KR20150104842A - Appatatus for aircraft captive flight test for guided anti-tank missile - Google Patents

Abstract

The present invention relates to an apparatus for a captive flight test for an antitank guided weapon for carrying out an efficient captive flight test (CFT) for an antitank guided weapon, which comprises an unmanned vehicle automatically flying along a pre-input flight trace of a guided missile; a target system measuring location information of a target; and a captive test specimen automatically copying the trace of the guided missile by controlling a triaxial operation of a specimen-mounted frame mounted based on the measured location information of the target and flight state information provided from the unmanned vehicle.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to an anti-

The present invention relates to an on-board flight test apparatus for an anti-tank-guided weapon capable of performing an efficient on-board flight test (CFT) on an anti-tank guided weapon.

In the process of developing missile, it is very important to test the performance of missile on demand. Various development tests such as injection test, plan guided flight test and comprehensive guided flight test conducted during the system development period, development and operation test after completion of development (DT / OT & E) Tests that verify performance by launching real missiles in order to verify performance should involve significant resource / time and effort in terms of cost and schedule.

Therefore, in order to verify the performance of the development missile, which is in the range of hundreds of millions to several billion won within the scope of the limited system development budget, there is a cost limitation in terms of the quantity of the missile to be tested. There are also certain restrictions that require you to complete all tests. However, it is also a serious risk to the developer to conduct the test evaluation without thorough verification and verification of the guided weapons during the weapon system development period.

In order to overcome the cost and certain limitations of the actual shooting test and to test and verify the performance of the navigator and induction steering system, which is the core system of the missile in various test environments during the development period, Captive Flight Test: CFT).

The conventional CFT method of the anti-tank guided weapon, which has been performed in the prior art, is to manufacture / mount a Captive Test Pod (CTP) integrated with a test vehicle, a searcher / navigator / data acquisition / And the CTP operator boarded the flight and carried out the onboard flight test. However, there are two major limitations to the onboard flight test conducted using manned aircraft.

The first is that it can not accurately simulate the flight trajectory for the altitude of the missile. In order to accurately verify / verify the performance of the navigator and induction control system, which is a core part of the guided missile, it is necessary to accurately simulate changes in the attitude angle of the shot and the gaze angle with the target according to the missile flight trajectory. However, the maneuvering maneuver that the pilot controls manually has a limitation in accurately simulating the missile trajectory. However, in order to improve the accuracy of the trajectory simulation, it is considered to be an undesirable method in consideration of the safety of the manned vehicle by modifying the maneuvering software of the maneuvering body so as to enable automatic flight according to the guided vehicle trajectory. In addition, it is impossible to simulate the map of the guided missile by the CTP operator.

The second is a matter of safety. In order to verify the performance of the anti-tank missile, test evaluation should be conducted in an environment where the actual weapon system is operated. Most of the operational areas where anti-tank missiles are operated are mostly mountainous. It is a dangerous flight mission to carry out a test to ascertain the performance of a development weapon system rather than a military operation in such a mountainous area, and to approach a target of 2 - 30 m near the target while two or three pilots and CTP operation personnel are on board. And it is inevitable that it will be restricted by manned flight due to various weather conditions (rain, snow, wind, etc.). In addition, tracking performance verification is an important part in the target proximity distance where the target occupies most of the target area on the explorer screen. In the CFT using the manned helicopter, the approach to the target is restricted due to the safety problem.

It is an object of the present invention to provide an apparatus and method for a flight test apparatus for an anti-tank guided weapon capable of relatively accurately simulating the flight trajectory of an anti-tank guided weapon and the flight attitude of a pilot missile.

It is another object of the present invention to provide an apparatus and method for mounting an anti-tank guided weapon capable of overcoming safety-related limitations and carrying out an on-board flight test even under various test locations, times, environments and target conditions .

According to another aspect of the present invention, there is provided an apparatus for mounting an anti-tank guided weapon according to an embodiment of the present invention. A mounted specimen mounted on a unmanned aerial vehicle with a specimen mounted thereon; And a target system for measuring the position information of the target and transmitting the measured position information to the mounted test object, wherein the mounted test object controls the three-axis driving of the test object mounting frame based on the position information of the target and the flight status information of the unmanned aerial vehicle To simulate the flight path of the missile and the attitude of the shot.

The mounted test body controls the roll, pitch, and yaw angle of the driving device according to the flight distance and simulated missile position information and target information of the simulated missiles, and performs posture simulation of the flying missile.

The mounting portion of the unmanned aerial vehicle and the mounted test object is equipped with a dustproof structure for suppressing vibration transmitted from the rotor of the unmanned aerial vehicle, and the mounted test object equipped with the dustproof structure is mounted on the rotor shaft of the unmanned aerial vehicle.

The present invention provides a unmanned aerial vehicle equipped with an anti-tank guided weapon mounted test object, thereby accurately capturing the target flight trajectory and the attitude of the shot, It can be confirmed / verified accurately in an environment such as a flight situation. In addition, the present invention overcomes the safety-related limitations that can be incurred when using a manned vehicle, thereby enabling flight tests to be carried out under various test locations, times, environments, and target conditions.

FIG. 1 is a conceptual diagram illustrating the operation of a CFT (Flight Test) using an onboard flight test apparatus of an anti-tank guided weapon according to an embodiment of the present invention; FIG.
2 is a functional block diagram of a loaded test specimen (CTP).
Fig. 3 is a view showing a schematic shape of a mounted test object; Fig.
Fig. 4 is a perspective view of a vibration damping structure applied to a mounting body mounted on an unmanned aerial vehicle.

In accordance with an embodiment of the present invention, there is a need for three sub-systems for the on-board flight test apparatus of an anti-tank guided weapon.

The first is a unmanned aerial vehicle that acts as a platform to simulate the guided weapon trajectory. Unmanned aerial vehicles that can be operated on the CFT include flywheels and fixed wing unmanned aerial vehicles, depending on their flight characteristics. Depending on the flight characteristics and trajectory of the missile, which is the subject (subject) navigator and the guidance control device, it is decided which type of unmanned aerial vehicle to use as the platform. For example, it is desirable to select a turbocharged unmanned aerial vehicle for a guided car with a large change in trajectory while flying at a relatively low speed with respect to a target located at a short range, and a fixed-wing unmanned aerial vehicle is selected as a platform for long- . Especially, it is considered that the use of a flywheel unmanned aerial vehicle for the purpose of confirming the sub-system performance of the anti-tank missile will meet the purpose of the test.

The advantage obtained by using the unmanned aerial vehicle is that the flight trajectory information of the missile can be pre-inputted into the flight control computer (FCC) of the unmanned aerial vehicle to simulate the missile flight trajectory relatively accurately. In addition, it is possible to secure the reliability of data by acquiring / verifying information obtained from the ground control site (GCS) remotely in real time on the unmanned aerial vehicle in flight.

The second is the mounted test specimen (CTP).

The CTP includes a test object (a guided vehicle with an explorer and an induction control device) to be tested for its performance, and can be used not only as a platform for mounting a test object on an unmanned aerial vehicle, And perform the roles simultaneously. The attitude simulation of the missile in flight can be performed by inputting the simulated missile's flight distance and altitude's missile position information to the mounted computer mounted on the CTP and operating the roll, pitch and yaw drive motor of the mounted specimen . In this case, it is necessary to correct the posture of the mounted specimen by receiving information on the flight attitude of the unmanned aerial vehicle. It is also important to apply the anti-vibration structure to the unmanned aerial vehicle and the CTP fastening part so that disturbances such as vibration and impact generated in the unmanned aerial vehicle are not transmitted to the mounted test object (CTP) in order to secure the reliability of the acquired data.

Finally, there is a need for a target system that transmits positional information about the stop and travel target to a computer onboard the Ground Control Center (GCS) and on-board (CTP). The main function of the target system is to allow the on-board (CTP) mounted on the unmanned aerial vehicle (CTP) to constantly direct / track the target based on the relative position information of the target, unmanned aerial vehicle and ground control station (GCS).

1 illustrates the concept of operating a CFT using an onboard flight test apparatus of an anti-tank guided weapon according to an embodiment of the present invention.

As shown in FIG. 1, a remote manual pilot of the CTP operator and the unmanned helicopter (unmanned helicopter) 100 is located in the ground control station (GCS) 102.

Before performing the CFT, the CTP operator inputs the flight trajectory data of the missile into the FCC of the unmanned air vehicle 100, and performs the launching process when the actual missile is fired . When the launch procedure is completed on the ground, the UAV 100 prepares for the flight test, and the remote manual pilot of the ground control station 102 prepares for the accident and dangerous situations of the unmanned aerial vehicle do.

When the unmanned air vehicle 100 acquires an appropriate altitude for automatic flight (generally 10 to 20 m in the case of the unmanned helicopter), the unmanned air vehicle 100 performs automatic flight according to the pre- Test (CFT). The flight control computer (FCC) of the unmanned aerial vehicle 100 includes information on the attitude of the unmanned aerial vehicle 100, attitude information of the CTP 101, navigator image information acquired from the subject, (Red arrow), and the target system 103 transmits positional information about the target to a mounting computer (102) mounted on a mounting test body (CTP) ) (Red arrow). At this time, the tracking performance of the unmanned vehicle (100) flight searcher can be confirmed through the analog searcher image transmitted to the GCS 102 in real time, and the digital image of the searcher is stored in the original form Stored and used for future analysis purposes.

Conventionally, a target system for transmitting target location information has not been implemented, so a CTP operator has to manually direct the CTP 101 as a target through the screen of the computer.

2 is a functional block diagram of a mounted test object 101 according to the present invention.

2, the mounted test object 101 according to the present invention includes a test object mounting frame (gimbal) 50 to which a test object is mounted, (CFT POD part) 51 for receiving the flight status information of the unmanned air vehicle 100 and controlling the three-axis motions of the test object mounting frame 50 to simulate the trajectory of the guided vehicle.

The mounted specimen 101 includes a modem for receiving position information of a target from a target system; (Modem) for transmitting and receiving data obtained from the object to be tested, and an Attitude & Heading Reference System (AHRS) for transmitting attitude information of the unmanned air vehicle 100. The AHRS provides attitude information of the UAV 100 to the CTP 101 to simulate the attitude of the missile on the on-board flight test. However, when the unmanned aerial vehicle 100 can directly receive the information on the flight attitude, it is not necessary to use a separate AHRS sensor.

In the present invention, the object to be tested may be a searcher mounted on a guided vehicle, and optical measuring instruments such as LWIR, MWIR, and CCD may be mounted to obtain infrared and visible images of the target according to the purpose of the test.

Fig. 3 shows a schematic shape of the designed mounted test specimen.

Referring to FIG. 3, the frame to be tested is designed to be capable of driving three axes (roll, pitch, and yaw) for the purpose of tracking and tracking a target object of a mounted test object (CTP). As shown in the figure, when the infrared ray searcher is to be tested, a cooling gas cylinder for supplying a cooling gas to the detector is additionally attached. In addition, a mounting computer and a video signal transmitting / receiving device, which are responsible for transmitting and receiving the data (including video) and the drive command of the CTP acquired from the object to be tested, are mounted. The skid portion of the unmanned aerial vehicle should be constructed considering the driving range of the mounting frame and the angle of view of the subject chain searcher, and the pedestal portion should not be displayed on the navigator image between the flight tests.

Fig. 4 shows the mounting portion of the unmanned aerial vehicle and the CTP.

A preliminary requirement for the onboard flight test using the unmanned aerial vehicle (100) is how to reduce the mechanical vibration and shock transmitted from the unmanned aerial vehicle (100) to the mounted test object (CTP). Most of the vibration is caused by the rotation of the rotor. In particular, in the case of the onboard flight test where a small target located at a long distance is to be captured / tracked using a rotary wing unmanned aerial vehicle, the target may not be captured / tracked due to the vibration transmitted from the rotor of the wing wing unmanned aerial vehicle.

The most efficient way to mechanically eliminate such vibrations is to place the center of gravity of the CTP on the rotor shaft of the rotor flywheel. In the CFT using the conventional induction helicopter, it was impossible to attach the CTP to the rotor shaft of the helicopter by extending the height of the helicopter, so it was inevitable to mount the CTP on one side of the left or right side of the helicopter.

As shown in FIG. 4, the present invention applies a dustproof structure to the unmanned aerial vehicle and the CTP mounting part to suppress the vibration transmitted from the rotor of the rotary wing unmanned aerial vehicle. In order to apply the anti-vibration structure, the following steps are performed.

First, the vibration of the unmanned aerial vehicle, which occurs when the unmanned aerial vehicle is flying with no load and CTP, is measured, and a vibration damping material capable of reducing the amplitude of the maximum vibration frequency band is selected. Once the vibration damping material is selected, determine the quantity of the vibration damping material considering the total weight of the mounted specimen, and select the position where the vibration and impact can be absorbed equally in the material. Finally, by mounting the mounted specimen with the dustproof structure on the shaft of the unmanned helicopter rotor, the vibration transmitted from the unmanned helicopter to the mounted specimen can be minimized.

As described above, according to the present invention, not only can the trajectory of the missile can be simulated by controlling the three-axis driving of the object mounting frame based on the position information of the target and the flight state information of the unmanned air vehicle, It is possible to accurately identify and verify the target acquisition and tracking performance of the DU chain seeker and the guidance control device between the UAV and the UAV in the same circumstances as the flight situation. In addition, the present invention overcomes the safety-related limitations that may arise when a manned vehicle is used, so that flight tests can be carried out even under various test locations, times, environments and target conditions.

It will be appreciated that the configurations and methods of the embodiments described above are not to be limited and that the embodiments may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. Therefore, it should be understood that the above-described embodiments are to be considered in all respects as illustrative and not restrictive.

100: unmanned aerial vehicle 101: mounted test body
103: Target system

Claims (10)

An unmanned aerial vehicle that autonomously flies according to the trajectory of the inputted missile;
A mounted specimen mounted on a unmanned aerial vehicle with a specimen mounted thereon; And
And a target system for measuring the position information of the target and transmitting the position information to the mounted specimen,
Wherein the three-axis drive of the frame for mounting the test object is controlled based on the position information of the target and the flight status information of the unmanned aerial vehicle to automatically simulate the flight trajectory and the attitude of the shotgun, . 2. The method of claim 1, wherein the unmanned aerial vehicle
Wherein said at least one of said at least one of said at least one of said at least one of said at least one of said at least one at least one of said at least one at least one of said at least one of said at least one of said at least one of 2. The method of claim 1, wherein the unmanned aerial vehicle
And the trajectory of the missile to be tested is determined according to the flight characteristics and trajectory of the missile to be tested. The apparatus according to claim 1,
A modem for receiving location information of the target from the target system;
A frame to be tested for mounting a test object;
A video signal transmitting and receiving device for transmitting and receiving data obtained from a test object;
Attitude & Heading Reference System (AHRS) to transmit posture information of unmanned aerial vehicle; And
And a mounting computer for controlling the three-axis driving of the test object mounting frame based on the position information of the target and the flight status information of the unmanned aerial vehicle. The system of claim 1, wherein the target system
Wherein the target mounted on the unmanned aerial vehicle based on the relative position information of the target, the unmanned aerial vehicle and the ground control station is capable of continuously aiming / tracking the target. The apparatus according to claim 1,
Wherein the attitude of the anti-tank guided weapon is controlled by controlling the roll, pitch and yaw angle of the drive unit according to the flight distance and the altitude of the simulated missile, tester. The mounting structure of the unmanned aerial vehicle according to claim 1,
Wherein the anti-vibration structure is installed to suppress the vibration transmitted from the rotor of the unmanned aerial vehicle. The mounting test instrument according to claim 7,
Mounted on a rotor shaft of an unmanned aerial vehicle. 2. The method of claim 1, wherein the unmanned aerial vehicle
Wherein the attitude information of the unmanned aerial vehicle, the attitude information of the mount body of the mount, the image information of the navigator acquired from the specimen, and the command information generated by the induction steering apparatus are transmitted to the ground control station in real time. The apparatus of claim 1, further comprising a ground control station for confirming the tracking performance of the unmanned aerial vehicle navigator through a navigator image transmitted from the loading test body.

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