• Defense and Technology
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• no.2 s.204
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• pp.68-79
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• 1996

• Defense and Technology
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• no.12 s.36
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• pp.6-17
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• 1981

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.10
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• pp.817-824
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• 2017

This paper presents the characteristics of wing-tail interference for a tail-controlled missile. The magnitude of wing-tail interference was calculated with wind tunnel test results and its effects on aerodynamic coefficients were investigated. The downwash angle of tail wing was calculated with experimental data and the effect of wing-tail interference was expressed as a ratio of angle of attack. Numerical simulations were made to examine flow characteristics of wing-tail interference and the vorticity contour of missile were compared with respect to angle of attack. Experimental and numerical analysis results show that the wing-tail interference has significant effects on static stability of tail-controlled missile.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.19 no.8
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• pp.1965-1972
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• 2015

The Missile Flight Test Launch Control System is to operate in conjunction with the Fire Control System during flight test to guided weapons. Also, this is a system for the test control and situation monitoring depending on the type of guided weapons and testing purposes. Message structure, communication protocols, such as data types for interworking with the fire control system and the Missile Flight Test Launch Control System are defined in the Launch Control ICD(Interface Control Document). ICD are composed differently of each guided weapons system and each test object. Previously, in order to interwork with the Fire Control System, the interlocking software was developed, which had a variety of problems. Therefore, we developed a new parsing algorithm in order to recognize the variety of Launch Control ICD and verified that the algorithm operates normally by checking transmitting and receiving various message in conjunction with the fire control system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.4
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• pp.245-255
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• 2019

This paper describes on aerodynamic analysis based on the truncation rate of guided-weapon nose using computational fluid dynamics. The shape to perform the analysis is only the body of the guided weapon and the diameter to length ratio is 10.7. Three nose shapes were selected and hemisphere, 25% and 50% truncation were compared. For the accurate CFD analysis of the body, the grid method and the analytical method were selected and verified using NASA wind tunnel test data. For the three nose shapes, the drag analysis for the flight Mach number is 6~20% different. This difference was analyzed by the pressure distribution from nose to base.

• Journal of Advanced Navigation Technology
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• v.22 no.2
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• pp.105-110
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• 2018

The North Korea nuclear issue is now posing a serious security threat to the Korea and Northeast Asia. Accordingly, the South Korean military is pushing for the introduction of long-range air-to-surface flights and the development of domestic nuclear facilities that can precisely hit North Korea headquarters building and nuclear facility even hundreds of kilometers above the border. In this paper, we removed the cable braid for securing the weight of the missile among several design elements for long-range air-to-surface missile development and estimated and analyzed the resulting performance. The possibility of braid removal was analyzed in terms of crosstalk inside the cable and CS114, RE101 of MIL-STD-461F.

• Defense and Technology
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• no.2 s.192
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• pp.48-55
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• 1995

최근 러시아는 무기의 해외판매에 주력하고 있으며, 이의 일환으로 '93년에 무기전시회와 에어쇼를 통해 여러 종류의 무기를 공개전시하였으나 기술적 내용과 특징은 잘 알려져 있지 않다. 이 글에 소개된 내용은 S-300V, S-300 PMU, TOR 등 대공유도무기용 위상배열레이다를 중심으로 하여 우리 군과 방산종사자들의 관심이 많은 대공방어체계용 레이다 관련 자료를 모으고 기술적인 해석을 하였다.

• Convergence Security Journal
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• v.7 no.2
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• pp.145-154
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• 2007

In this paper, a study on the actuator device technology in guided weapon system development. Hydraulic and pressure, electric motor device had been mostly used, but recently due to high output to weight ratio, pressure actuator device is widely used except for small tactical guided ammunition which needed small power. And now the actuator design concept and technical level is changed because of high mobility of guided ammunition, development of magnetic materials which used new material for requirement of despondence, progress of control and electrodynamics technology, and digitalize and integrity. In this paper we clearly proposed the actuator design criteria and detailed technology development trend for next generation guided weapon system.

• Journal of Aerospace System Engineering
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• v.11 no.5
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• pp.50-55
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• 2017

This research describes the ConOps(Concept of Operations) of sea-based guided weapon systems. The ConOps describes how the proposed system is to be used and is more descriptive than technical in terms of various stakeholders. It should be prepared to support the concept of the life cycle stage of the system. Developing ConOps plays an important role in ensuring that operational/maintenance, maintenance, and acquisition and development areas are better understood by users' needs and expectations. In this point of view, this work presents the process of deriving ConOps and aims to derive operational concept of maritime guided weapon system by using tools.

• Journal of Aerospace System Engineering
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• v.16 no.5
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• pp.94-101
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• 2022

In this paper, we have obtained the acceleration coefficient of the IMU (Inertial Measurement Unit) to prove reliability by analyzing the characteristic of the MEMS IMU installed in guided weapon systems for overseas export and the operating environment of the guided weapon system. Additionally, based on designed life testing, we performed life tests on three the IMUs and demonstrated a target lifetime of 12 years.