• Journal of the Korean Society for Precision Engineering
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• v.23 no.4 s.181
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• pp.67-74
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• 2006

The paper presents gravitational effect on eigenvalue branches and flutter modes of a vertical cantilevered pipe conveying fluid. The eigenvalue branches and modes associated with flutter of cantilevered pipes conveying fluid are fully investigated. Governing equations of motion are derived by extended Hamilton's principle, and the related numerical solutions are sought by Galerkin's method. Root locus diagrams are plotted for different values of mass ratios of the pipe, and the order of branch in root locus diagrams is defined. The flutter modes of the pipe at the critical flow velocities are drawn at every one of the twelfth period. The transference of flutter-type instability from one eigenvalue branches to another is investigated thoroughly.

• 제어로봇시스템학회:학술대회논문집
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• 2000.10a
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• pp.503-503
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• 2000

This paper presents the design technique of the using of PlI, PID and PIDA Controllers in order to achieve the desired transient and steady state responses. The merit of the proposed technique is any tuning method is not being required. By using of the forward controller, so that all given specifications to be designed can be obtained via the root locus approach.

• Journal of the Korean Society for Precision Engineering
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• v.18 no.8
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• pp.96-106
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• 2001

As the drilling depth increases, the cutting torque increases and fluctuates, which can lead to the machine tool vibration, severe tool wear, and catastrophic tool breakage. Hence, cutting torque control is very important to improve productivity in drilling. In this paper, a PID controller was designed to control the drilling torque. The plant including the feed drive system, cutting process and spindle drive system was modeled for controller design. The Ziegler-Nichols method was used to determine the controller gain and control action times and the root locus plot was used to tune the controller gain for a certain cutting condition. Also, suggested was a simple method to obtain the tuned controller gain for an arbitrary cutting condition not using the Ziegler-Nichols method and the root locus plot. The performance of the designed controller and the effect of controller gain tuning were verified from experiments.

• Proceedings of the KIEE Conference
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• 2006.04a
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• pp.249-251
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• 2006

In this study, a systematic and effective tuning method of the actuator control parameters of the control loading system for aircraft based on control theory is presented. Firstly, to raise the time response of the system, the proportional gain and the integral gain of the velocity control loop is maximized within the range where vibration and noise does not occur. And then the position control loop is composed by getting the transfer function of the control loading system including the velocity control loop. With the root locus of the composed position control loop, the proportional gain of the position control loop that keeps stable transient state and leads good time response of the system is predicted, and the simulations are performed by using the predicted gain. Lastly, the actuator control parameters of actual control loading system are set to the previously obtained gain values. And the experiments to actuate the control loading system are executed. It shows that the tuning method of the actuator control parameter proposed in this study is applied to actual control loading system very well by comparing the results of the experiments with those of the simulations.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1996.04a
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• pp.330-335
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• 1996

The well-conditioned observer design method is extended for two-output systems where observer gains are not determined uniquely with respect to the desired observer poles. Similar to the previous results, this design method makes off-diagonal elements of the observer upper-left submatrix skew-symmetric and simulataneously, places the eigenvalues of the observer matrix widely separated by selecting upper two rows of the observer gain. The proposed design method is evaluated in a spindle-drive example where the load speed is estimated based on motor speed and the armature current.

• Proceedings of the KIEE Conference
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• 1999.11b
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• pp.251-254
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• 1999

This paper presents the basic tuning method for PSS control parameters. This method includes the phase compensation and root-locus based gain tuning for one machine with infinite bus system. At the tuning condition and least stable condition, the effect of gain tuning is also discussed.

• 제어로봇시스템학회:학술대회논문집
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• 1990.10a
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• pp.485-492
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• 1990

This paper propose a optimal design method for robust notion controllers of under-water vehicles using the combined technique between classical and modern theories. The proposed method is presented which utilizes classical control methods to obtain a good robustness and modern control methods to set optimal gains. LQ, SVD, multivariable frequency analysis and Bode-Root Locus (BRL) plot are used.

• 제어로봇시스템학회:학술대회논문집
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• 1990.10a
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• pp.475-480
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• 1990

A design of aeroload simulator is proposed which is used for the dynamic test of guided missile servoactuation system. Since the simulator is linked to the servoactuation system, it is a two-input one-output system. The mathematical model of the aeroload simulator is derived and the root-locus method is applied to design compensator to improve the stability, response speed and accuracy of the system. Computer simulations are done to verify the goodness of the system design.

• International Journal of Control, Automation, and Systems
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• v.5 no.2
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• pp.208-211
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• 2007

In a recently proposed method of model reduction for discrete interval systems, the denominator polynomial of a reduced model is computed by applying interval arithmetic to dominant poles of the original system. However, the denominator polynomial obtained via interval arithmetic usually has poles with larger intervals than desired ones. Hence an unstable polynomial can be derived from the stable polynomial. In this paper a simple technique is presented to partially overcome such a stability problem by accurately preserving desired real dominant poles.

• Journal of Industrial Technology
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• v.15
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• pp.195-202
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• 1995

In this paper, we analyze the effects of scaling factors on the performance of a fuzzy controller. The quantitative relation between input and output variables of a fuzzy controller is obtained by using a quasi-linear fuzzy model. And an approximate transfer function of a fuzzy controller is derived from the comparison of fuzzy controller with the conventional PID controller. Then we analyze the effects of scaling factor using this approximate transfer function and root locus method.