KR101362911B1 - Ofp system for driving a synthetic aperture radar mounted in the flight and controlling method for the same - Google Patents

Abstract

The present invention provides an OFP system for driving a synthetic aperture radar mounted in an airplane and a controlling method for the same, which include: a mission computer in which an OFP, which is mounted in a TA-50 or an FA-50 airplane and performs flight management and mission management of a corresponding airplane, generates and outputs an SAR mode operation signal for SAR mode operation through an SAR mode execution apparatus part; an SAR mode radar which enables a user to trace a target precisely by realizing an SAR image for the target designated by an airplane pilot by making a land cover map of high image quality by realizing an SAR mode according to an SAR mode operation signal transmitted from the mission computer. The present invention enables the airplane pilot to perform a mission by checking target information on the ground accurately, because the present invention realizes an image of high image quality through a synthetic aperture radar in an airplane like a TA-50 and an FA-50, by mounting the synthetic aperture radar in the airplane of the TA-50 or the FA-50 and comprising an OFP system driving the synthetic aperture radar in the mission computer. [Reference numerals] (5) SAP Bullseye module; (7) SU function module; (8) GR Component module; (9) DT Component module

Description

OFP system for driving a Synthetic Aperture Radar mounted in the flight and controlling method for the same}

The present invention relates to an OFP system for driving a synthetic opening radar mounted on an aircraft and a control method thereof. In particular, the synthetic opening radar is mounted on a TA-50 and FA-50 aircraft, and the synthetic opening radar is driven in a mission computer. The present invention relates to an OFP system and a control method for driving a synthetic opening radar mounted on an aircraft that can be significantly improved in the mission precision of an aircraft pilot by implementing the OFP (Operational Flight Program) system.

In general, aircraft, particularly combat aircraft, are equipped with a radar for detecting the opponent's plane or ship, or for automatic tracking of guided objects. At this time, the radar mounted on the combat aircraft as described above usually emits electromagnetic waves of microwaves (microwave, 10cm ~ 100cm wavelength) to the object and receives the electromagnetic waves reflected from the object to find out the distance, direction, and altitude of the object. It is a wireless monitoring device. The radar is classified into a mechanical radar and an electron scanning radar according to a method of changing the scanning direction of the antenna beam. Mechanical radars are called mechanical because dish-like or flat-shaped antennas detect targets as they move mechanically. Electron scanning radars, on the other hand, are called electron scanning because they control the propagation phase of the radiating element mounted on the antenna and change the beam direction electronically. The electron scanning radar is electronically steered in the direction of the beam, so there is no need to move the antenna. Therefore, the electron-scanning radar is characterized by being fixedly fixed to the aircraft's airframe or ship hull. In addition, there are two types of the electromagnetic scanning radar, passive and active. The dual passive electron scanning (PESA) radar has a transmitter and a receiver for generating a radio wave like a mechanical radar. On the other hand, in the active electron scanning (AESA) radar, a small transmission / reception module (TRM), which is responsible for transmitting and receiving beams, is arranged in a large amount on the antenna. On the other hand, the radar of the APG-67 type of the radar as described above is currently used in the Republic of Korea Air Force aircraft, such as TA-50 aircraft.

Then look at the radar device mounted on the conventional TA-50 as described above with reference to FIG.
Onboard the TA-50, the OFP is equipped to carry out the flight management and mission management of the aircraft, and transmits a Total Cursor Range Vector. A computer 70;

Of the OFP of the mission computer 70, the FC OFP GR Component module (Fire Control OFP Ground Range-Thermal Control Program Ground Distance Module: 71) is loaded with a related algorithm and implemented, and then the Total Cursor Range received from the mission computer 70. A DT (Data Transfer-Data Transfer) Component module 72 for outputting the vector by mux communication (muliplexer communication-multiplex communication);

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An APG-67 type radar 73 is used to track an object by displaying an A-G cursor on the Ground Map mode using the Total Cursor Range Vector transmitted from the DT Component module 72.

On the other hand, the operation of the radar device mounted on the conventional TA-50 aircraft as described above, in order to demonstrate the AG Cursor to track the object in the APG-67 radar 73, OFP equipped with a mission computer 70 Send Total Cursor Range Vector to DT Component module 72 by using. Then, the DT Component module 72 loads and implements the related algorithm from the FC OFP GR Component module 71 among the OFPs of the mission computer 70, and mux-communicates the Total Cursor Range Vector to the radar 73. Let's do it.

In this case, the Total Cursor Range Vector indicates the Range Vector X, Y, Z of the platform coordinate system from the aircraft to the SPI.

Accordingly, the APG-67 radar 73 tracks an object by displaying an A-G cursor on the ground map mode (ground map mode) using the total cursor range vector transmitted from the DT component module 72.

However, since the radar device mounted on the conventional TA-50 aircraft does not have a synthetic aperture radar (hereinafter referred to as a SAR (Synthetic Aperture Radar) mode radar), it is not only possible to process high-definition images using SPI coordinates, but also the aircraft pilot. Because the target information on the ground could not be confirmed accurately, the mission could not be performed accurately, and the accurate map could not be implemented on the radar. Therefore, the targets on the ground could not be identified. Therefore, it caused a problem of limiting the performance of the TA-50 aircraft.

Therefore, the present invention has been invented to solve the problems of the prior art as described above, because the aircraft can be implemented in a high-definition image by mounting the SAR mode radar on the TA-50 and FA-50 aircraft aircraft targets on the ground The object of the present invention is to provide an OFP system and a control method for driving a synthetic opening radar mounted on an aircraft to accurately check information and perform a mission.

Still another object of the present invention is to drive a synthetic opening radar mounted on an aircraft presenting high-definition fine-grained identification image information through a SAR mode radar so that the pilot of the aircraft can quickly identify the targets on the ground and perform a desired mission. To provide an OFP system and its control method.

The present invention for achieving the above object is SAR apparatus for SAR mode operation for SAR mode operation of the OFP mounted on the TA-50 and FA-50 aircraft to perform flight management and mission management of the aircraft A mission computer for generating and outputting through the unit;

The aircraft includes a SAR mode radar to precisely track the target by implementing the SAR mode according to the SAR mode operation signal transmitted from the mission computer to implement the SAR image of the target specified by the aircraft pilot. Provides OFP system for driving synthetic opening radar mounted on board.

Another feature of the present invention as described above is to generate the SAR mode operation signal for the SAR mode operation unit for SAR mode operation through the OFP to perform flight management and mission management of the TA-50 or FA-50 aircraft A first process of outputting the SAR mode radar;

After the first process, the SAR mode radar implements the SAR mode according to the SAR mode operation signal transmitted from the mission computer, and implements the SAR image of the target designated by the aircraft pilot by displaying the surface map in high quality. Provides a control method of the OFP system for driving the composite opening radar mounted on the aircraft.

According to the present invention as described above, the TA-50 and FA-50 aircraft are equipped with a synthetic opening radar on the TA-50 and FA-50 aircraft, and the SARP radar is driven in the mission computer. In the aircraft, the SAR mode radar can realize high-definition video, so that the aircraft pilot can accurately check the target information on the ground and perform the mission, thereby significantly improving the mission precision of the aircraft pilot.

In addition, the present invention as described above by presenting high-definition fine-grained identification image information through the SAR mode radar so that the pilot of the aircraft can quickly identify the targets on the ground to perform the desired mission, TA-50 and FA-50 It also has the effect of maximizing the performance of aircraft.

1 is an explanatory view schematically illustrating a radar device of the APG-67 method mounted on the conventional TA-50 and FA-50 aircraft.
2 is an explanatory diagram schematically illustrating an OFP system for driving a SAR mode radar mounted on aircraft of a TA-50 and a FA-50 model according to the present invention;
3 is a flowchart of the present invention.

Hereinafter, preferred embodiments of the system 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 numbers refer to like elements throughout. 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 this specification, the singular forms also include the plural unless specifically stated otherwise in the text. 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 diagram schematically illustrating an OFP system for driving a SAR mode radar mounted on TA-50 and FA-50 aircraft according to the present invention, and FIG. 3 is a flowchart of the present invention.

Referring to Figure 2, OFP system for driving the synthetic opening radar mounted on the aircraft TA-50 and FA-50 in accordance with an embodiment of the present invention,

OFP (1) installed on TA-50 or FA-50 aircraft and performing flight management and mission management of the aircraft, generates SAR mode operation signal for SAR mode operation through SAR mode execution unit (2). A mission computer 3 for outputting;

According to the SAR mode operation signal transmitted from the mission computer 3, the SAR mode radar is implemented to precisely track the target by realizing the SAR map of the target specified by the aircraft pilot by implementing the SAR map in high quality. 4) is configured to include.
Here, the SAR mode operation signal includes a mode command signal (a mode command signal-a signal for commanding a radar from a mission computer), a system point of interest (SPI) coordinate, a target management switch (TMS) signal, and the like.
In addition, the mission computer 3 executes a SAR Bullseye Bearing & Range adjustment function to check a target SAR image displayed on the SAR mode radar 4 by executing a SAR Bullseye Bearing & Range adjustment function. It further includes a SAR Bullseye module (5) for calculating the bearing and range value up to display on the display (6).
On the other hand, the SAR mode execution unit 2 includes a SU function module (7) storing a SU function (Support Utility function-support utility function) algorithm for obtaining SPI coordinates;
A GR (Ground Range-Ground Range) Component module (8) which loads and executes the SU function algorithm from the SU function module (7) and calculates and outputs SAR SPI coordinates based on the SPI Range Vector value;

And a DT Component module 9 which mux-communicates the SAR SPI coordinates calculated by the GR Component module (ground distance module: 8) and outputs them to the SAR mode radar 4.

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On the other hand, in the case of the Korean Air Force, the SAR mode radar, which is known to have superior tracking capability than the APG-68 (v) 5/7 radar mounted on a conventional aircraft such as a TA-50 or FA-50 aircraft by a radar modification project ( 4) For example, an EL / M-2032 radar is mounted and used. In particular, the avionics system of the TA-50 or FA-50 aircraft is composed of an integrated mission computer (IMDC; Integrated Mission / Display Computer). At this time, the mission computer (3) is to control the multiplex (Multiplex Bus) of the double X and Y, the flight control computer is to replace the function in case of failure, the operational capability of the T-50 / A-50 7 Modes: Dogfighting, Missile Overriding, Air-to-Air, Air-to-Surface, Navigation, Selective Jettision, Emergency Jettision), each display device and sensor communicate with each other through the multiple buses, are integrated with other components, and the sensors, display devices and subsystems are each system mode via IMDC. It is gathered together.

Next, a control method of the system of the present invention as described above will be described.

In the method of the present invention, as shown in FIG. 3, the SAR mode operation signal for SAR mode operation is performed through OFP performing flight management and mission management of a TA-50 or FA-50 aircraft in an initial state S1. A first step (S2) of generating and outputting the SAR mode execution unit of the computer to the SAR mode radar;

After the first step (S2), the SAR mode radar implements the SAR mode according to the SAR mode operation signal transmitted from the mission computer to display the surface map in high quality to implement the SAR image for the target specified by the aircraft pilot (S3).

In the first step (S2), the first step (S1-1) in which the GR component module of the SAR mode execution unit unit loads and executes the SU function algorithm from the SU function module;

After the step 1-1, the GR Component module of the SAR mode execution device unit moves the distance from the current aircraft position to the center of the earth. Platform coordinate system Y-axis is east and Z-axis is perpendicular to the XY plane. Unlike the body coordinate system where the X axis changes depending on the aircraft's attitude, this platform coordinate system has the characteristic that the coordinate axis is determined regardless of the aircraft's attitude. Receiving first and second aircraft coordinates calculated by the EGI as a reference;

After the steps 1-2, the GR Component module of the SAR mode execution unit unit calculates the SPI Range Vector (System Point Interest Range Vector) by adding the aircraft coordinates, the steerpoint coordinates and the Cursor values. Calculating steps 1-3;

Steps 1-4 after calculating the SAR SPI coordinates based on the SPI Range Vector value through the SU function algorithm loaded by the GR Component module of the SAR mode execution unit after the steps 1-3;

After the steps 1-4, the DT component module may further include steps 1-5 to mux-communicate SAR SPI coordinates calculated by the GR component module and output the SAR mode radar.

On the other hand, in the second step (S3), if the SAR Bullseye function is set in the mission computer, the SAR Bullseye module executes the SAR Bullseye Bearing & Range adjustment function so that the aircraft pilot can check the target SAR image displayed on the SAR mode radar. It further includes executing the SAR Bullseye function to calculate the bearing & range values up to the point and display it on the display.
Here, the SAR Bullseye function execution step includes moving the SAR pointer (synthetic aperture radar pointer) when the SAR Bullseye module of the mission computer moves the cursor from SAR, and coordinates with the SAR pointer when the TMS (Target Management Switch) is up. A coordinate changing step of changing to SPI coordinates;

If the SAR Bullseye module of the mission computer is not in tracking mode, it calculates the bearings and ranges to the bullseye (prearranged fixed target on the ground) and the SAR pointer, while in the tracking mode, Bullseye and Target (target) The method further includes a Bullseye calculation step for calculating a bearing & range up to the target displayed due to radar search.

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In other words, in order to use the OFP system 10 for driving the synthetic opening radar according to the present invention, first, a mission computer 3 for performing flight management and mission management of an aircraft, for example, a TA-50 or FA-50 aircraft. OFP generates a SAR mode operation signal for the SAR mode radar 4 through the SAR mode execution unit 2 and outputs it to the SAR mode radar 4.

At this time, the GR Component module 8 of the SAR mode execution unit 2 receives the SU function algorithm from the SU function module 7 and executes the SU function algorithm. Receive the aircraft coordinates calculated by The GR Component module 8 of the SAR mode execution unit 2 calculates the SPI Range Vector after adding the aircraft coordinates obtained from the mission computer 3, the steerpoint coordinates, and the Cursor values. Further, the SAR SPI coordinates are calculated on the basis of the SPI Range Vector value obtained as described above through the SU function algorithm loaded with the GR Component module 8 of the SAR mode execution device unit 2 to the DT Component module 9. Output it. Then, the DT Component module 9 mux-communicates the SAR SPI coordinates calculated by the GR Component module 8 and outputs it to the SAR mode radar 4.

Therefore, the SAR mode radar 4 implements the SAR mode through the SAR SPI coordinates transmitted from the mission computer 3 to display the surface map in high quality, so that the aircraft pilot designates the designated target implemented on the SAR mode radar 4. Identify the SAR image of the and clearly carry out the established mission.

On the other hand, if the SAR Bullseye function is set in the mission computer 3 during the SAR mode operation, the SAR Bullseye module 5 provided in the mission computer 3 is operated. At this time, the SAR Bullseye module 5 executes the SAR Bullseye Bearing & Range adjustment function so that the pilot can clearly and accurately confirm the target SAR image displayed on the SAR mode radar (4). Calculate and display on the display installed in the aircraft cockpit.

In this case, the SAR Bullseye module 5 moves the SAR pointer when moving the cursor in the SAR mode radar 4, and changes the coordinates and the SPI coordinates covered by the SAR pointer when the TMS (Target Management Switch) is up.

In addition, the SAR Bullseye module 5 of the mission computer 3 calculates Bearing & Range up to Bullseye and SAR pointer when not in Tracking mode, and calculates Bearing & Range up to Bullseye and Target when in Tracking mode. Reflected on the display 6.

Therefore, according to the present invention as described above, even in the TA-50 or FA-50 aircraft can implement a high-definition image through the SAR mode radar, so that the aircraft pilot can accurately check the target information on the ground to perform the mission As a result, the aircraft pilot's mission accuracy can be significantly increased, and the aircraft's pilots can quickly identify the ground targets and present the highest quality and finest identification image information through the SAR mode radar to perform the desired mission. You can also maximize the performance of the 50 and FA-50 aircraft.

1: OFP 2: SAR mode execution unit
3: mission computer 4: SAR mode radar
5: SAR Bullseye Module 6: Display
7: SU function module 8: GR Component module
9: DT Component Module 10: OFP System

Claims (8)

Operational Flight Program (OFP), which is installed on TA-50 or FA-50 aircraft and performs flight management and mission management of the aircraft, generates SAR mode operation signals for SAR mode operation through the SAR mode execution unit. A mission computer for outputting;
According to the SAR mode operation signal transmitted from the mission computer, the SAR mode is implemented on the aircraft including a SAR mode radar which implements a SAR map for the target designated by the aircraft pilot to track the target. OFP system for driving synthetic aperture radar. The method of claim 1,
The SAR mode operation signal is a OFP system for driving a synthetic opening radar mounted on an aircraft, comprising a mode command signal. . The method of claim 1,
The mission computer calculates the bearing and range values to the target point by executing the SAR Bullseye Bearing & Range adjustment function to check the target SAR image displayed on the SAR mode radar. OFP system for driving the synthetic opening radar mounted on the aircraft, characterized in that it further comprises a SAR Bullseye module to display on the display. The method of claim 1,
The SAR mode execution unit includes: a SU function module storing an SU function algorithm for obtaining SPI coordinates;
A GR (Ground Range-Ground Range) Component module for loading and executing an SU function (support utility function) algorithm from the SU function module and calculating and outputting SAR SPI coordinates based on the SPI Range Vector value;
And a DT Component module for mux-communicating SAR SPI coordinates calculated by the GR Component module (ground distance module) to output the SAR mode radar. SAR mode operation signal for SAR (Synthetic Opening Radar) mode operation is generated by OFP which performs flight management and mission management of TA-50 or FA-50 aircraft. Outputting a first process;
After the first process, the SAR mode radar implements the SAR mode according to the SAR mode operation signal transmitted from the mission computer, and implements the SAR image of the target designated by the aircraft pilot by displaying the surface map in high quality. Control method of OFP system for driving synthetic opening radar mounted on aircraft. The method of claim 5,
The first step includes the step 1-1 that the GR component module of the SAR mode execution unit unit loads and executes the SU function algorithm from the SU function module;
After step 1-1, the GR component module of the SAR mode execution device unit receives the aircraft coordinates calculated by the EGI based on the platform coordinate system (platform coordinate system) based on the distance from the current aircraft position to the earth center; ;
After the steps 1-2, the GR component module of the SAR mode execution unit unit calculates by adding the aircraft coordinates, the steerpoint coordinates and the Cursor value, and then the SPI Range Vecto (System Point Interest Range Vector). calculating steps r-1 to 3;
Steps 1-4 after calculating the SAR SPI coordinates based on the SPI Range Vector value through the SU function algorithm loaded by the GR Component module of the SAR mode execution unit after the steps 1-3;
After the steps 1-4, the DT component module further comprises steps 1-5 for mux-communicating the SAR SPI coordinates calculated by the GR component module to output the SAR mode radar. Control method of OFP system driving radar. The method of claim 5,
In the second step, when the SAR Bullseye function is set in the mission computer, the SAR Bullseye module executes the SAR Bullseye Bearing & Range adjustment function so that the aircraft pilot can check the target SAR image displayed on the SAR mode radar. And a SAR bullseye function executing step of calculating a bearing & range value to a point and displaying the same on a display. The method of claim 7, wherein
In the execution phase of the SAR Bullseye function, when the SAR Bullseye module of the mission computer moves the cursor from SAR, the SAR pointer is moved, and when the TMS (Target Management Switch) is up, the coordinate changed by the SAR pointer and the SPI coordinate is changed. Steps;
If the SAR Bullseye module of the mission computer is not in tracking mode, it calculates the bearing and range up to Bullseye (preset ground fixed target) and SAR pointer, while in tracking mode, Bullseye and Target (target-radar search). And a Bullseye calculation step for calculating a bearing & range up to the target to be displayed.

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