• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.351-354
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• 1996

A new target adaptive guidance (TAG) algorithm is proposed to engage the aim point formed by adding a bias to the information from an infrared (IR) seeker for improving passive homing guidance effectiveness. The TAG algorithm utilizes an observability enhancing mid-course guidance algorithm to obtain convergent estimates of state variables involved particularly in range channel otherwise unavailable from passive sensors. Simulation results indicate that the TAG algorithm provides improved terminal effectiveness without computational complexities.

• 전기학회논문지
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• 제68권1호
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• pp.172-181
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• 2019

This paper deals with the problem of generating the energy optimal trajectory which is intended to enhance the target tracking performance of a passive homing missile. Noticing that the essence of passive target tracking is the range estimation problem, the target information gathered by passive measurements can be readily analyzed by introducing the range estimator designed in line-of-sight(LOS) frame. Moreover, for the linear filter structure of the suggested range estimator, the cost function associated with the target information is clearly expressed as a function of the line-of-sight rate. Based on this idea, the optimal missile trajectory maximizing the target information is obtained by solving the saddle point problem for an indefinite quadratic cost which consists of the target information and the energy. It is shown that, different from the previous heuristic approaches, the guidance command producing the optimal passive homing trajectory is produced by the modified proportional navigation guidance law whose navigation constant is determined by the weighting coefficient for target information cost.

• 한국항공우주학회지
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• 제42권1호
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• pp.20-28
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• 2014

본 논문에서는 비례항법 유도의 특성을 이용하여 수동 호밍 유도탄을 위해 탐색기의 lock-on 조건을 유지하면서 충돌각 제어를 할 수 있는 복합 유도법칙을 제안한다. 제안된 유도법칙은 두 가지 형태의 유도명령으로 구성되어 있다. 첫 번째 유도명령은 초기 유도단계에서 탐색기의 지향각(look angle)을 일정하게 유지키기 위한 것이고, 두 번째는 비례항법 유도명령으로서 특정 시선각 조건을 만족시킨 후 적용하여 원하는 충돌각으로 표적을 타격시키게 된다. 제안된 유도법칙은 유도탄의 탐색기 field-of-view(FOV)와 가속도 제한을 동시에 고려하고, 유도명령을 생성시키기 위해 표적 거리정보와 잔여비행시간(time-to-go) 정보가 필요하지 않기 때문에 수동 호밍 유도탄에 직접 적용할 수 있다. 다양한 비선형 시뮬레이션 결과를 통해서 제안된 유도법칙의 특성 및 성능 분석을 수행한다.

• 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.

• International Journal of Aeronautical and Space Sciences
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• 제18권4호
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• pp.757-766
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• 2017

For implementing the proportional navigation guidance law on passive homing missiles equipped with strapdown imaging infrared seekers, the line-of-sight angles and rates with respect to the inertial frame should be estimated by carefully handling the parasitic instability effect due to the seeker's latency. By introducing a new state vector representation along with the Pade approximation for compensating the time-delay of the seeker, this paper proposes a new guidance filter structure, stochastic dynamic models and measurement equations, in three-dimensional homing problem. Then, it derives the line-of-sight angle and rate estimator in general two-dimensional engagement by applying the extended Kalman filter to the proposed structure. The estimation performance and the characteristics of the proposed filter were evaluated via a series of numerical experiments.

• 한국해양공학회지
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• 제35권3호
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• pp.238-246
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• 2021

The survivability of a naval ship is the ability of the ship and its onboard systems to remain functional and continue a designated mission in man-made hostile environments. A passive decoy system is primarily used as a weapon system for improving the survivability of a naval ship. In this study, an engagement scenario-based simulation program was developed for decoy effectiveness assessments against an anti-ship missile (ASM), which tracks a target with sea-skimming and active radar homing. The program can explain the characteristics of a target ship, such as the radar cross section and evasive maneuvers, as well as the operational performance of the onboard decoy system, the guidance method of the ASM, and the engagement environment's wind speed and direction. This paper describes the theory and formulations, configuration, and user interface of the developed program. Numerical examples of a decoy effect assessment of a virtual naval ship against an ASM are presented.

• 한국시뮬레이션학회논문지
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• 제25권3호
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• pp.53-63
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• 2016

본 연구는 어뢰공격에 대비한 수상함의 생존율 향상을 위해 자항식 기만기와 부유식 기만기를 혼합적으로 적용한 시뮬레이션을 고려한다. 적의 공격어뢰는 수동 음향 추적 어뢰로써 어뢰의 표적 탐지거리 및 빔폭 내에서 수동 소나 방정식에 의해 신호이득을 계산하여 표적을 탐지, 추적하며, 수상함은 회피기동과 함께 자항식 및 부유식 기만기를 운용하여 어뢰공격에 대응하는 것으로 가정한다. 효과적인 기만기 혼합 운용을 위해 4가지의 기만기 운용 방안을 제안하며, 각각의 경우에 대하여 설정된 실험 환경 내에서 몬테카를로 시뮬레이션을 통한 수상함의 생존율에 대한 효과도 분석을 수행하였다. 또한 기만기의 속도 및 음원 준위, 함정의 어뢰 탐지거리, 어뢰의 표적 탐지거리를 변수로 설정하고 변수값의 변화에 따른 생존율의 변화 추이를 관찰하여 구성요소의 운용 성능에 대한 참고자료를 제시하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.245-248
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• 1996

This paper suggests a new concept for missile guidance control, called linearized common curvature guidance law that enhances the probability to kill a target. The proposed guidance system is composed of two switching modes; one for the midcourse guidance and the other for the terminal guidance, which is switched by a specified critical value (.epsilon.). And the system and the commands are formulated and its simulations are provided in comparison with the conventional commanded line of sight guidance algorithm. Miss distance and angle of attack are denoted as performance of parameters. This new concept, common curvature guidance algorithm, revises the navigation guidance and accompanies, various considerations.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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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).