• Proceedings of the Korean Society for Agricultural Machinery Conference
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• 2017.04a
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• pp.61-61
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• 2017

노지 고추 수확작업은 100% 인력에 의존하고 있으며 7~9월에 걸쳐 5~6회의 다수의 작업이 수행되어 노동 강도가 크다. 또한 농촌의 고령화와 노동력 감소로 인하여 수확인력의 부족이 발생하고 있음에도 불구하고 시중에 유통되고 있는 고추 및 노지채소 수확작업 편이기기는 동력이 아닌 인력으로 이랑사이를 이동하며 작물을 수확하는 구조로 되어있다. 이는 노동 강도를 줄여주는 효과가 미미하기 때문에 동력이 수반된 편이장치가 필요하며 또한 적절한 모터 및 제어장치가 요구된다. 적절한 모터를 선정함에 있어서 영향을 주는 인자는 주행저항(RR)이며, 구성요소로는 구름마찰저항(Rr), 공기저항(RА), 등판저항(Rg), 가속저항(Ra)이 있으며, 다음과 같은 식으로 정의된다. 주행저항(RR)=구름마찰저항(Rr)+공기저항(RA)+등판저항(Rg)+가속저항(Ra) 구름마찰저항(Rr)=구름마찰저항계수(${\mu}$)${\times}$차량총중량(W) 등판저항(Rg)=차량총중량(W)${\times}Sin{\theta}$ 공기저항(RА), 및 가속저항(Ra)은 1m/s 미만의 속도가 요구되기 때문에 무시할 수 있다. 동력원에서 최종 구동축으로 전달된 동력은 주행장치를 통하여 지면에 전달되고 이 동력에 의해 작업차의 주행장치에 추진력이 발생하며 주행장치의 추진력이 주행저항 이상이 될 때 작업차는 전진하게 된다. 따라서 작업차의 주행속도를 V(m/s), 전동기의 효율을 ${\mu}_m$, 동력전달효율을 ${\mu}_{TD}$라고 하면 다음과 같은 식이 산출된다. 전동기의 소요출력(P)=주행저항(RR)${\times}$속도(V)/전동기의 효율(${\mu}_m$)${\times}$동력전달효율(${\mu}_{TD}$) 구름마찰계수를 0.3이라고 할 때 포장의 경사도와 작업차의 주행속도 변화에 따른 주행소요 동력을 비교하였다. 주행소요동력은 포장의 경사각과 주행속도의 증가와 더불어 증가한다. 고추 및 노지채소 수확작업 편이장치의 작업시 요구되는 주행속도는 일반적으로 0.25m/s, 등반각은 5도이다. 이때 구동 전동기의 출력은 안전율을 고려하여 식에 의해 계산한 결과 1ps으로 산출 되었다. 선정한 구동모터의 감속비는 7.18 : 1, 에너지의 효율은 78 %, 기동토크는14 N/m 이며, 축전지의 경우 구동모터에 기반 하여 구입이 간편하고 상용화 되어있는 연축전지를 사용하여 교체 및 수리가 간단하도록 하였다. 축전지는 12V 18Ah의 축전지 2개를 사용한다.

• Journal of Hospice and Palliative Care
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• v.7 no.2
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• pp.179-188
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• 2004

Purpose: The purpose of this study was to investigate the degree of fatigue and its related factors in cancer patients during chemotherapy. Methods: The subjects of this study consisted of 90 patients over 20 years old who were receiving chemotherapy at the injection room of the o.p.d. and ward admission care unit in a University hospital located in Gwang-ju city and data were collected from August 8th to October 2nd, 2002. Collected data were analysed using SPSS v 10.0. to obtain summary statistics for the descriptive analysis, t-test, ANOVA, pearson correlation, and multiple regression. Results: 1. Fatigue of the subjects was significantly correlated with physical distress score. and 6 items of subscale those were nausea, vomiting, anorexia, pain, and immobility, showed statistically significant correlation. 2. Fatigue of the subjects showed statistically significant differences according to a nap satisfaction. Fatigue of the subjects was significantly correlated with mood state, Also, all 5 items of subscale, which are those were anxiety, confusion, depression, energy, and anger showed statistically significant correlations. 3. Fatigue of the subjects showed statistically significant differences according to metastasis, chemotherapy cycle, post operation existence, post radiation therapy existence. There were significant negative correlation between fatigue and hematocrit and fatigue and weight change. There was no significant correlation between fatigue and spiritual well-being state. With the result to multiple regression, Immobility, Anorexia, Anger explained fatigue by, pain, and immobility showed statistically significant correlation.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.1
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• pp.31-36
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• 2012

Military vehicles, compared to conventional vehicles, require higher driving performance, quieter operation, and longer driving distances with minimal fuel supplies. The series hybrid electric vehicle can be driven with no noise and has high initial startup performance, because it uses only a traction motor that has a high startup torque to drive the vehicle. Moreover, the fuel economy can be improved if the vehicle is hybridized. In series hybrid electric vehicles, the electric generation system, which consists of an engine and a generator, supplies electric energy to a battery or traction motor depending on the vehicle driving state and battery state of charge (SOC). The control strategy determines the operation of the generation system. Thus, the fuel economy of the series hybrid electric vehicle relies on the control strategy. In this study, thermostat, power-follower, and combined strategies were compared, and a 37% improvement in the fuel economy was implemented using the combined control strategy suggested in this study.

• Journal of Aerospace System Engineering
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• v.13 no.6
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• pp.52-59
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• 2019

The rotor blade is a key component that generates the lift, thrust, and control forces required for helicopter flight by the torque transmitted through the hub and the blade pitch angle control, and should be designed to factor vibration characteristics so that there is no risk of resonance with structural safety. In this study, the structural design of the main rotor blade for MPUH(Multi-Purpose Unmanned Helicopter) was conducted and the sectional stiffness measurement of the fabricated blade was performed. The evaluation of the vibration characteristics of the main rotor system was then conducted factoring the measured stiffness distribution. The interior of the rotor blade comprised of the skin, spar, and torsion box, and carbon and glass fiber composites were applied. The Ksec2D program was applied to predict the stiffness of blade, and the results were compared to the measured data. CAMRADII, a comprehensive rotorcraft analysis program, was applied to investigate the natural frequency trends and resonance risks due to the rotor rotation.

• Journal of Astronomy and Space Sciences
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• v.25 no.4
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• pp.481-490
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• 2008

Reaction wheel is one of the actuators for spacecraft attitude control, which generates torque by changing an inertial rotor speed inside of the wheel. In order to generate required torque accurately and estimate an accurate angular momentum, wheel speed should be measured as close to the actual speed as possible. In this study, two conventional speed detection methods for high speed motor with digital tacho pulse (Elapsed-time method and Pulse-count method) and their resolutions are analyzed. For satellite attitude maneuvering and control, reaction wheel shall be operated in bi directional and low speed operation is sometimes needed for emergency case. Thus the bias error at low speed with constant acceleration (or deceleration) is also analysed. As a result, the speed detection error of elapsed-time method is largely influenced upon the high-speed clock frequency at high speed and largely effected on the number of tacho pulses used in elapsed time calculation at low speed, respectively.

• Journal of IKEEE
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• v.24 no.4
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• pp.954-960
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• 2020

This paper proposes a speed variable proportional resonant current control method for a single-phase permanent magnet synchronous motor(PMSM). Due to the electromagnetic characteristics of a single-phase PMSM, negative and zero torques are generated in the part corresponding to the phase difference between the stator current and the back electromotive force. In addition, overcurrent limitation is required because of the low stator resistance and inductance in sensorless operation. When using the vector control for current control of single-phase PMSM under these conditions, processes of coordinate transformation, inverse coordinate transformation, and generation of virtual dq-axis components are required. However, the proposed variable speed proportional resonant current control method does not need the coordinate transformation used for AC motors. In this paper, we have confirmed stable maneuverability by using variable proportional resonant current control algorithm, and proposed sensorless control based on a mathematical model of a single-phase PMSM without a position sensor when reaching a constant speed. The usefulness of the current control method was verified through several experiments.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.6
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• pp.134-141
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• 2019

This paper is a study on design improvement of rotorcraft horizontal stabilizer. The rotorcraft horizontal stabilizer stabilizes the behavior of the pitch, yaw, etc. from the aircraft. Because of this role, horizontal stabilizers are a major component (Flight Safety Part) that affects flight safety on rotorcraft. However, when the rotorcraft was operated in domestic, cracks were found in the inner structure of the horizontal stabilizer and design improvement was needed. In this paper, we identified the two causes of the horizontal stabilizer crack defects through fracture analysis and structural analysis. The first is the tightening torque when the bolt is tightened, and the second is the lead-lag behavior of aircraft. In order to improve these two causes, bolt fastening method, flange structure and thickness were changed and composite ring was applied. In order to verify the design improvement, the structural analysis was performed and the structural strength was improved. Also Fatigue analysis of the internal structure (Rib 1) was performed and it was confirmed that the requirements were satisfied.