• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.12
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• pp.1152-1162
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• 2008

This paper deals with the State-Dependent Riccati Equation (SDRE) technique for the design of helicopter nonlinear flight controllers. Since the SDRE controller requires a linear system-like structure for nonlinear motion equations, a state-dependent coefficient (SDC) factorization technique is developed in order to derive the conforming structure from a general nonlinear helicopter dynamic model. Also on-line numerical methods of solving the algebraic Riccati equation are investigated to improve the numerical efficiency in designing the SDRE controllers. The proposed method is applied to trajectory tracking problems of the helicopter and computational tips for a real time application are proposed using a high fidelity rotorcraft mathematical model.

• Journal of the Korean Operations Research and Management Science Society
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• v.9 no.2
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• pp.28-33
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• 1984

In this paper some procedures are given whereby an analytic solution may be found for the Riccati differential equation and algebraic Riccati equation in optimal control theory. Some iterative techniques for solving these equations are presented. Rate of convergence and initialization of the iterative processes are discussed.

• Proceedings of the KIEE Conference
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• 1992.07a
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• pp.296-298
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• 1992

Presented in this paper is a generalized norm bound for the continuous and discrete algebraic Riccati equations. The generalized norm bound provides a lower bound of the Riccati solutions specified by any kind of submultiplicative matrix norms including the spectral, Frobenius and $\ell_1$ norms.

• 제어로봇시스템학회:학술대회논문집
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• 1986.10a
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• pp.68-72
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• 1986

Upper bounds of the perturbed Co-semigroups of the infinite dimensional systems are investigated by using the algebraic Riccati equation(ARE). In the case that the solution P of the ARE is strictly positive, the perturbed semigroups are uniformly bounded. A sufficient condition for the solution P to be strictly positive is provided. The uniform boundedness plays an important role in extending approximately weak stability to weak stability on th whole space. Exponential Stability of the perturbed semigroups is studied by using the Young's inequlity. Some further discussions on the uniform boundedness of the perturbed semigroups are given.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.10
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• pp.816-822
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• 2014

The estimation of the angular rate of a satellite has been discussed. A nonlinear observer has been proposed based on the state-dependent Riccati equation method. A sufficient stability condition for the convergence of estimation error has been presented. This condition is related to a state-dependent algebraic Riccati equation. It has been derived by transforming nonlinear error dynamics into a Lipschitz nonlinearity. An observer gain is obtained from this condition. Numerical simulations are presented to verify the proposed method.

• Journal of the Korean Institute of Telematics and Electronics
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• v.16 no.5
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• pp.18-26
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• 1979

This paper extends some well-known system theories on algebraic matrix Lyapunov and Riccati equations. These extended results contain two point boundary conditions in matrix differential equations and include conventional results as special cases. Necessary and sufficient conditions are derived under which linear systems are stabilizable with feedback gains derived from periodic two-point boundary matrix differential equations. An iterative computation method for two-point boundary differential Riccati equations is given with an initial guess method. The results in this paper are related to periodic feedback controls and also to the quadratic cost problem with a discrete state penalty.

• Bulletin of the Korean Space Science Society
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• 2011.04a
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• pp.24.3-24.3
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• 2011

우주발사체를 이용하여 인공위성을 궤도에 올리는 문제에서 가장 중요시해야 할 부분은 임무의 성공, 즉 정밀한 궤도 진입이다. 이것이 만족되어졌을 때, 비용의 최소화 또한 설계 시 중요한 고려사항이 된다. 이 두 가지 문제를 동시에 해결하기 위해선 최적 제어 전략이 필요한데, 통상적으로 이 과정은 발사 전에 최적화 기법 등을 이용하여 계산되고 검증된다. 그러나 기존의 최적화 기법은 대부분 선형 시스템에 적합한 기법들 이고, 우주발사체와 같이 매우 복잡하고 강한 비선형을 가진 운동방정식을 최적화 하려면 많은 계산이 소요된다. 계산 소모 시간을 줄이기 위해서는 선형화 등의 기법이 사용되는데, 그러한 경우 최적 해에 대한 신뢰도가 낮아질 수밖에 없다. 이 논문에서는 그러한 문제를 해결하기 위해 최근 활발히 연구되고 있는 비선형 최적화 기법인 상태 의존 Riccati 방정식 기법 (SDRE)을 이용하여 인공위성을 주어진 궤도에 진입시키는 우주발사체의 최적궤도를 계산하였다. 또한 Hamiltonian 을 이용하여 산출된 궤도의 최적성을 보이고, 목표한 궤도와의 비교를 통해 제어기의 정밀성을 확인하였다.

• 전자공학회논문지 IE
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• v.44 no.4
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• pp.26-29
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• 2007

In this paper, we use Lyapunov equations and functions to consider the linear systems with perturbed system matrices. And we consider that what choice of Lyapunov function V would allow the largest perturbation and still guarantee that V is negative definite. We find that this is determined by testing for the existence of solutions to a related quadratic equation with matrix coefficients and unknowns the matrix Riccati equation.

• Proceedings of the KIEE Conference
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• 1986.07a
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• pp.235-237
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• 1986

• Bulletin of the Korean Space Science Society
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• 2006.10a
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• pp.74-74
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• 2006