• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.56-64
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• 2004

In this research, design results of computer hardware which control solid motor movable nozzle thrust vector control(TVC) actuator for Korea Space Launch Vehicle I(KSLV-I) are described. TVC computer hardware is the equipment which has jobs for receiving control commands from Navigation Guidance Unit(NGU) and then actuating TVC actuator. Also, it has ability to communicate with other on board or ground equipments. Computer hardware has a digital signal processor as the main processor which is capable of high speed calculating ability of control algorithm, so it can have more stability, reliability and flexibility than the previous analog controller of KSR-III. Target board was designed for on board program development and then first prototype hardware was developed. Top level system design criteria, hardware configurations and ground support equipment of TVC computer system are described.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.7
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• pp.620-628
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• 2016

The homotopy algorithm provides a robust method for determining optimal control, in some cases the global minimum solution, as a continuation parameter is varied gradually to regulate the contributions of the nonlinear terms. In this paper, the Successive Backward Sweep (SBS) method, which is insensitive to initial guess, augmented with a homotopy algorithm is suggested. This approach is effective for highly nonlinear problems such as low-thrust trajectory optimization. Often, these highly nonlinear problems have multiple local minima. In this case, the SBS-homotopy method enables one to steadily seek a global minimum.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.585-589
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• 2010

It is important for the liquid rocket engine to meet the exact performance requirements in order to guarantee the successful mission of the launch vehicle. Usually, a ground combustion test for the engine is conducted to reduce the performance error and for the tuning. For the gas-generator (GG) cycle engine, this adjustment process can be easily tuned by means of the control valves. A linearized correlation between the process parameters of the control - the combustion chamber pressure and the mixture ratio of engine - and the independent parameter of the control- rotational angle of the control valve - could be suitable to reduce the tuning errors. Also this linearity can reduce the effort for the tuning and make the process more explicit by ensuring a more intuitive control. In this point, we proposed an algorithm in the frame of the in-house-developed program to obtain the control valves' inherent characteristics which satisfy the linearity.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.5
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• pp.514-523
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• 2008

This paper presents a single-axis simulator developed to verify the attitude control algorithm of KAUSAT-2 satellite. Named KAUSatSIM, the simulator is composed of a single-axis rotation table using an air-bearing that simulates a frictionless environment, as well as sensors and momentum wheel that was used on KAUSAT-2. The simulator can be utilized for verification of KAUSAT-2 attitude control algorithm, development of new algorithms, and verification of performance. Tests were performed on the single-axis rotation simulator using the momentum wheel in order to verify the attitude control algorithm of KAUSAT-2. Satisfactory test results were obtained by designing a wheel controller that employs the proportional-derivative control method. In addition, a propulsion system was added and tested for development of a new satellite attitude control algorithm.

• Journal of the Korean Society of Marine Environment & Safety
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• v.22 no.1
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• pp.129-137
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• 2016

In the present study we verified performance of feed-forward control algorithm using short term prediction of ship motion information by taking advantage of developed numerical simulation model of FPSO motion. Up until now, various studies have been conducted about thrust control and allocation for dynamic positioning systems maintaining positions of ships or marine structures in diverse sea environmental conditions. In the existing studies, however, the dynamic positioning systems consist of only feedback control gains using a motion of vessel derived from environmental loads such as current, wind and wave. This study addresses dynamic positioning systems which have feedforward control gain derived from forecasted value of a motion of vessel occurred by current, wind and wave force. In this study, the future motion of vessel is forecasted via Brown's Exponential Smoothing after calculating the vessel motion via a selected mathematical model, and the control force for maintaining the position and heading angle of a vessel is decided by the feedback controller and the feedforward controller using PID theory and forecasted vessel motion respectively. For the allocation of thrusts, the Lagrange Multiplier Method is exploited. By constructing a simulation code for a dynamic positioning system of FPSO, the performance of feedforward control system which has feedback controller and feedforward controller was assessed. According to the result of this study, in case of using feedforward control system, it shows smaller maximum thrust power than using conventional feedback control system.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.16 no.12
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• pp.8187-8194
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• 2015

To accelerate a heavy roller coaster train with over 1G force, a lot of thrust is required and linear synchronous motor(LSM) as propulsion method is suitable for this kind of system. To increase the propulsion efficiency of LSM, precise and real-time position information of vehicle is required for accurate phase control. However, the discontinuous position information with relatively long time interval is usually transmitted from the hall-sensors on the track every magnet length. In this paper, the basic motor model based on traditional dq-axis equations is described and the motor dynamic model is produced by considering the cogging force and friction loss. To improve the position accuracy, the position estimator is also proposed for LSM control system. Simulations were performed to check the characteristics of the torque control system which includes the position estimator based on the motor model. Simulation results based on the linearized model show that this control system has an enough bandwidth and phase margin and the executed algorithm achieves an ideal effect to follow the real-time position signal. Therefore, the feasibility of position estimator is also confirmed.

• Proceedings of the Korean Institute of Intelligent Systems Conference
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• 2002.12a
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• pp.143-147
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• 2002

본 논문에서는 비행물체의 운동에 기초한 지능제어 알고리즘을 사용하여 대기의 환경적 요인과 기체형태 및 추력의 인위적 요인들간의 복잡한 함수관계를 지식과 경험에 의한 제어규칙으로서 비행안정성 확보와 자율비행을 위한 비행 자세제어를 행하였다. 비행 자세제어를 위하여 사용한 지능제어기는 다변수 입력 및 출력이 가능하며 강인성을 지닌 퍼지제어기를 사용하였다 실험을 위해 모형비행기와 자세 검출용 센서를 제작하고, 비행 전문가의 지식과 경험을 기초로 하여 작성한 제어규칙에 의하여 프로그램 된 퍼지제어기를 수 차례의 시험비행을 통해 제어규칙을 조정한 결과 안정된 자세제어를 행할 수 있었다.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.4
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• pp.73-78
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• 2011

When a liquid rocket engine - specifically for the gas-generator cycle engine has throttle valves to control the thrust level and mixture ratio of the engine, it is possible to adjust the inherent flow characteristics of the control valves in order to secure a linearized correlation between the control-process-parameters like the thrust or mixture ratio of an engine and the throttle angle of valve. These linearities can reduce the complexity of the control process and make the process more explicit by ensuring the intuitive control. In this point, we proposed an algorithm within the frame of the in-house-developed program to obtain the control valves' inherent flow characteristics which satisfy the linearity, and calculated the sensitivities of control valves with respect to the throttle angle. Also, we compared the obtained inherent flow characteristics with the existed data and concluded the results are satisfactory.

• The Transactions of the Korean Institute of Power Electronics
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• v.7 no.3
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• pp.281-288
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• 2002

This paper has realized a control system of a vibrator using PM excited Transverse Flux Linear Motor(TFLM). Proposed vibrator can supply a vibration force up to 700[N] at rated current, wide operation range of vibration displacement and high frequency for a tested structure. Also, volume of a vibrator system can be decreased because of a high trust force rato(a thrust force per weight=N/Kg). A proposed vibrator instead of a hydraulic vibrator can improve efficiency and have may advantages of maintenance and management. A desired value command is a vibration frequency and displacement in a controller for a vibrator system and a controlled values we a instant position and velocity of a mover Output value of the controller is phase current controlled by PWM converter. In this research, Dynamic simulation has been executed for analysis of a control algorithm and dvnauuc characteristics and is compared with experimental result.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.4
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• pp.73-80
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• 2005

In general, the performance of movable nozzle used for thrust vector control in solid rocket motor is estimated on the basis of the effective pivot of nozzle. However, it is nearly impossible to define the exact effective pivot by the mathematical model or experimental technique owing to pivot dynamics. In this paper, pivot dynamic properties were investigated by ADAMS simulation technique and trajectory of the exact effective pivot was modelled by the artificial neural network. Comparison of the proposed method was made with the virtual movable nozzle (computer simulation) to verify the method, and showed good agreement. Therefore, the proposed method will be applicable to predict the effective pivot of movable nozzle during bench or ground test.