• Journal of the Korea Society for Simulation
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• v.27 no.1
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• pp.111-117
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• 2018

It is indispensable for a missile to track a target under the flight condition since the tracking capability affects the system performance considerably. The best way to verify the tracker's performance is flight test while it costs too much. Consequently, captive flight test or CFT has an important role in the development of a missile system. CFT, however, cannot simulate missile dynamics and is an offline and open-loop test. In this paper, we propose a new integrated-flight simulation(IFS) method using CFT imagery to overcome the limitation of synthetic image-based IFS method. This method increases the utilization of CFT's outputs and compensates the reality of imagery which lacks in the synthetic image-based IFS. Using this method make it possible to verify the system capability in various simulation modes.

• Journal of the Korea Institute of Military Science and Technology
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• v.22 no.4
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• pp.536-544
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• 2019

During the assembly and function inspection of missile system, flight simulation process is required. In the conventional flight simulation check of missiles, an inertial navigation system simulator was used to transmit the navigation output data acquired in HILS. There are several disadvantages in terms of check configuration complexity and data synchronization when using the simulator. So we proposed a new flight simulation method that utilizes the nonvolatile built-in memory of the aviation control unit. The data processing procedure and operation procedure of the proposed method for type I and type II missiles are presented. And we analyzed the causes of the difference between proposed method result and the HILS result for type II missile. By comparing the results obtained by the experiments using the proposed method with the results of HILS, the validity of proposed method was confirmed.

• Journal of the Korea Society for Simulation
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• v.26 no.1
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• pp.13-19
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• 2017

6-DOF flight simulation program is most generally used M&S tool in domestic missile development procedure. The 6-DOF M&S method, however, cannot validate the performance of a imaging seeker-adopted missile in various conditions. A M&S tool for the analysis of the integrated-flight simulation is required since the tracking performance of the imaging seeker is highly dependent on the missile maneuvering, which introduces the displacement and rotation of the target in the seeker imagery. Through the development of the $3^{rd}$ generation anti-tank missile, Raybolt, the integrated-flight M&S tool was developed and applied to the missile configuration design. It integrates synthetic image generation S/W, imaging tracker, and flight simulation program and computes the main system performance criteria, hit probability by Monte-Carlo Simulation. In this paper, the issues in the $3^{rd}$ generation anti-tank missile configuration and the integrated-flight M&S method and results are described.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1997.11a
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• pp.4-4
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• 1997

로켓 조종장치는 크게 추력방향 조종(TVC, Thrust Vector Control) 장치, 측면추력조종(Lateral Thrust Control) 장치 그리고 공기역학 조종면으로 분류할 수 있다. 조종장치의 공통된 특징은 모터가 작동하거나 유도탄이 비행할 때만 타의 효과가 발생한다는 점이다. 그러므로 조종장치를 개발하기 위해서는 이상류 초음속 유동이나 삼음속 이상의 자유유동(freestream)을 지상에서 효과적으로 모의할 수 있는 지상 시험장치가 필요하다. 이 시험장치에는 초음속 풍동과 유동 시험장치(cold-flow test stand), 그리고 6분력 트러스트 스텐드가 포함된다. 삼성항공은 우주용 추진기관의 성능을 지상에서 간단한 장치를 구현하여 시험할 수 있는 모의연소 시험장치, 노즐유동에 포함된 고체입자를 직접 수집할 수 있는 고체입자 포집장치 등 각종 시험장치를 제작하였다. 이를 바탕으로 차세대 전술유도탄의 핵심기술가운데 하나인 조종장치와 이를 효과적으로 개발하기 위한 지상 시험장치 확보에 착수하고 있다.

• Journal of the Korean Institute of Telematics and Electronics S
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• v.36S no.6
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• pp.45-56
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• 1999

This paper presents a method for designing an autopilot of the BTT missile using 2DOF Wiener-Hopf control technique to improve tracking performance. Linear controllers are designed based on the linearized models which are obtained from the nonlinear missile dynamic equations at various operating points. The gain scheduling technique is used to implement the final autopilot. A simulation on the flight of missiles is carried out through the use of 6DOF equation program including exact nonlinear equations of the missile and the variations of aerodynamic variables in order to check applicability of the suggested method in real situation.

• Journal of Advanced Navigation Technology
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• v.26 no.2
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• pp.47-53
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• 2022

With the recent development of defense technology, various aircraft armaments/equipments are being developed. Among them, cruise guided weapons(missile) for launching aircraft can be installed on aircraft aftersecuring reliability and safety through varioustests. In order to avoid collision with aircraft, missile separated from aircraft must release restraint of wing at the specified time, control wing in the specified direction. In order to confirm this, a test system that can control MIL-STD-1760 according to safety separation procedure and verify release performance is required. test system needs a function to check circuit for release of restraints and a function to check driving performance by controlling MIL-STD-1760. In addition, test system should be simulate environment separated from aircraft. This paper presented a testsystemthat can verify circuit and driving performance mounted on missile according to the safety separation procedure, and it was confirmed that it was normally separated from aircraft through flight tests.

• Proceedings of the KIEE Conference
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• 2005.07d
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• pp.2540-2542
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• 2005

This paper proposed the new HILS technique called Injection Method for Inertial Sensor Verification of high maneuvering missiles. The performance of Inertial Sensor is verified by Injection Method and traditional FMS Method. After all, Injection Method for Inertial Sensor has capability for various scenario and critical condition test.

• Journal of the Korea Institute of Military Science and Technology
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• v.19 no.2
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• pp.185-194
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• 2016

It is essential for generating the synthetic image to test and evaluate a guided missile system in the hardware-in-the-loop simulation. In order to make the evaluation results to be more reliable, the extent of fidelity and rendering performance of the synthetic image cannot be left ignored. There are numerous challenges to simulate the LWIR sensor signature of sea surface depending on the incident angle, especially in the maritime environment. In this paper, we investigate the key factors in determining the apparent temperature of sea surface and propose the approximate formula consisting of optical characteristics of sea surface and sky radiance. We find that the greater the incident angle increases, the larger the reflectivity of sea surface, and the greater the water vapor concentration in atmosphere increases, the larger the amount of sky radiance. On the basis of this information, we generate the virtual maritime environment in LWIR region using the SE-WORKBENCH, physically based rendering software. The margin of error is under seven percentage points.