• 한국항공우주학회지
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• 제45권11호
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• pp.967-974
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• 2017

반작용휠은 저속구간에서 마찰로 인해서 비선형 토크 응답을 보인다. 따라서 이 구간에서는 위성의 정밀한 자세제어를 달성하기 어렵다. 기존 연구들은 마찰력 보상이나 디더명령을 인가하는 방법을 사용하여 본 문제를 해결하려 하였다. 하지만 마찰력 모델링의 어려움이나 휠속도의 빈번한 영점 교차 때문에, 이러한 방법을 실제 위성 자세제어에 적용하기에는 어려움이 있다. 이를 해결하기 위해서, 자세오차에 따라서 자세제어기의 이득값을 조절하는 방법을 제안한다.

• 문화기술의 융합
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• 제5권3호
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• pp.257-262
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• 2019

최근 드론 같은 무인 이동체에 대한 관심과 일상생활에 활용이 늘어나면서 많은 다양한 분야에서 이를 이용하는 응용 사례가 급속도로 확산되고 있다. 하지만 이러한 무인 이동체는 쉽게 외부 환경 요인으로 인한 균형 이탈이나 추락 등의 사고로 이어질 수 있는 많은 위험 요인을 내포하고 있다. 이러한 무인 이동체의 안전한 운용을 위하여 안정적인 자세 제어 알고리즘은 매우 중요한 부분을 차지하고 있으며 현재 널리 사용되고 있는 PID 제어 알고리즘은 거의 완벽한 단계의 자세 제어 기술을 선보이고 있다. 본 연구에서는 기존의 자세 제어 방법과는 달리 보다 외부 환경적인 요인으로 부터 안정적이고 지속적인 자세 제어를 할 수 있는 퍼지 로직을 기반으로 하는 스마트 자세 제어 알고리즘을 제안하고 모의실험을 통하여 기존의 방법과 그 성능을 비교 분석하고자 한다.

• 임상간호연구
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• 제15권1호
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• pp.123-132
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• 2009

Purpose: This study was conducted to identify the effects of provision of a cancer pain guideline and education for patients with cancer and their families on their knowledge and attitude toward cancer pain control. Method: A nonequivalent control group pre-post test design was used. The participants were selected according to a selection criteria from patients and their families on the medical ward at K university hospital in D city. Both the experimental group for patients with cancer and control group consisted of 16 patients and their families. Results: The first hypothesis, which assumed that there was a difference between the patients in the experimental group and the control group on knowledge (t=-20.006, p=.000) and attitude (t=-13.492, p=.000), was accepted. The second hypothesis, which assumed there was a difference between families in the experimental group and the control group on knowledge (t=-16.087, p=.000) and attitude (t=-10.262, p=.000), was supported. Conclusion: Education for cancer related pain control with a patient guideline had a positive effect on knowledge and attitude of patients with cancer patients and their families suggesting that there is a need to developed this type of guidelines.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.62.3-62
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• 2001

The predictive control is one of the nonlinear three-axis rotation methods. The desired trace of a satellite is pre-determined, and the control inputs are designed so that the satellite follows the ´predictive´ trace. The predictive control has been adapted to the research for the three-axis attitude control. In that case, the control variables are the quaternion represented the angular rates and attitude angles of the body about the three-axes. The objective of this paper is to propose to design a predictive controller for the three-axis attitude control under external disturbances. In order to do that, this paper proposes how to construct a predictive control law including disturbances and to discern them. The basic algorithm of the existent predictive control is partially modified, and the presumption and modeling of disturbances are performed ...

• International Journal of Aeronautical and Space Sciences
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• 제8권1호
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• pp.21-31
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• 2007

Relaxed Static Stability (RSS) concept has been applied to improve aerodynamic performance of modern version supersonic jet fighter aircraft. The T-50 advanced supersonic trainer employs the RSS concept in order to improve the aerodynamic performance. And the flight control system stabilizes the unstable aircraft and provides adequate handling qualities. The T-50 longitudinal control laws employ a proportional-plus-integral type controller based on a dynamic inversion method. The longitudinal dynamic modes consist of short period with high frequency and phugoid mode with low frequency. The design goal of longitudinal control law is optimization of short period damping ratio and frequency using Lower Order Equivalent System (LOES) complying the requirement of MIL-F-8785C. This paper addresses phugoid mode characteristics such as damping ratio and natural frequency that is affected by the nonlinear control laws such as angle of attack limiter, auto pitch attitude command system and autopilot of pitch attitude hold.

• 제어로봇시스템학회논문지
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• 제12권3호
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• pp.300-306
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• 2006

In this paper an error analysis of 3-dimensional GNSS attitude determination system is given. The attitude error covariance matrix is derived and analyzed. It implies that attitude errors are affected by the baseline length and configuration, the satellites numbers and geometry, receiver measurement noises and the nominal attitude of the vehicle. By defining Euler Angle Dilution Of Precision (EADOP) which is analogous to GDOP, roll, pitch and yaw errors can be efficiently analyzed. However the expression of the attitude error is too complex to get some intuitions. Therefore with a commonly adopted assumption, new expressions for attitude error are derived. The formulas are easy to compute and represent the attitude error as a function of the nominal attitude of a vehicle, the baseline configuration and the receiver noise. Using the formula, the accuracy of the attitude can be analytically predicted without the computer simulations. Applications to some widely used configurations reveal the effectiveness of the proposed method.

• 대한전기학회논문지:시스템및제어부문D
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• 제54권2호
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• pp.61-68
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• 2005

This paper is concerned with attitude control of 2 rotor 1 DOF aerial vehicle. The proposed controller consists of two parts: the attitude estimation filter part and PID controller part. For attitude estimation, performance of 3 different filters (complementary filters, Kalman filter, indirect Kalman filters) are tested and compared. For the PID controller, characteristic ratio assignment methods are used to assign PID coefficients. Through experiments, it is shown that attitude of the vehicle successfully follows the step command.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1995년도 Proceedings of the Korea Automation Control Conference, 10th (KACC); Seoul, Korea; 23-25 Oct. 1995
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• pp.150-153
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• 1995

In this paper the attitude control system is developed for longitudinal motion of Foil-Catamaran in regular waves with all-movable foils which attached to fore and after part of the ship and verified the system by theoretical calculation and model-tests. The linearized equations of motion of the ship is employed to apply the linear control theories, the PID control and the LQR. The strip method was used to calculate hydrodynamic coefficients and wave exciting forces of the demi hull, and unsteady hydrodynamic forces of foils are considered by using the result of Wu(1972). About 40-60% of motions is reduced in experiments. The control system described in this paper is able to extended to 6-DOF motions or control in irregular wave with trivial modification. And it is applicable to hull shape development for better seakeeping performance and to determine the size and the position of hydrofoils for the attitude control.

• International Journal of Aeronautical and Space Sciences
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• 제15권2호
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• pp.190-198
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• 2014

The pyramidal reaction wheel arrangement is one of the configurations that can be used in attitude control simulators for evaluation of attitude control performance in satellites. In this arrangement, the wheels are oriented in a pyramidal configuration with a tilt angle. In this paper, a study of pyramidal reaction wheel arrangement is carried out in order to find the optimum tilt angle that minimizes total power consumption of the system. The attitude control system is analyzed and the pyramidal configuration is implemented in numerical simulation. Optimization is carried out by using an iterative process and the optimum tilt angle that provides minimum system power consumption is obtained. Simulation results show that the system requires the least power by using optimum tilt angle in reaction wheels arrangement.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2007년도 한국우주과학회보 제16권2호
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• pp.135-138
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• 2007

The present work is to estimate the stability region of the State-Dependent Riccati Equation (SDRE) controlled system, which is used for a decentralized coordinated attitude control in satellite formation flying. In this research, currently emerging methods which estimate region of attraction for the SDRE controllers are introduced and the methods are applied to attitude control systems. The results guarantee the stability of the given decentralized coordinated attitude control system in satellite formation flying.