• 한국군사과학기술학회지
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• 제14권6호
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• pp.1031-1036
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• 2011

In this paper, we have proposed a methodology which can test and evaluate on system level in development phase of command guided missile system. Test and evaluation play a significant role in the development of weapon system, providing the means for determining to what extent the weapon system satisfies its requirements, whether it functions normally in the operational environment. In case of command guided missile having seeker, the missile communications link provides data to allow the missile to fly an efficient trajectory toward target. Therefore, it is very important to test and evaluate for data link between missile and radar on whole system aspect. we introduce the concept and devices for system level test and evaluation of command guided missile system.

• 한국군사과학기술학회지
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• 제16권4호
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• pp.449-455
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• 2013

When a missile is launched, a fracture-type canister cover should be properly broken by a collision with a missile or inner pressure of a canister. The fracture performance of a canister cover should be evaluated by a test using a real missile; however, it is unrealistic due to high cost and time restriction in a design stage. In this study, a test technique is newly developed to predict fracture performance of a canister cover. The test was design to have same kinetic energy with a real missile test when the cover is collide with a missile. The effectiveness of the suggested test technique was proved by comparing the test result with that of a real missile test.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 추계 학술대회논문집(수송기계편)
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• pp.57-60
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• 2005

Modal parameters of a structure are the important factor to control the missile maneuver. In general, a dummy structure is used for the modal test of missile structure instead of the real warhead and propellant because there may be the danger of a explosion by the electric shock of test equipment, such as the exciter and the power amplifier. However, the modal testing of a real missile structure is required to acquire the modal parameters and to analyze the missile performance accurately. The new test system and technique are developed to get rid of the danger and secure the safety during the testing. This test system is made of with the computer network system and controlled remote from test site. Using His new test system, the modal test of real missile structure is performed successfully and its validity is proven.

• 한국항행학회논문지
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• 제24권5호
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• pp.423-429
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• 2020

본 논문에서는 전자기 적합성 (EMC; electromagnetic compatibility)시험 규격에 대해 설명하고, 유도탄 구성품과 유도탄 시스템의 전자기 내성 (EMS; electromagnetic susceptibility)시험에 대한 목적과 시험 구성을 확인하였다. 시험구성과 규격은 미 국방규격인 MIL-STD-461F와 MIL-STD-464C를 기반으로 유도탄 구성품과 유도탄 시스템의 구성을 제시하였고, 유도탄 구성품과 유도탄 시스템의 최종운용 상태인 비접지 상태가 구성되도록 설명하였다. 또한, 내성 시험 중 정상상태 확인 방법과 고려해야할 점에 대하여 소개하였다.

• 한국산학기술학회논문지
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• 제20권2호
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• pp.329-335
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• 2019

본 연구에서는 특정 유도무기체계에 대한 신뢰도 성장 분석을 수행하였다. 개발단계에서의 시험을 통해 고장 모드와 원인을 식별하고 시험 중 발견된 고장을 분석하여 지속적인 관리 활동을 수행하고 있다. 해당 유도무기체계는 유도탄과 발사 체계로 구성되어 있으며, 각 장비의 시험 결과에 따라 신뢰도 성장 분석을 실시하였다. 유도탄의 경우에는 일회성 무기로 성공과 실패인 이산형 데이터로 시험 결과를 획득하였다. 발사체계의 경우에는 시험에서 지속해서 장비 운용을 하여 연속형 데이터로 시험 결과를 획득하였다. 각각의 시험 결과 형태로 신뢰도 성장 모델을 Standard Gompertz 모델과 Crow-Extended 모델을 적용하였다. 해당 모델을 사용하여 현재까지 수행한 시험 결과에 대한 신뢰도 성장 분석 결과를 확인하였다. 또한 미래에 수행될 시험 결과를 가정하여 신뢰도 성장 결과를 예측할 수 있었다. 본 연구는 해당 유도무기체계의 신뢰도 목표값을 달성하고 시험 횟수를 결정하는데 있어 유용하게 활용될 수 있을 것이다. 그리고 이후 계획된 시험을 확인하여 해당 유도무기체계에 대한 신뢰도 성장 관리를 지속적으로 추진할 예정이다.

• 한국항행학회논문지
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• 제25권5호
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• pp.313-319
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• 2021

본 논문에서는 MIL-HDBK-344A 기반의 ESS(environmental stress screening) 시험 에 대해 소개하고, 유도탄 내부 케이블의 ESS 시험에 대한 목적과 규격 설정 및 시험 방안에 대하여 확인하였다. ESS 시험구성은 온도 순환과 랜덤 진동의 환경 자극으로 이루어져 있으며, 핸드북의 절차를 기반으로 유도탄 내부 케이블의 ESS 시험 규격 설정과 시험 구성을 제시하고, 진동 시험을 위한 유도탄 내부 케이블의 ESS 시험을 위한 치구를 제작하였다. 스크린 강도(SS; screening strength)를 통해 결정되는 결함 감지 확률은 일회성으로 사용되는 유도탄의 신뢰성에 부합되도록 선정하였고, 또한 ESS 시험 중 유도탄 내부 케이블의 검사방법과 고려해야 할 점에 대하여 소개하였다.

• 한국군사과학기술학회지
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• 제19권5호
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• pp.606-612
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• 2016

A Captive Flight Test(CFT) is used to verify the performance of missile component such as seeker and guiding algorithm of missile. Recently most of surface to air missile adapts multi-mode guidance method which include command guidance and active/passive guidance. A CFT system for missile system adapting multi-mode guidance method consists of pod equipment, command transmitting system and measuring system. In this paper, we proposed CFT system and testing method for missile which adapt multi-mode guidance, and system integration procedure by using distributed missile system integration method and procedure. The proposed CFT system and system integration method was applied to CFT of surface to air missile, and brought successful result.

• 한국정밀공학회지
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• 제33권10호
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• pp.781-787
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• 2016

We introduce FEST (Flight Environment Simulation Test) procedures for precise guided missiles to reliably improve systems. Flight vibration specification was established based on power spectral density curves calculated from flight test data of a high speed precise guided missile. A FEST pre-profile was developed according to flight vibration specification and delivered to a precise guided missile assembly. Vibration responses were measured by installing accelerometers on electronic components vulnerable to dynamic forces. The FEST profile was adjusted by comparing the vibration responses and the flight vibration specification. Subsequently, the FEST profile was repeatedly modified through trial and error, because the responses were similar to the flight environment. The modified FEST profile enabled performance testing of assembled precise guided missiles under simulated flight conditions on the ground, where unexpected errors could be corrected before the flight tests, leading to cost and risk reduction in the development of the precise guided missile system.

• 한국군사과학기술학회지
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• 제27권4호
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• pp.466-473
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• 2024

An Emergency Destruction System is inevitable for ensuring safety both at sea and in populated areas, particularly during emergency detonations triggered by abnormal missile flight or upon mission completion. This paper introduces a novel method for developing an Emergency Destruction System capable of precisely calculating the Instantaneous Impact Point(IIP) during high-speed, maneuverable long-range surface-to-air missile flight tests. The Emergency Destruction System designed for long-range surface-to-air missile flight tests generates impact position tables that meticulously incorporate wind errors and navigation equations based on the Earth's ellipsoidal model. Factors such as the Coriolis effect and the direction of the gravitational acceleration vector are accounted for, significantly enhancing the accuracy of IIP determination amidst highly variable missile speed and attitude.

• 한국군사과학기술학회지
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• 제10권4호
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• pp.176-184
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• 2007

The missile for this study has shown different natural frequency characteristics depending on the test conditions; natural frequencies obtained from its flight test are higher than those in its ground test. It was found that the hinged joints connecting front airframe to rear one had the nonlinear stiffness and caused the missile to show very complex dynamic characteristics. The angular stiffness at hinged joints was calculated using 3D finite element analysis, and it was verified that there was a highly nonlinear relationship between angular stiffness and external load. Natural frequencies calculated considering the nonlinearity of angular stiffness were nearly the same as test results. Through this study, the dynamic characteristics of a missile having split airframes with hinged joints could be clearly identified and a way of maintaining its natural frequencies consistent was generated.