• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1992년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 19-21 Oct. 1992
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• pp.165-170
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• 1992

In this paper, the Hardware-In-The-Loop Simulation(HILS) of missile systems are studied. The HILS is an effective performance evaluation technique that bridges the simulation fidelity gap between analytic all-digital simulations and actual flight tests of missile systems. The HILS may be required to perform system integration tests, performance evaluation at system or subsystem level. Major elements of this HILS facility will include the flight table, simulation computers, I/O computer and peripheral equipments. HILS of missile systems typically involve computer modeling of flight dynamics coupled with a hardware guidance and control(G/C) systems. This paper describes a real time performance evaluation technique of a G/C system, Development of a HILS for a Autopilot of SAM G/C will be used as an example.

• 한국산학기술학회논문지
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• 제9권6호
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• pp.1585-1591
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• 2008

현재 움직이는 물체의 운동을 제어하기 위해 하중이라는 개념의 사용이 시도되고 있다. 하중이라는 제어 개념으로 불확실성으로 인한 비선형성을 포함한 시스템에서 신뢰성 있는 제어값을 찾기 위해 MIN 설계 방법이 제안되었다. 이러한 MIN설계 방법에서는 기존의 선형화 방법에 의한 상태방정식에서의 제어값을 찾는 문제와 달리 비선형하중 모델에서 직접 제어 값을 찾는 방식을 보이고 있다. 본 논문에서는 미사일 하중 운동역학과 유도 기하학의 비선형 역학을 고려한 하중 제어값을 찾는다. 즉 시선각 또는 미사일의 받음각 변화에 따른 진행방향에 대한 미사일의 속도 조건을 만족하기 위한 제어값과 표적을 따라가기 위한 선회 각도을 위한 제어값을 구한다. 즉 본 논문에서는 미사일 시스템과 추적 동역학에서 하중 제어값을 구해본다. 이렇게 구해진 하중 제어값으로 유도 제어 법칙을 비선형 시스템에서 직접 쉽게 구할 수 있음을 확인해 보았다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.359-362
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• 1996

The guidance system which uses the line-of-sight(LOS) rate to guide the missile towards its target has been used to the conventional differential game, such as the pursuer-evader game. Proportional navigation guidance and its derivatives have been shown to be an effective LOS rate guidance system. In this paper, we have used the genetic algorithm to construct the guidance system for the pursuer-evader type differential game. Also we have proposed the prediction model to obtain the informations about the intention of future actions of the pursuer and the evader.

• 한국군사과학기술학회지
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• 제19권1호
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• pp.43-49
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• 2016

This paper addresses the problem of the software update or upgrade of embedded equipments on a missile assembly with booster. Because the embedded equipments are assembled delicately and closely one another with various communication and power cables, they should be very carefully disassembled to directly upgrade the software of a certain embedded equipment. This may cause not only the costs for disassembly and reassembly but also additional tests to verify the completeness of the reassembled missile as a missile assembly with booster. This paper presents an indirect data transfer technique based on MIL-STD-1553B through Guidance Control Unit to easily upgrade the software of other equipments without any additional costs caused by disassembly and reassembly. The presented technique was successfully applied to the software upgrade of various equipments on real missile assembly with booster.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1990년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 26-27 Oct. 1990
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• pp.469-474
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• 1990

The implementation of modern guidance law derived from optimal control theory requires accurate current states of target, for example, position, velocity and acceleration etc. But there is no sensors that measure the target states directly. So they are estimated from measurable data. For atmospheric missile engagement, direct application of the modern guidance laws may result In deterioration of Intercept performance because of poor observability associated with angles only-measurements by passive seeker and homing geometry. In this paper, a trajectory modulation method called "adaptive Intermittent maneuvers" is added to the modern guidance law, so the observability is enhanced and, consequently, improved the intercept performance. The estimation algorithm called "modified gain pseudo-measurement filter" is used for tracking filter. It is assumed that the passive seeker measure the angles between line of sight and Inertial frame. The Monte-Carlo simulation for realistic air-to-air Intercept scenario are conducted to demonstrate the effectiveness of intermittent maneuvers.ermittent maneuvers.

• Journal of the Korean Society for Industrial and Applied Mathematics
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• 제19권3호
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• pp.253-270
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• 2015

Two major simultaneous attack strategies have been introduced, as one of cooperative attack of multiple missiles. One strategy is an undesignated time attack, in which the missiles communicate among themselves to synchronize the arrival times by reducing the mutual differences of times-to-go of multiple missiles during the homing. The other is a designated time attack, in which a common impact time is commanded to all members in advance, and thereafter each missile tries to home on the target on time independently. For this individual homing, Impact-Time-Control Guidance (ITCG) law is required. After introducing cooperative proportional navigation (CPN) for the first strategy, this article presents a new closed-form ITCG guidance solution for the second strategy. It is based on the linear formulation, employing base trajectories driven by PNG with various navigation constants. Nonlinear simulation of several engagement situations demonstrates the performance and feasibility of the proposed ITCG law.

• 한국항공우주학회지
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• 제45권7호
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• pp.610-617
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• 2017

최근의 무기체계에서는 효율적으로 적진을 탐색, 타격할 수 있는 저가의 소형 유도무기 개발이 많이 요구되고 있다. 이처럼 저가의 소형 드론형 무기의 제어를 위해서는 무선 인터페이스, 자세제어 위치탐색 타깃 탐색들을 위한 다양한 센서들과 고성능 카메라, 그리고 이를 실시간으로 통합하여 처리할 수 있는 고성능의 프로세싱 능력들을 갖춘 통합 전자장치가 필수적이다. 본 논문에서는 이를 위한 솔루션으로 안드로이드 스마트폰을 통합 전자 제어장치로 제안하고, 유도조종 알고리듬을 수행할 어플리케이션을 구현한다. 제안된 어플리케이션을 실제 스마트폰에 올려 비행모의 시뮬레이션을 통해 성능을 분석한다.

• 한국군사과학기술학회지
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• 제13권4호
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• pp.520-527
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• 2010

The kill probability of a missile depends on guidance error, warhead performance, and etc. In this paper, we analyzed the kill probability of anti-tank missile in a new approach. Under the condition that the missile hit the target, we studied the effect of angle of attack and impact angle. High impact angle increase the probability that the missile hits the upper armour which is relatively weaker, while high angle of attack at the impact instant decreases the effectiveness of the jet induced by the warhead. We proposed a way to increase the capability of penetration by analyzing the interrelation between impact angle and angle of attack.

• 한국군사과학기술학회지
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• 제13권6호
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• pp.1019-1025
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• 2010

This paper describes on methods in test and evaluation of the guided rocket munitions of the domestic new generation multiple launcher rocket system. We modified and refer to the present model of air-to-air missile(AAM) and surface-to-air missile(SAM). Also we suggested a method of surface-to-surface missile(SSM) based on the characteristics of the guided rocket in test and evaluation(T&E). According to this study, the suggested activity of T&E should be observed methods compatible with each item on the established model. Therefore, we expect that the proposed research material will be a good guide to the study of a surface-to-surface missile(SSM) installed GPS/INS integration navigation guidance & control systems in the future.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2002년도 ICCAS
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• pp.82.2-82
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• 2002

The new guidance law for a missile with the varying velocity after the rocket motor burned out is presented. This guidance is mechanized by combining the proportional navigation and the pure pursuit navigation. Some simulations are performed and then the simulation results show that the guidance law presented is effective even if the vehicle speed decreases significantly and has higher off-boresight ability than the proportional navigation.