• 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.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1992년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 19-21 Oct. 1992
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• pp.572-577
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• 1992

In this paper, the optimal homing guidance problem is investigated for the general missile/target models described in the state-space. The closed-form solution of the optimal guidance law derived, and its asymptotic properties are studied as the time-to-go goes to infinity or zero. Futhermore, several approximate solutions of the optimal guidance law are suggested for real-time applications.

• 한국군사과학기술학회지
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• 제11권4호
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• pp.29-35
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• 2008

In this paper, a new guidance law to reduce sensitivity to the initial heading errors is proposed. In order for shaping the input weights over the flight, we introduce the distribution functions expressed in terms of time-to-go and its inverse term. By applying the optimal control theory with the synthesized weights, the homing guidance law is derived. Also the characteristics of the proposed law are examined. Various computer simulations show the good performance of the proposed guidance.

• 한국항공우주학회지
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• 제35권11호
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• pp.1006-1012
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• 2007

본 논문에서는 호밍 유도 비행체의 종말에서의 충돌각 구속조건을 고려한 준 최적 호밍 유도법칙을 제안한다. 기존의 일반 LQ 최적 제어와는 달리 추가적인 구속조건을 위해 여분의 자유도를 확보하도록 보조 루프를 도입하고, 도입된 부가항을 고려하여 Schwartz 부등식으로부터 최적 제어 입력을 설계한다. 비행체에 인가되는 전체 유도 명령은 최적해와 더불어 부가항을 합성한 준최적 유도법칙의 구조를 갖는다. 또한 제안한 유도법칙의 여러 가지 특성을 고찰하고 기존의 유도법칙들과 비교 연구도 수행한다. 다양한 시뮬레이션 결과를 통하여 제안한 유도법칙의 타당성을 보여준다.

• 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.

• International Journal of Aeronautical and Space Sciences
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• 제18권4호
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• pp.709-718
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• 2017

This paper proposes the guidance laws for an agile turn of air-to-air missiles during the initial boost phase. Optimal solution for the agile turn is obtained based on the optimal control theory with a simplified missile dynamic model. Angle-of-attack command generating methods for completion of agile turn are then proposed from the optimal solution. Collision triangle condition for non-maneuvering target is reviewed and implemented for update of terminal condition for the agile turn. The performance of the proposed method is compared with an existing homing guidance law and the minimum-time optimal solution through simulations under various initial engagement scenarios. Simulation results verify that transition to homing phase after boost phase with the proposed method is more effective than direct usage of the homing guidance law.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.482-485
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• 1996

We design a homing guidance law based on the proportional navigation for the fast-rolling, single-axis control missiles and analyse the misdistance of the designed guidance system. The guidance law includes a compensation scheme which compensates for the phase-shift between the commanded and achieved acceleration which is peculiar to the fast rolling airframe with single-axis control. In the error analysis of the guidance system, we calculate the misdistance with respect to the target maneuver on the 3-dimensional space via direct simulations. Also, we conduct adjoint simulation on the 2-dimensional plane in case that phase-shift is perfectly compensated. Finally we approximate the linear time-varying dynamics of the missile with autopilot to a linear time-invarient system, and as a result we can find the misdistance as a closed-form.

• 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 2001년도 ICCAS
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• pp.64.3-64
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• 2001

In this paper, an estimation scheme with the IMM algorithm to estimate radome slope and target states is used to reduce the radome induced miss distance effectively in spatial active homing engagements of an anti-air missile. The filter algorithm in conjunction with proportional navigation guidance is tested by a series of simulation runs.