• Journal of the Korean Institute of Intelligent Systems
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• v.16 no.2
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• pp.144-149
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• 2006

This paper deals with a balanced model reduction for uncertain nonlinear systems via T-S fuzzy approach. We define a generalized controllability/observability gramian and obtain a balanced state space model using generalized gramians which can be obtained from solutions of linear matrix inequalities. We present a balanced model reduction scheme by truncating not only state variables but also uncertain elements. An upper bound of the model reduction error will also be suggested. In order to demonstrate the efficacy of our method, a numerical example will be presented.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.6
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• pp.505-516
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• 2011

The concept of the IGC(Integrated Guidance and Control) has been introduced to overcome the performance limit of the SGC(Separated Guidance and Control) loop. A new type of IGC with impact angle constraint has been proposed in this paper. Angle of attack, pitch angle rate, pitch angle and line of sight angle are considered as state variables. A controllability analysis and equilibrium point analysis have been carried out to investigate the control characteristic of the prposed IGC. The LQR(Linear Quadratic Regulator) has been adopted for the control law and detailed explanations about the adoption has been provided. The performance comparison between the IGC and the SGC has been carried out. The result of numerical simulations shows that the IGC guarantees better guidance performance than the SGC when the agile maneuver is needed for a specific guidance geometry.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.17 no.1
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• pp.11-19
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• 1992

This paper proposes a reduced order method which reduces passband error by changing controllability and observability gramian based on weighted functions in the linear time invariant system. In the case that the 4-order model is the reduced to 3-order model in the low-pass filter, the QEI in the proposed method is improved to 6.15724 compared to 10.16464 in the balanced realization method and the sensitivity is improved to 5.45962 compared to 7.790568. The frequency property curves show that the proposed method is superior to the balanced realization method.

• Proceedings of the KIEE Conference
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• 2007.10a
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• pp.217-218
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• 2007

최근 개발된 비선형 자동조종 제어기를 사용하면 비행 환경에 무관하게 BTT 미사일의 입출력 동특성이 일정한 선형 시스템의 형대로 표현될 수 있다. 본 논문에서는 이와 같은 특성을 바탕으로 BTT 미사일이 목표물의 취약 지점을 정밀하게 요격할 수 있도록 자동조종장치 동역학의 시간 지연 효과를 고려하여 표적 충돌각을 최소화하는 최적 종말 유도 법칙을 설계하였다. 제안된 최적 종말 유도 법칙은 극좌표 변환을 사용하지 않기 때문에 가제어성을 보장하며, 가속도 편향값을 사용하지 않기 때문에 기존의 유도 법칙에 비하여 미사일의 기동성을 향상시킬 수 있는 장점을 갖는다.