• Journal of Advanced Marine Engineering and Technology
• /
• 제25권2호
• /
• pp.351-356
• /
• 2001

In this paper, a general one-loop control system was assumed as a model system which has a time-delay element connected with a first order-lag element in series. After the corresponding parameter set causing stability limit condition for the model system was obtained by mathematical procedures, their loci on the parameter space was taken according of frequency change,. The parameter set loci of stability limit showed a specific pattern, and particularly the curves on the Kp-Ti parameter space were able to generalized in the form of an exponential formula. These properties were also compared with the results taken from experimental procedures by Nyquist response method and Ziegler & Nichols method on the time domain, and both results were confirmed to be nearly same.

• 대한수학회지
• /
• 제39권6호
• /
• pp.963-973
• /
• 2002

We study torsion phenomena in the integral cohomology of finite if-spaces X through the Eilenberg-Moore spectral sequence converging to H＊($\Omega$X; Z$_{p}$). We also investigate how the difference between the Z$_{p}$-filtration length f$_{p}$(X) and the Z$_{p}$-cup length c$_{p}$(X) on a simply connected finite H-space X is reflected in the Eilenberg-Moore spectral sequence converging to H＊($\Omega$X;Z$_{p}$). Finally we get the following result: Let p be an odd prime and X an n-connected finite H-space with dim QH＊ (X;Z$_{p}$) $\leq$ m. Then H＊(X;Z) is p-torsion free if (equation omitted).tion omitted).

• International Journal of Aeronautical and Space Sciences
• /
• 제15권3호
• /
• pp.281-292
• /
• 2014

We propose a novel cooperative guidance law design method based on the finite time disturbance observer (FTDO) for multiple near space interceptors (NSIs) with impact time control. Initially, we construct a cooperative guidance model with head pursuit, and employ the FTDO to estimate the system disturbance caused by target maneuvering. We subsequently separate the cooperative guidance process into two stages, and develop the normal acceleration command based on the super-twisting algorithm (STA) and disturbance estimated value, to ensure the convergence of the relative distance. Then, we also design the acceleration command along the line-of-sight (LOS), based on the nonsingular fast terminal sliding mode (NFTSM) control, to ensure that all the NSIs simultaneously hit the target. Furthermore, we prove the stability of the closed-loop guidance system, based on the Lyapunov theory. Finally, our simulation results of a three-to-one interception scenario show that the proposed cooperative guidance scheme makes all the NSIs hit the target at the same time.

• 한국마린엔지니어링학회:학술대회논문집
• /
• 한국마린엔지니어링학회 2000년도 추계학술대회 논문집(Proceeding of the KOSME 2000 Autumn Annual Meeting)
• /
• pp.135-142
• /
• 2000

The adjusting parameter set which enable control systems to locate on stability limit can be derived from theoretical or trial methods for an existing real system. The data from the results are much available to keep a system in the Proper stability condition even to site engineers who are inexperienced in the control system. In this paper, a general one loop control system was adopted for a model system the process of which was assumed to consist of a time-delay element and a first order-lag element in series. After obtaining the corresponding parameter set for the model system by mathematical procedures, their loci on the parameter space was taken according to frequency change. The parameter set loci of stability limit showed unique pattern, and particularity , the curves on the Kg-Ti parameter space were able to be generalized in the form of, an unique exponential formula. These properties were also compared with the results taken from experimental procedures by Nyquist response method and Ziegler & Nichols method on the time domain, and both results were confirmed to be nearly same.

• Korean Journal of Mathematics
• /
• 제18권2호
• /
• pp.175-183
• /
• 2010

The classical group completion theorem states that under a certain condition the homology of ${\Omega}BM$ is computed by inverting ${\pi}_0M$ in the homology of M. McDuff and Segal extended this theorem in terms of homology fibration. Recently, more general group completion theorem for simplicial spaces was developed. In this paper, we construct a symmetric monoidal 2-category ${\mathcal{A}}$. The 1-morphisms of ${\mathcal{A}}$ are generated by three atomic 2-dimensional CW-complexes and the set of 2-morphisms is given by the group of path components of the space of homotopy equivalences of 1-morphisms. The main part of the paper is to compute the homotopy type of the group completion of the classifying space of ${\mathcal{A}}$, which is shown to be homotopy equivalent to ${\mathbb{Z}}{\times}BAut^+_{\infty}$.

• 천문학회보
• /
• 제36권2호
• /
• pp.89.2-89.2
• /
• 2011

The geometry of an MC (magnetic cloud) in the interplanetary space can be estimated by the magnetic flux rope model. But the single point observation in the interplanetary space near the Earth is scanty to comprehend the global configuration of MC because the MC is considered a huge loop extending from the Sun with both legs rooted on the Sun. If the MC is observed at two different locations sufficiently far away from each other, it may provide the global configuration of the MC. In this study, we model the MC which is observed two different locations using a simple straight cylinder model. The MC model fit parameters are the flux rope axis orientation (${\Theta}$, ${\phi}$), the intensity of the magnetic field at the flux rope axis ($B_0$), the radius of the MC ($R_0$), and the impact parameter (p), etc. With the MC model fit parameters we look into the difference between two observed MC geometries and also calculate the magnetic flux and helicity of the MC.

• Journal of Advanced Marine Engineering and Technology
• /
• 제24권4호
• /
• pp.470-477
• /
• 2000

The states of control loops in existing actual systems are changed according to time varying conditions of controllest process and other system components. Adjusting control parameters properly at site which is performed generally by Ziegler & Nichols mthod is important for safe and efficient operation, but the method may require much time to adjust and not easy to inexperienced engineers. This study is aimed to propose more handy method to adjust control parameters by plotting operating conditions on the space of adjusting parameters. One loop of model control system without perturbation condition has been adopted and its stability limit was plotted on the coordinates of Gain and Integral time which was acquired after analyzing Nyquist diagrams and time domain responses. The result showed that the sets of adjusting parameters according to critical stability and proper stability could be acquired reasonably through both responses and the curves on parameter space revealed available patterns for the purpose of easy maintenance of control characteristics.

• ETRI Journal
• /
• 제45권2호
• /
• pp.203-212
• /
• 2023

In this study, we developed a co-located and space-shared multiple-input multiple-output (MIMO) antenna module with a modular design and high integration level. The proposed antenna pair includes a half-wavelength loop antenna and a dipole-type antenna printed on the front and back sides of a compact modular board. Owing to their modal orthogonality, these two independent antenna elements are highly self-isolated and free of additional decoupling components, even though they are assembled at the same location and within the same space. Thus, the proposed antenna is attractive in 5G MIMO systems. Furthermore, the proposed co-located and space-shared MIMO antenna module was employed in a 5G smartphone to verify their radiation and diversity performances. A 12 × 12 MIMO antenna system was simulated and fabricated using the proposed module. Based on the results, the proposed module can be employed in large-scale MIMO antenna systems for current and future terminal devices owing to its high integration, compactness, simple implementation, and inherent isolation.

• 한국항공우주학회지
• /
• 제45권10호
• /
• pp.863-871
• /
• 2017

헬리콥터 능동진동제어시스템에 널리 이용되는 LMS (least mean square) 알고리즘은 전방경로 (forward path) 전달함수와 에러 신호의 연산을 통해 제어 입력을 계산한다. 에러 신호가 정현파 형태일 경우, 기준 신호에 동기화된 진동수, 위상을 가지는 코사인과 사인 함수의 조합으로 표현될 수 있다. 제어 신호 또한 동일한 진동수를 가지게 되므로 제어 입력의 코사인, 사인 성분의 크기만 계산하고, 기준 신호의 진동수, 위상 정보를 활용하면 제어알고리즘은 단순하게 구현될 수 있다. 제어 입력 신호의 계산은 단순한 행렬 연산으로 구현되고, 제어 명령의 변화는 에러 센서의 주파수에 비해 느리기 때문에 제어알고리즘은 낮은 주파수에서 운용 가능하다. 에러 센서의 코사인, 사인 성분을 추출하는 신호처리 알고리즘을 시뮬링크 모델로 구현하고, PIL (processor in the loop) 모드 시뮬레이션을 통해 실시간 작동 성능을 평가하였다.

• 한국항공우주학회지
• /
• 제42권10호
• /
• pp.842-850
• /
• 2014

본 논문은 예측하지 못한 외부 환경 요소 변화로 인해 저하되는 비행 성능을 $L_1$ 적응 제어 기법으로 보상하는 궤적 추종 기법을 제안하였다. 제안된 궤적 추종 기법은 상대 거리를 이용하여 속도 명령을 생성하는 유도 법칙과 속도 명령을 추종하는 적응 제어 루프로 구성되어 있다. 경로 추종 성능을 향상시키기 위하여, 유도 법칙에서 생성한 속도 명령이 적응 제어기의 기준 입력이 되도록 설계하였다. 유도 법칙에서는 목표 궤적과 상대 거리와 그 변화량에 따른 가속도 명령이 생성되며, 이를 적분하여 속도 명령을 생성한다. $L_1$ 적응 제어 루프는 불확실성이 존재하는 환경에서 정밀한 경로 추종 성능을 보장한다. 제안된 경로 추종 시스템은 쿼드로터 항공기를 사용하여 수직 이착륙 및 이동 표적 추종과 같은 비행 실험으로 검증하였다.