• Title/Summary/Keyword: Guided missile

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A Study on Methods of Measuring and Compensating Misalignment between Inertial Sensor Body and Housing Frame (관성항법장치의 관성 센서축과 하우징 축과의 비정렬 측정과 보상에 관한 연구)

  • Yu, Hae-Sung;Kim, Tae-Hoon;Kim, Cheon-Joong;Lee, Youn-Seon;Park, Heung-Won
    • Journal of the Korea Institute of Military Science and Technology
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    • v.15 no.4
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    • pp.374-380
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    • 2012
  • In guided missile systems, reducing terminal-position error is the primary objective of the inertial navigation system. As a seeker is used to sense and track a target, the critical function of the inertial navigation system is to provide the seeker with accurate missile attitude information and help the seeker to keep tracking a target continuously. As inertial sensor body and missile body alignment errors are taken into account, it is desirable to minimize the alignment errors between the missile seeker and the attitude of inertial navigation system. Among the alignment errors, this paper addresses the methods of measuring and compensating misalignment between inertial sensor body and housing frame and shows test results of several experiments.

A Radar Performance Model for Mission Analyses of Missile Models (유도무기 임무 분석을 위한 레이더 성능 모델)

  • Kim, Jingyu;Woo, S.H. Arman
    • Journal of the Korea Institute of Military Science and Technology
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    • v.20 no.6
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    • pp.822-834
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    • 2017
  • In M&S, radar model is a software module to identify position data of simulation objects. In this paper, we propose a radar performance model for simulations of air defenses. The previous radar simulations are complicated and difficult to model and implement since radar systems in real world themselves require a lot of considerations and computation time. Moreover, the previous radar simulations completely depended on radar equations in academic fields; therefore, there are differences between data from radar equations and data from real world in mission level analyses. In order to solve these problems, we firstly define functionality of radar systems for air defense. Then, we design and implement the radar performance model that is a simple model and deals with being independent from the radar equations in engineering levels of M&S. With our radar performance model, we focus on analyses of missions in our missile model and being operated in measured data in real world in order to make sure of reliability of our mission analysis as much as it is possible. In this paper, we have conducted case studies, and we identified the practicality of our radar performance model.

A Study on Improvement of Launch Performance for Precision Guided Missile by Live-fire test results (사격시험 결과에 따른 정밀 유도무기 발사성능 개선에 관한 연구)

  • Seo, Bo-Gil;Choi, Nak-Sun;Yoon, Young Ho
    • Journal of the Korea Academia-Industrial cooperation Society
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    • v.20 no.9
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    • pp.488-494
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    • 2019
  • Precision Guided Missiles after production and militarization have various characteristics that enable the final performance to be identified by conducting live-fire tests after long-term storage. Likewise, the performance and reliability of ${\bigcirc}{\bigcirc}$ Missiles, which are currently used by the Korean Navy, are also verified consistently by conducting live-fire tests after militarization. Specially, the live fire test at '00 year, which was conducted by Korean Navy, showed the result that 'Ring', which is a component of the canister's front cover, was jammed with wings for propulsion and then broke away from the canister during the missile launch process. This situation led to an interruption of the deployment of wings and finally affected the missile's flight performance. The results of a survey of the canisters of those missiles whose live fire tests were conducted successfully, based on the live fire test at '00 year, showed the 'Ring's separation from canisters. This raises recognition for the need to solve the problems of 'Ring's separation and breakaway. This study suggests an improvement derived by the result of live-fire tests and introduces the effect of final launch performance of ${\bigcirc}{\bigcirc}$ Missiles and test result after applying the improvement.

Development of Reliability Analysis Procedures for Repairable Systems with Interval Failure Time Data and a Related Case Study (구간 고장 데이터가 주어진 수리가능 시스템의 신뢰도 분석절차 개발 및 사례연구)

  • Cho, Cha-Hyun;Yum, Bong-Jin
    • Journal of the Korea Institute of Military Science and Technology
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    • v.14 no.5
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    • pp.859-870
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    • 2011
  • The purpose of this paper is to develop reliability analysis procedures for repairable systems with interval failure time data and apply the procedures for assessing the storage reliability of a subsystem of a certain type of guided missile. In the procedures, the interval failure time data are converted to pseudo failure times using the uniform random generation method, mid-point method or equispaced intervals method. Then, such analytic trend tests as Laplace, Lewis-Robinson, Pair-wise Comparison Nonparametric tests are used to determine whether the failure process follows a renewal or non-renewal process. Monte Carlo simulation experiments are conducted to compare the three conversion methods in terms of the statistical performance for each trend test when the underlying process is homogeneous Poisson, renewal, or non-homogeneous Poisson. The simulation results show that the uniform random generation method is best among the three. These results are applied to actual field data collected for a subsystem of a certain type of guided missile to identify its failure process and to estimate its mean time to failure and annual mean repair cost.

Storage Reliability Evaluation of Engine Assembly (엔진 조립체의 저장 신뢰도 평가)

  • Park, Jong-Won;Chang, Mu-Seong;Park, Tae-Kook;Kim, You-Il;Kim, Sun Je
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.157-159
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    • 2017
  • This paper presents a storage reliability evaluation method based on the accelerated degradation test for the engine assembly and parts of the guided missile. The test of the engine assembly is performed at accelerated conditions equivalent to the real storage period, and then the aging condition of parts is checked. For engine parts, performance degradation characteristics are measured periodically at the accelerated conditions and failure times are predicted at each condition. Storage lifetime at normal use conditions is predicted using an accelerated model and failure times at all accelerated conditions.

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An Analysis of Haeseong Guided Missile Reliability (Using Field Data) (해성 유도탄 발사체계 신뢰도 분석(야전운용제원 활용))

  • Hur, Jangwan;Min, Seungsik;Oh, Kyungwon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.142-143
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    • 2017
  • As weapons systems are fused with advanced technologies, many of the expenses for research and development are favorites, and that group demands high reliability of weapons systems before the lifecycle. However, empirical studies on the reliability of defense weapons systems are restricted to lack of attention and limitation of data. In this research, we proposed the process of collecting field operation specifications based on the experience gathered by visiting directly to the weapons system operator's trap, strategy and maintenance support force (COMROKFLT, Naval Logistics Command, Naval Shipyard, production company). We used this to derive the operation MTBF of the solubility inducing bullet shooting system and compared it with the target value at the time of development.

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A Study on the Wind Tunnel Facility Performance Improvement of ADD Ludwieg Tube (국방과학연구소 Ludwieg Tube 풍동설비 성능개량 연구)

  • Sangjun Ma
    • Journal of Aerospace System Engineering
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    • v.17 no.4
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    • pp.118-125
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    • 2023
  • The wind tunnel test is one of the essential processes in the development of guided missile systems, and various wind tunnel facilities exist depending on the test requirements, various conditions, and their purposes. The Ludwieg tube is very useful in the development of guided missile systems, and we have necessitated the upgrade of the Ludwieg tube in ADD to acquire various test requirements, such as high angle of attack, repeatability, and stability. In this paper, upgrading the nozzle, vacuum tank, and model support is suggested to improve the Ludwieg tube performance, and we demonstrate a result of the solution through pressure measurement.

A performance anaylsis technique for guided weapons (유도무기체계의 성능분석기법)

  • 이연석;이장규;장상근
    • 제어로봇시스템학회:학술대회논문집
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    • 1991.10a
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    • pp.274-279
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    • 1991
  • The development of a guided weapon system, such as a tactical missile, requires a performance analysis of a nonlinear system. Generally, the Monte Carlo analysis method is used for this purpose. The limitation of this method, a large number of simulations, for a nonlinear system performance analysis strongly motivated the development of a more efficient analytic technique. In this paper, the statisfical linearization methods is used for the performance analysis to the guided weapon system with the help of covariance analysis technique. Because the statistical linearization methods cannot be used to the look-up table nonlinear form such as aerodynamic coefficients, the second order polynomial representations is obtained from the table using the Lagrange interpolating polynomial and linearized statistically. Simple simulations about initial state conditions and random component in guidance command shows the results of this technique.

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A Design of Management and Verification Tool of Component and A Development of SAM Simulator based on Dynamic Reconfiguration Architecture (컴포넌트 관리 및 검증도구 설계와 동적 재구성 아키텍처 기반 SAM 시뮬레이터 개발)

  • Suk, Jeebeom;Lee, Jaeoh;Lee, Jaejin;Seo, Yoonho
    • Journal of the Korea Society for Simulation
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    • v.22 no.2
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    • pp.1-10
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    • 2013
  • Modeling and simulation techniques construct experimental environment considering battlefields and are able to analyze performance of components of weapon system that closely resemble reality. However, developed model has low scalability and not cared reusability because it has been used only in a limited range of domain. In this paper, we develop a verification tool to verify reusability of developed component for dynamic reconfiguration and to judge scalability of it and a management tool to control data of it effectively. In addition, dynamic reconfiguration architecture of guided weapon systems designed in the previous study has been applied to SAM(Surface to Air Missile) System Simulator, and we study effectiveness of the developed component. Thus the user can configure various guided weapon systems through simulation application of dynamic reconfiguration architecture of component.