGU) 200 is configured to calculate a navigation and attitude control algorithm of the projectile so that the projectile can be guided to a preset reference coordinate. The calculated information is transmitted to the induction control drive module 220.

Here, the calculated information transmitted through the inertial navigation module 200 is divided into discrete signals and analog signals, and the inertial navigation module 200 and the induction control drive. Signal input and output of the module 220 is interfaced with a diskette / analog signal of several tens to hundreds of channels.

The induction control drive module 220 receives information calculated from the inertial navigation module 200 or the RTS module 150, and controls the attitude control, the gas thrust and the aerodynamic pin of the projectile to fly the projectile. It is in charge of the course control.

The actuator module 220 includes a thrust vector control system (TVCS), a gas thrust control system (RCS) and an aerodynamic pin control system (AFCS) for performing actual attitude control. Driver systems such as Aerodynamic Fin Control System) may be included.

First, the attitude control of the projectile using the thrust vector control system is performed by the attitude control algorithm software mounted for stabilization of the vehicle. The engine nozzle angle is changed by movement to control the pitch / yaw attitude of the projectile.

In addition, the attitude control of the projectile using the gas thrust control system is a posture control method applied to the roll attitude control in the non-thrust flight section three-axis attitude control or thrust flight section, the internal storage tank provided in the projectile It is a method of controlling posture by reacting the injected gas by filling the high pressure nitrogen or hydrazine gas and opening and closing the valve attached to the thruster nozzle by the On-Off driving command signal.

On the other hand, the attitude control of the projectile using the aerodynamic pin control system is a method of performing the attitude control by changing the displacement angle of the aerodynamic pin attached to the lower end of the projectile in the section where the atmosphere after the projectile takes off.

The inertial navigation module 200 measures the posture motion of the projectile generated during the real-time simulation test, calculates the nozzle driving angle in the form of an analog signal, and transmits it to the thrust vector control system, and the on-off required for driving the gas thruster. The characteristic is calculated and transmitted to the gas thrust control system in the form of a discrete signal.

On the other hand, the attitude control algorithm software mounted in the inertial navigation module 200 allows the same attitude control algorithm software to be installed inside the RTS module (Real Time System) 150 to determine suitability for flight use.

As described above, the attitude control algorithm software mounted on the inertial navigation module 200 and the RTS module 150 is performed at the same time as the simulation is performed in real time, and the calculation is performed in the induction control driving module 220. The drive command signal for each driver system is generated independently.

The DSC module (Discrete Signal Converer module) 110 selects the effective drive command signal A from the diskette drive command signal received from the inertial navigation module 200 or the RTS module 150 to induce the control module 220 The ASC module 120 selects a valid drive command signal B among analog drive command signals received from the inertial navigation module 200 or the RTS module 150 to control the induction. Transfer to the drive module 220.

The effective driving command signals A and B are driving commands of the inertial navigation induction module 200 by a switch operation or automatic recognition selection located on the front panel (not shown) of the DSC module 110 and the ASC module 120. The driving command signal selected from the signal or the driving command signal of the RTS module 150 is referred to.

The induction control drive module 220 is driven by the effective drive command signal A and the effective drive command signal B to generate a TVC nozzle angle and an RCS nozzle thrust measurement pressure. The TVC nozzle angle and the RCS nozzle thrust measurement pressure are generated. Is converted into a diskette signal and an analog signal, and the diskette signal is transmitted to the RTS module 150 through the diskette input signal converting unit 111 and the diskette input signal converting unit 114 of the DSC module 110. The analog signal is input to the RTS module 150 via the noise removing filter 121 of the ASC module 120.

On the other hand, the TBB module (Terminal Block Box; 140), the inertial navigation module 200, the induction control drive module 220 and the external connection device, the DSC module 110 and ASC module 120 mutually As an interface connection module for signal connection, the module may have a form of a terminal block assembly.

In this case, the external connection device, means a sub-system or a sub-device externally connected to the projectile HILS test signal interface system of the present invention, and the signal connection with the projectile HILS test signal interface system through the TBB module 140 do.

The RTS module 150 is electrically connected between the inertial navigation module 200 and the inductive control drive module 220, so that the flight environment and disturbance condition for the flight simulation test HILS. Provide data for

Here, the RTS module 150 is equipped with the same attitude control algorithm as the inertial navigation module 200 to output a drive command signal to the induction control driving module 220 independently of the inertial navigation module 200. Meanwhile, the driving command value of the inertial navigation module 200 and the feedback command value of the induction control driving module 220 are measured in real time.

Herein, the driving command value means a valid driving command signal A and a valid driving command signal B selected from the information calculated from the inertial navigation module 200.

In addition, the feedback command value means information in which the result of performing the operation of driving the induction control drive module 220 by the effective driving command signal A and the valid driving command signal B is converted into a discrete signal and an analog signal. .

In addition, the RTS module 150 manages a real-time simulation test, selects a flight sequence and a flight scenario, and performs a real-time simulation test. The TVC nozzle angle and the RCS module gas returned from the induction control drive module 220 are performed. The feedback command value such as the measured pressure is input to the projectile 6 degree of freedom simulation program mounted in the RTS module 150.

By inputting the feedback command value, the motion table equipped with the inertial navigation guide module 200 is moved based on the posture motion data and the flight condition data calculated from the projectile 6 degree of freedom simulation program, and the inertial navigation guide module 200. The driving command signal generated from the attitude control algorithm software mounted on the controller is measured, and the validity verification of the inertial navigation module 200 software is performed through real-time comparison with the internal attitude control algorithm software of the RTS module 150.

For example, in the case of the thrust vector control system, the nozzle drive command angle generated from the RTS module 150 or the inertial navigation module 200 and the measured nozzle angle or the feedback induction control drive of the measured induction control drive module 220. By comparing the values of the feedback nozzle angles of the module 220, it may be determined whether a time delay or an absolute magnitude difference of a signal occurs.

That is, the validity verification can be confirmed by comparing feedback signal measurement values for whether the induction control driving module 220 has been operated in response to the driving command signal of the RTS module 150 and the inertial navigation module 200.

In addition, the RTS module 150 executes a projectile six degree of freedom simulation program to describe flight trajectories, attitude movements and flight environment of the projectile during the flight simulation test, and executes script commands for data storage and processing. Real Time System (RTS) is used for this purpose.

The computer used in the RTS is equipped with a real-time OS (Operation Software), it is desirable to have a specification that ensures strict real-time performance by performing the relevant operation based on the clock source of the precision timer, in one embodiment CE -5500, CE-2604 single board computer dual-mounted, IRIG Timer coverage for precision clock sources, SCRAMNET, AD, D / A and DIO boards for external signal interfaces, IEEE GPIB 488 communication board Can be configured.

On the other hand, as an apparatus for measuring the system efficiency of the projectile HILS test signal interface system of the present invention, in addition to the above-described RTS module 150, the outside of the projectile HILS test signal interface system through the connection with the TBB module 140 The measurement module 210 may measure the efficiency of the system.

The external measurement module 210 is mounted to the TBB module 140 as one of the external connection devices, and is electrically connected between the inertial navigation module 200 and the induction control drive module 220. By comparing the drive command value transmitted from the inertial navigation module 200 with the feedback command value transmitted from the induction control drive module 220, the system control efficiency of the projectile HILS test interface system can be measured. have.

In addition, the projectile HILS test signal interface system of the present invention includes a timer control module 130 for checking the launch sequence and the test progress time during the projectile real-time simulation (HILS).

As shown in FIG. 3, the timer control module 130 may operate the operation mode of the timer display unit 132 indicating the operation start time of the system in manual mode or auto mode. A start time setting switch 133 for setting a start time, a start time setting switch 134 for setting an operating time of the system in the manual mode, and a start time setting for starting time setting when the start time setting switch 134 is set; Or a start time start / stop switch 136 for setting whether to stop or not.

The timer control module 130 resets the start time previously set through the start time setting switch 134 when the mode changeover switch 133 is manually switched, and then starts time. After adjusting to a new start time through the adjustment switch 135, the adjusted time is set to the set start time through the start time setting switch 134, and then through the start time start / stop switch 136. The timer can be controlled by starting or stopping the start time.

Meanwhile, when the mode switch 133 is switched to the automatic mode, the time synchronization signal generated from the RTS module 150 and the mode switch 133 are synchronized so that the timer display unit 132 performs driving. .

Next, the operation principle of the signal interface system for the projectile HILS test of the present invention will be described with reference to FIGS.

First, the diskette signal input and output flow in the DSC module 110, as shown in Figure 1, DSC module 110 and the RTS module 150 and TBB module 140 for real-time simulation (HILS) and The TBB module 140 is connected to the inertial navigation module 200, the induction control drive module 220, and the external measurement module 210, so that the RTS module 150 is inertial navigation induction. The module 200, the induction control drive module 220 and the external measurement module 210 is provided to be connected to the signal.

The diskette driving command signal generated from the RTS module 150 and the inertial navigation module 200 is selected through the diskette signal selecting unit 113 included in the DSC module 110, and the selected valid driving command signal is selected. A is transmitted to the external measurement module 210 via the diskette output signal conversion unit 112 or to an induction control drive module 220 such as a thrust vector control system, a gas thrust control system, and an aerodynamic pin control system. The induction control drive module 220 is driven.

At this time, the diskette output signal conversion unit 112, the effective drive command signal according to the characteristics of the signal acceptable to the external measurement module 210 and the induction control drive module 220 to which the effective drive command signal A is to be transmitted. The signal characteristics of A are bisected and converted.

That is, the diskette output signal converting unit 112 includes a converter having various signal values according to characteristics of a signal to which the driving command signal A can be converted, such as OV / 24V, Open / Short, and 0V / 5V. Converter may be provided, and the diskette output signal converter 112 converts the transmitted effective drive command signal A according to a signal characteristic selectable by an internal jumper.

For example, when the external measurement module 210 requires a signal characteristic of 0V / 24V, and the induction control drive module 220 requires a signal characteristic of 0V / 5V, the diskette output The driving command signal A transmitted to the signal conversion unit 112 is divided into a signal having a signal characteristic of 0V / 24V and a signal having a signal characteristic of 0V / 5V, and the driving command signal A of 0V / 24V is The driving command signal A of 0V / 5V is transmitted to the external measurement module 210 and is transmitted to the induction control driving module 220.

On the other hand, the diskette signal generated from the inertial navigation module 200 and input to the DSC module 110 through the TBB module 140, the diskette input signal conversion unit provided in the DSC module 110 ( 111 and the diskette input signal converting unit 114 for recognizing the RTS are converted to the signal characteristics that can be processed by the RTS module 150 and then transferred to the RTS module 150.

That is, the diskette input signal converter 111 may include a converter having various signal values according to characteristics of a signal to which the diskette signal can be converted, such as Open / Short and 0V / 5V. The diskette input signal converter 112 may convert the input diskette signal according to a signal characteristic selectable by an internal jumper.

Next, referring to the analog signal input / output flow in the ASC module 120, as in the DSC module 110 described above, as shown in FIG. 2, the ASC module 120 includes an RTS module 150 for real-time simulation (HILS) and Interface with the TBB module 140, the TBB module 140 is connected to the inertial navigation module 200, the induction control drive module 220 and the external measurement module 210, the RTS module ( 150 is provided to signal connection with the inertial navigation module 200, the induction control drive module 220 and the external measurement module 210.

The analog drive command signal generated from the RTS module 150 and the inertial navigation module 200 is selected through the analog signal selector 122 included in the ASC module 120 and the TBB module 140 of the TBB module 140. The induction control drive module 220 is driven through the analog output unit and simultaneously transferred to the external measurement module 210.

On the other hand, the induction control drive module 220 is driven by the effective drive command signal B which is the selected analog signal and generates a TVC nozzle angle and RCS nozzle thrust measurement pressure, the generated TVC and RCS nozzle thrust measurement pressure is A frequency bandwidth that can be processed by the RTS module 150, which is a signal characteristic of a preset channel, is input to the noise removing filter unit 121 provided in the ASC module 120 via an analog input unit provided in the TBB module 140. Filtered according to the range is delivered to the RTS module 150.

That is, the noise removing filter unit 121 filters according to a signal characteristic of a preset channel, and filters the transmitted driving command signal B into one frequency band selected by an internal circuit jumper among 50 Hz, 100 Hz, and 200 Hz. It is provided to.

In this case, the filtered analog signal selector 123 may be further provided at a route through which the analog signal filtered by the noise removing filter 121 is transmitted to the RTS module 150.

Accordingly, the effective driving command signal B passing through the noise removing filter 121 is selectively filtered through the filtered analog signal selector 123 and transmitted to the input unit of the RTS module 150.

Here, the part of the analog signal channel inputted to the RTS module 150 through the analog signal selector 123 is. Inputted to the projectile six degree of freedom simulation program posture motion generation algorithm mounted inside the RTS module 150, in real flight environment by the induction control drive module 220 and the connection harness according to the real-time simulation conditions and signal characteristics There is a possibility that noise components of various components that do not occur occur.

When this noise component is amplified, there is a possibility that a test under a different condition from the actual firing environment may be performed during the real-time simulation test. It is desirable to be provided so that.

Meanwhile, the measured analog signal channel which is not used as an input of the projectile six degree of freedom simulation program may be provided to select whether or not the filter passes through a jumper for each analog channel so as not to undergo filtering to prevent distortion of the signal.

The projectile HILS test interface system of the present invention may be mounted in a standardized rack cabinet as shown in FIG. 4.

Referring to FIG. 4, the rack cabinet includes a plurality of consoles on which the DSC module 110, the ASC module 120, the timer control module 130, the TBB module 140, and the RTS module 150 are mounted. ) Is provided.

In addition, each module (110, 120, 130, 140 and 150) is embedded in the respective console, mounted, each module is provided so that each module is connected to each other in the harness inside the rack cabinet with each module mounted It is desirable to be.

Therefore, the projectile HILS test signal interface system of the present invention can be mounted on the rack cabinet, so that the length of the harness is minimized, thereby reducing the generation of noise signals due to the connection of the harness, and connecting the harness. The effect of simplifying and making adjustments can be realized.

As described above, although the present invention has been described by way of limited embodiments and drawings, the present invention is not limited thereto and is intended by those skilled in the art to which the present invention pertains. Of course, various modifications and variations are possible within the scope of equivalents of the claims to be described.

1 is a block diagram of a discrete signal input and output control block of the projectile HILS signal interface system according to an embodiment of the present invention;

2 is a block diagram of an analog signal input and output control block of the signal interface system for a projectile HILS test of FIG. 1;

3 is a block diagram showing a timer control module of the signal interface system for a projectile HILS test of FIG.

Figure 4 is a schematic diagram showing the configuration of the rack cabinet equipped with the signal interface system for the projectile HILS test of FIG.

<Explanation of symbols for main parts of the drawings>

110 ... DSC module 111 ... Disklet input signal converter

112 Discrete output signal converter 113 Discrete signal selector

120 ... ASC module 121 ... Noise reduction filter

122 ... Analog signal selector 140 ... TBB module

150 ... RTS module 200 ... Inertial navigation module

210 ... External measurement module 220 ... Induction control drive module

Claims (11)

In the signal interface system for the projectile HILS test to evaluate the flight simulation of the projectile, An inertial navigation induction module for calculating a navigation and attitude control algorithm such that the projectile is guided to a preset reference coordinate; An induction control drive module that receives information calculated from the inertial navigation module or an RTS module, and controls flight paths of the projectile by controlling posture control, gas thrust, and aerodynamic pins of the projectile; A DSC module which selects an effective drive command signal A among the diskette drive command signals inputted from the inertial navigation module and transmits it to the induction control drive module; An ASC module that selects an effective drive command signal B among analog drive command signals received from the inertial navigation module and transfers the signal to the induction control drive module; A TBB module which is an interface connection module for connecting the inertial navigation module, the inductive control drive module, the external connection device, and the DSC module and the ASC module to each other; It is electrically connected between the inertial navigation module and the induction control drive module to provide data on the flight environment and disturbance conditions for the flight simulation test, and drive command value and induction control drive module of the inertial navigation module. Projectile HILS test signal interface system comprising an RTS module for measuring the feedback command value of. The method of claim 1, wherein the RTS module, And a control efficiency of the system by comparing the measured driving command value of the inertial navigation induction module and the feedback command value of the induction control driving module, and measuring the control efficiency of the projectile HILS test signal interface system. 3. The method of claim 2, Is mounted on the TBB module and electrically connected between the inertial navigation module and the induction control drive module, And an external measurement module for measuring control efficiency of the system by comparing the drive command value transmitted from the inertial navigation module and the feedback command value transmitted from the induction control drive module. The method of claim 3, wherein The valid drive command signal A of the diskette drive commands generated from the inertial navigation module and the RTS module is selected through the diskette signal selector provided in the DSC module, The selected effective drive command signal A drives the induction control drive module via a diskette output signal converter provided in the DSC module, or is transferred to the external measurement module and processed. . The method of claim 3, wherein Of the analog drive commands generated from the inertial navigation module and the RTS module, the valid drive command signal B is selected through an analog signal selector provided in the ASC module. The selected effective drive command signal B drives the induction control drive module via an analog output signal converter provided in the ASC module, or is transferred to the external measurement module and processed. The method of claim 5, The induction control drive module is driven by the selected effective drive command B and generates TVC nozzle angle and RCS nozzle thrust measurement pressure, The generated TVC nozzle angle and the RCS nozzle thrust measurement pressure are input to a noise removing filter provided in the ASC module via an analog input provided in the TBB module, and filtered according to a signal characteristic of a predetermined channel. Projector HILS test signal interface system. The method of claim 6, wherein the noise removing filter unit, A filter interface system for projectile HILS test, characterized in that the filtering is performed according to a signal characteristic of a predetermined channel, and the transmitted analog signal is classified and filtered into one frequency band selected by an internal circuit jumper among 50HZ, 100Hz, and 200Hz. The method of claim 1, And a timer control module configured to drive a timer display by receiving a synchronization signal from the RTS module. The method of claim 8, wherein the timer control module, A mode change switch for setting whether to start the operation mode of the timer display unit indicating the system start time in manual mode or auto mode; A start time setting switch for setting an operating time of the system in the manual mode; And a start time start / stop switch configured to set whether to start or stop a start time when the start time is set through the start time setting switch. The method of claim 9, And the timer display unit is driven by synchronizing the time synchronizing signal generated from the RTS module with the mode change switch when the mode change switch is switched to the automatic mode. The method of claim 1, wherein the TBB module, A signal interface system for a projectile HILS test, in the form of a terminal block assembly.

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