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항공통신기술 : 패러포일 투하 시스템의 궤적 추종 제어기의 설계
양빈 ( Bin Yang ),최선영 ( Sun Young Choi ),이정태 ( Joung Tae Lee ),임동근 ( Dong Keun Lim ),황정원 ( Chung Won Hwang ),박승엽 ( Seung Yub Park ) 한국항행학회 2014 韓國航行學會論文誌 Vol.18 No.3
본 논문은 패러포일 투하 시스템을 설계하고 분석하는데 있다. 패러포일 시스템의 6-자유도(6-DOF) 모델을 새우고, 비선형 모델 예측 제어와 PID 제어 방법이 펄럭 편 요각을 제어하기 위해 각각 적용되었다. 펄럭 편 요각의 오버슈트 시간 및 세팅 시간의 결과를 비교하면서 PID제어 방법을 사용하는 것으로부터 펄럭 편 요각이 좀 더 안정화 되는 것을 확인하였다. 그런 다음 MATLAB에 의해 수행된 궤적 추종 효과의 시뮬레이션 결과에 의해 궤적 추종 제어기가 설계되었다. 패러포일 궤적의 측 방향 오차가 그것의 측 방향 편차 제어 방법에 의해 제거 될 수 있었다. 참고로 측 방향 편차는 현재 경로계획의 보간법에 의해 얻어졌다. 그리고 설계된 궤적을 사용하면서, 풍 외란을 추가하는 것으로부터 궤적 추종 시스템이 시뮬레이션 되었다. 시뮬레이션 결과는 풍 외란이 PID로 제어되는 펄럭 편 요각 변화에 의해 제거됨으로써 설계된 궤적에 아주 만족하였다. In this paper, parafoil airdrop system has been designed and analyzed. 6-degrees of freedom (6-DOF) model of the parafoil system is set up. Nonlinear model predictive control (NMPC) and Proportion integration differentiation (PID) methods were separately applied to adjust the flap yaw angle. Compared the results of setting time and overshoot time of yaw angle, it is found that the of yaw angle is more stable by using PID method. Then, trajectory following controller was designed based on the simulation results of trajectory following effects, which was carried out by using MATLAB. The lateral offset error of parafoil trajectory can be eliminated by its lateral deviation control. The later offset deviation reference was obtained by the interpolation of the current planning path. Moreover, using the designed trajectory, the trajectory following system was simulated by adding the wind disturbances. It is found that the simulation result is highly agreed with the designed trajectory, which means that wind disturbances have been eliminated with the change of yaw angle controlled by PID method.
FPGA를 이용한 공간벡터 변조 PWM 및 디지털 제어부의 System On Programmable Chip 설계
황정원(Jeong-won Hwang),김승호(Seung-ho Kim),양빈(Bin Yang),이천기(李千紀),박승엽(Seung-yub Park) 대한전기학회 2012 전기학회논문지 P Vol.61 No.1
This paper presents implementation of SVPWM technique for three phase Voltage Source Inverter using FPGA. Software-based vector-control calculations much this drawback, in order to improve the hardware-vector-control tries. Without the need for additional software, vector control algorithm is designed to be modular SOPC, and DSP will reduce most of the operations. In this paper, the SVPWM that using HDL for the AC motor vector control algorithm level, and the dead time part and the speed control in order to controled a speed detector and designed in the form of modules. Then ALTERA corporation Cyclone Ⅲ series EP3C16F484 can be verified by implemented.
영구자석형 동기전동기의 고저/선회 제어용 드라이버 설계 모델링
이천기(Chun-Gi Lee),황정원(Jeong-Won Hwang),이정태(Joung-Tae Lee),양빈(Bin Yang),임동근(Dong-Keun Lim),박승엽(Seung-Yub Park) 대한전기학회 2014 전기학회논문지 P Vol.63 No.4
The purpose of this paper is to control of the low-speed, high-precision PMSM 2- axes pitch/turning. In this paper, apply the PAM-PWM inverter for it. However, The PAM-PWM inverter, control algorithms and hardware is complex. But it is possible to improve the performance in the low-speed operation can reduce the effect of the PWM ripple and Dead Time of inverter by applying suitable DC-bus voltage control. The direct driver PMSM(Permanent Magnet Synchronous Motor) configured to vector control part, PAM control part and the other controller. The vector control part includes PI current, speed control, additional space vector modulation. PAM control part has to have PI voltage controller and P current controller for DC-bus voltage control. Besides, the motor position estimator , the speed estimator and the counter electromotive force and Dead Time Compensation are added. With this arrangement, PMSM was driven with a low pole pitch / turning by performing the current control to the current command or torque command is the paper. As a result, it was possible to minimize the disturbance component that appears in the drive in proportion to the DC voltage magnitude. The use of a hydraulic drive method for a two-axis bubble column is a typical tank. When using the PWM PAM inverter driver is in the turret can be driven by high-precision, low vibration, low noise compared to the hydraulic drive may contribute to the computerization of the turret.
3차원 공간에서의 비행 경로각을 이용한 비행시간 및 충돌각 제어 유도법칙
김승호 ( Sheng Hao Jin ),이천기 ( Chun Gi Lee ),양빈 ( Bin-yang ),황정원 ( Chung Won Hwang ),박승엽 ( Seung Yub Park ) 한국항행학회 2012 韓國航行學會論文誌 Vol.16 No.1
본 논문에서는 표적이 고정되고 유도탄의 속도가 일정하다고 가정하고, 3차원 공간에서 비행 경로각을 이용하여 비행시간과 충돌각을 동시에 제어하는 호밍 유도법칙을 제안한다. 유도탄 비행궤적의 비행 경로각을 독립변수로 하여 비선형 모델을 구성한다. 제안한 호밍 유도법칙이 종말 종속 충돌각과 비행시간 제어가 가능하며, 목표물에 정확히 도달하는 과정을 보여준다. 그리고 동시공격시나리오에도 적용할 수 있다. 시뮬레이션을 통해 제안한 유도법칙의 성능을 확인한다. This paper on the assumption that the target is stationary and the velocity of missile is fixed value. In three dimensional space. Using flight path angle to simultaneous control impact-time-and-angle base on a homing guidance law. The independent variable in the nonlinear engagement model is the flight path angle of the missile. The propose homing guidance law can see the controllability of impact-time-and-angle. And also can see the processing of the missile arrive at the target. It is applied to several salvo attack scenarios. The performance of the proposed guidance law is verified by simulations.