• Proceedings of the Korean Society of Precision Engineering Conference
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• 2009.10a
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• pp.535-536
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• 2009

• Strategy21
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• s.41
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• pp.232-260
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• 2017

The purpose of this paper is to open a debate about what kind of deterrent strategy the ROK military should pursue in the era of NK's weapons of mass destruction and missile threats. I argue that the ROK military needs a comprehensive deterrent strategy that reflects the international security situations and trends and that builds on clear understanding of the basic concepts and how deterrence operates. The paper starts with surveying the basic knowledge of deterrence from the perspectives of both theory and practice. Then, it provides explanations on why deterrence against NK can be particularly difficult given the security environment in and around the Korean peninsula. For example, South Korea and North Korea hardly share 'common knowledge' that serves as a basic element for the operation of deterrence. Deterrence against North Korea involves complex situations in that both deterrence and compellence strategies may be relevant particularly to North Korea's WMD and missile threats. It also involves both immediate and general deterrence. Based on the discussion, I suggest several ideas that may serve as guidelines for establishing a deterrent strategy against NK. First, our threats for deterrence should be the ones that can be realized, particularly in terms of the international norms. In other words, they must be considered appropriate among other nations in the international community. Second, there should be separate plans for the different kinds of threats: one is conventional, local provocations and the other is WMD/missile related provocations. Third, we should pursue much closer cooperative relations with the U.S. military to enhance the effectiveness of immediate deterrence in the Korean peninsula. Fourth, the ROK military should aim to accomplish 'smart deterrence' maximizing the benefits of technological superiority. Fifth, the ROK military readiness and structure should be able to deny emerging North Korean military threats such as the submarine-launched ballistic missiles and intercontinental ballistic missiles. Lastly, in executing threats, we should consider that the current action influences credibility and reputation of the ROK, which in turn affect the decisions for future provocations. North Korea's WMD/missile threats may soon become critical strategic-level threats to South Korea. In retrospect, the first debate on building a missile defense system in South Korea dates back to the 1980s. Mostly the debate has centered on whether or not South Korea's system should be integrated into the U.S. missile defense system. In the meantime, North Korea has become a small nuclear power that can threaten the United States with the ballistic missiles capability. If North Korea completes the SLBM program and loads the missiles on a submarine with improved underwater operation capability, then, South Korea may have to face the reality of power politics demonstrated by Thucydides through the Athenians: "The strong do what they have the power to do, the weak accept what they have to accept."

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2002.11b
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• pp.914-920
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• 2002

Nonlinear flow-induced vibration characteristics of a generic missile wing (or control surface) are investigated in this study. The wing model has freeplay structural nonlinearity at its pitch axis. Nonlinear aerodynamic flows with unsteady shock waves are considered in the transonic flow region. To practically consider the effects of freeplay structural nonlinearity, the fictitious mass method (FMM) is applied to structural vibration analysis based on a finite element method (FEM). A computational fluid dynamics (CFD) technique is used for computing the nonlinear unsteady aerodynamics of all-movable wings. The aerodynamic analysis is based on the efficient transonic small-disturbance aerodynamic equations of motion using the potential-flow theory. To solve the nonlinear aeroelastic governing equations including the freeplay effect, a modal-based computational structural dynamic (CSD) analysis technique based on fictitious mass method (FMM) is used in time-domain. In addition, CSD and unsteady CFD techniques are simultaneously coupled to give accurate computational results. Various aeroelastic computations have been performed for a generic missile wing model. Linear and nonlinear aeroelastic computations have been conducted and the characteristics of flow-induced vibration are introduced.

• Journal of the Korea Society for Simulation
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• v.25 no.1
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• pp.1-9
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• 2016

This study focuses on the air to air missile control fin planform optimization for the minimizing hinge moment with the considering phenomena of fluid and structure simultaneously. The fluid-structure interaction method is applied for the fluid and structure phenomena simulation of the control fins. A transient-loosely coupled method is used for the fluid-structure interaction simulation because it is suited for using each fluid and structure dedicated simulation software. Searching global optimization point is required many re-calculation therefore in this study, a mathematical model is applied for rapidly calculation. The face centered central composite method is used for generating design points and the 2nd polynomial response surface is sued for generating mathematical model. Global optimization is performed by using the generic algorithm. An objective function is the minimizing travel distance of the center of pressure between Mach 0.7 and 2.0 condition. Finally, the objective function of optimized planform is reduced 7.5% than the baseline planform with satisfying constrained conditions.

• 제어로봇시스템학회:학술대회논문집
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• 2003.10a
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• pp.537-541
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• 2003

In order to control the missiles by aerodynamics, control surfaces sometime called fins are used. Deflection angles of these fins are the right control variables of the aerodynamics, but aerodynamicists prefer to use analytic variables called aileron, elevator and rudder instead of these physical variables, because these three analytic variables dominantly influence on the roll, pitch and yaw channels of the missile maneuver, respectively, and each can be assumed a linear combination of four fin deflection angles. On that basis, roll, pitch and yaw autopilots for controlling the attitudes or lateral acceleration of the missile are designed, and as a consequence outputs of each autopilot are aileron, elevator and rudder commands, respectively. In the existing fin control scheme for the typical tail-fin controlled cruciform missiles, firstly these outputs are distributed to four fin defection commands, and after that four fins are actuated by fin controllers so that their deflections follow the commands. This paper shows that performance of such control schemes can be degraded significantly when fin actuators have certain physical constraints such as slew rate, voltage or current limit, uncertainty of actuator dynamics, and so on, and propose a new control scheme which alleviates such problems. This scheme can be widely applied to various fin actuation systems. But in this paper, for convenience, tail-fin controlled cruciform missile is taken as an example, and it is shown that a proposed control scheme gives better performance than the existing one.

• 한국전산유체공학회:학술대회논문집
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• 2008.08a
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• pp.62.1-62.1
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• 2008

• Proceedings of the KSR Conference
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• 2007.11a
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• pp.1036-1041
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• 2007

In this paper, we studied the optimized design of roof structure to be separable roof structure. Also, the design have to satisfy with the GM/RT 2100' missile protection tests to verify the safety of railway vehicle structure. The separable roof structure design could have easier assembly process than whole roof structure in case of the interior outfitting and so on. Optimized design have to have as good as whole roof structure about results from the structure analysis. We studied separable roof structure to be optimized along with GM/RT 2100. The separable roof structure showed that the results have the same level of structure analysis

• 제어로봇시스템학회:학술대회논문집
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• 2003.10a
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• pp.1822-1825
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• 2003

A practical range estimator based on the robust Kalman filter is proposed to solve the range estimation problem for surface to air missile(SAM) homing guidance. Apart from the previous works based on the extended Kalman filter(EKF) with bearing only measurement, the proposed scheme makes use of line-of-sight(LOS) rate to ensure the fast convergency at long-range. In this reason, the robust Kalman filter is considered to deal with LOS rate measurement error. The recursive linear structure of proposed filter is easy to implement and make it possible to reduce computational burdens. Moreover, it shows good estimation performance without specific guidance law such as oscillation proportional navigation guidance(OPNG).

• 제어로봇시스템학회:학술대회논문집
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• 2001.10a
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• pp.156.5-156
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• 2001

Stabilized tracking platform in a missile consisting of a flat planar antenna, pitch/yaw gimbals, gear trains, and current controlled DC drive motors for pitch and yaw gimbal must have a capability to track a target as an inertial sensor in the presence of missile body motion such as maneuvering and vibration. Because of this reason, tracking a target from dynamic platform requires a servo architecture that includes a outer tracking loop(position loop) and inner rate loop that stabilizes the line of sight(LOS). This paper presents a gimbaled platform model including nonlinear phenomena due to viscous and Coulomb friction based on experimental data and torque equilibrium equation, the design concept for the inner tacholoop having P controller structure ...

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.18 no.5
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• pp.496-502
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• 2008

In this study, supersonic and hypersonic flutter characteristics have been analyzed for the various typical section shapes of missile fin configurations. Nonlinear flutter analyses are conducted considering the effect of moving shock waves. Computational fluid dynamic method is applied to accurately predict unsteady aerodynamic loads due to structural motions for the solution of aeroelastic governing equations. Commonly used typical section shapes of supersonic and hypersonic launch vehicles are considered in the present numerical study. Detailed flutter responses for four different typical section models are presented and the flutter characteristics are physically investigated.