• Proceedings of the Korean Society for Agricultural Machinery Conference
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• 2017.04a
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• pp.13-13
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• 2017

선회시스템의 수명을 정확히 예측하기 위해서는 굴삭기의 상부회전체 및 선회시스템의 모든 구성요소들의 질량관성모멘트를 고려하여 선회감속기의 수명 평가를 수행해야 한다. 선회감속기의 수명 평가방법은 주로 실험실 시험으로 수행이 되며, 시험 장비는 장비 구축 편의성과 비용 등의 이유로 증속기와 굴삭기 상부회전체의 등가 관성체 등으로 구성된다. 굴삭기 선회시스템의 정확한 등가 실험실 시험을 위해서는 시험에 사용되는 등가 관성체의 관성모멘트를 정확히 결정하는 것이 매우 중요하다. 본 연구는 굴삭기 선회시스템의 등가 실험실 시험을 위해 굴삭기 상부회전체의 관성모멘트를 결정하기 위하여 수행되었다. 굴삭기 선회 시험을 통하여 선회감속기 입력 속도 및 토크를 측정하였고, 반복계산법을 이용하여 굴삭기 상부 회전체의 등가관성모멘트를 계산하였다. 굴삭기 상부회전체의 시뮬레이션 모델을 개발하여 선회 시험 결과와 시뮬레이션 모델 비교 분석을 통해 굴삭기 시뮬레이션 모델을 검증하고, 검증된 모델을 이용하여 상부회전체의 관성모멘트가 반영된 등가 실험실 시험 시뮬레이션 모델을 개발하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.1
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• pp.34-42
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• 2009

High-speed air turbine handpieces have been used as a dental cutting tool in clinical dentistry for over 50 years, but little study has been reported on their performance analysis. Therefore, the effect of turbine blade shape on performance characteristics of dental air turbine handpiece were studied using CFD in this paper. Computations have been performed for five different positions of turbine blade by using frozen rotor method that is one of steady-state method. The characteristics of turbine blade for shapes and reflection angles were analyzed. As a result of the computation, torque is increased by increasing the reflection angle of turbine blade.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.10
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• pp.112-119
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• 2003

Design analysis and grow1d test on propellers for 50 m-long airship propulsion were conducted. The design analysis code developed by adopting the vortex-blade-element theory was applied to the design of optimum propeller at the condition of maximum flight speed at sea level. In order to validate the performance of the propeller, ground test of the propeller was performed, and thrust and torque were measured for several different pitch angles at static condition. The power coefficients and thrust coefficients obtained by the test compared well with the analysis results.

• The Journal of Korean Academy of Prosthodontics
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• v.50 no.2
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• pp.92-98
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• 2012

Purpose: The aim of this study was to evaluate the effects of different abutment materials on abutment screw loosening and settling-down effect in conical connection type implant system. Materials and methods: Three types of abutment, cementation, gold UCLA, and metal UCLA abutment were used. Two UCLA groups were fabricated in a similar pattern to cementation abutment. Type III gold alloy and Nickel-Chromium alloy was used for casting gold UCLA abutment and metal UCLA abutment, respectively. Fixture and abutment were tightened to 30 Ncm by using digital torque controller and re-tightening was conducted with same force after 10 minutes. Digital torque gauge was used to measure loosening torque and fixture/abutment length was measured by digital micrometer. Dynamic loads between 25 N and 250 N were applied with $0^{\circ}$ angle to the abutment axis. After loading, fixture/abutment length was re-measured and amount of settlement was calculated. Loosening torque value was also measured for comparison Results: All three groups showed significant differences of length when comparing before and after loading, but there was no significant difference of settling amount in all groups. Loosening torque values were significantly decreased when comparing before and after loading in all groups($P$<.05). However, there was no significant difference in loss of loosening torque values when compared to groups. Conclusion: In internal conical connection type implants, dynamic load affected on settlement and loosening torque of implant, but there was no differences between abutments materials. Likewise gold UCLA abutment, metal UCLA abutment might be able to withstand functional load.

• Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
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• v.13 no.2
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• pp.39-45
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• 1999

In case of field weakening region, torque is directly affected by flux. In this region, the flux reference is cIecreased inversely proportional to the rotor speed. As the flux is decreased, the magnetizing inductance is nonnally increased The increased magnetizing inductance limited voltage for controlling current In this paper, rreasuring q axis voltage in field weakening region, magnetizing inductance in flux calculating can be readjusted. Computer simulation and experiment results demostrate the efficacy of the prqx>sed rrethod. Proposed algorithm is expected to the application of the adjustable drive system in the spinning and weaving field. field.

• Proceedings of the KIEE Conference
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• 2009.07a
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• pp.706_707
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• 2009

This paper presents the torque calculation method of a permanent magnet spherical motor. To calculate the torque of the spherical motor by using finite element method (FEM), 3-dimensional FEM must be used. However since it spends too much time and memory in using 3-D FEM, the easier torque calculation method was presented. In this method, it is very important to get the approximation function of the torque profile curve; the authors present the approximation method of the torque profile curve. This paper shows the torque calculation result coming closer to the torque by 3-D FEM.

• Proceedings of the KIEE Conference
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• 2009.04b
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• pp.100-102
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• 2009

밴드패스필터를 사용하여 센서리스 벡터제어에 영향을 주는 6차고조파 성분을 제거하여 안정적인 제어를 제안하였다. 비정현적인 역기전력을 가진 IPMSM모터의 센서리스 벡터 제어에서 유기전압에 고조파가 포함되는 경우에 그 영향이 추정연산에 나타나게 된다. 삼상 모델에 나타나는 5차, 7차 고조파의 경우는 d, q축 모델로 변환 시 6차 고조파 성분으로 나타나게 된다. 이 6차 고조파 성분은 위치 추정과 속도추정에 영향을 주어서 토크 맥동을 발생시킨다. 본 논문에서는 이러한 6차 고조파의 영향으로 추정연산에 미치는 영향들을 알아보고. 이 영향을 고조파 제거를 위한 복잡한 계산을 하지 않으면서 간단한 밴드패스필터를 통해 고조파가 위치추정에 미치는 영향을 최대한 줄이는 방법을 제시하였다.

• Proceedings of the Korea Information Processing Society Conference
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• 2023.11a
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• pp.750-751
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• 2023

현재 로봇 배달 서비스의 실외 상용화를 위해 다양한 주행 환경에 대한 최적화 연구가 진행되고 있습니다. 본 논문에서는 비평탄 지형에 안정적인 주행이 가능하며, 효율적인 장애물 극복을 위한 로봇 구조를 제시합니다. 본 연구에서는 기존 다리-바퀴 방식을 통한 장애물 극복 로봇과 비교 연구를 진행하며 모터 구동 토크의 이론적인 계산 비교, 모의실험을 통한 검증으로 로봇 설계안의 성능을 평가합니다. 이 연구를 통해 고안한 로봇의 동작을 설명하며, 4륜 주행 로봇의 혁신적인 장애물 극복 설계 방법을 제안합니다.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.38 no.6
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• pp.609-617
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• 2014

Even though the variable pitch control of a wind turbine blade is known as an effective component for power control over the rated wind speed, it has limited applicability to small wind turbines because of its relatively high cost on the price of small wind turbine. Instead, stall control is generally applied in the blade design without any additional cost. However, stall delay can frequently be caused by high turbulence around the turbine blade, and it can produce control failures through excessive rotational speed and overpowering the electrical generator. Therefore, a passive pitch control module should be considered, where the pitch moves with the aerodynamic forces of the blade and returns by the elastic restoring force. In this study, a method to calculate the pitch moment, torque, and thrust based on the lift and drag of the rotating blade wing was demonstrated, and several effective wing shapes were reviewed based on these forces. Their characteristics will be estimated with variable wind speed and be utilized as basic data for the design of the passive pitch control module.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.10
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• pp.891-898
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• 2007

Optimal aerodynamic design for the pitch-controlled horizontal axis wind turbine and its aerodynamic performance for various pitch angles are performed numerically by using the blade element momentum theory. The numerical calculation includes effects such as Prandtl‘s tip loss, airfoil distribution, and wake rotation. Six different airfoils are distributed along the blade span, and the special airfoil i.e. airfoil of 40% thickness ratio is adopted at the hub side to have structural integrity. The nonlinear chord obtained from the optimal design procedure is linearized to decrease the weight and to increase the productivity with very little change of the aerodynamic performance. From the comparisons of the power, thrust, and torque coefficients with corresponding values of different pitch angles, the aerodynamic performance shows delicate changes for just $3^{\circ}$ increase or decrease of the pitch angle. For precisive pitch control, it requires the pitch control algorithm and its drive mechanism below $3^{\circ}$ increment of pitch angle. The maximum torque is generated when the speed ratio is smaller than the designed one.