• 대한전기학회논문지:전기기기및에너지변환시스템부문B
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• 제49권5호
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• pp.358-363
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• 2000

In this paper, a voltage equations, a thrust force equations and kinetic equation are derived from the basic structure of a 2-phase hybrid type linear stepping motor(HLSM). And a micro-stepping method in order to eliminate effectively the resonant phenomena and to increase the positional resolution of the HLSM was proposed. The proposed micro-stepping method can divide one step into the maximum 128 micro-steps under simple control system. The dynamic characteristics of proposed micro-stepping method were analyzed by the ACSL(Advanced Continuous Simulation Language) with the voltage equations, the thrust force equations and the kinetic equation, and were measured by laser experimental system. As the result, the justice of theory was confirmed, and the resonant phenomena, the positional resolution and dynamic thrust were improved by the proposed micro-stepping method.

• 대한전기학회논문지:전기기기및에너지변환시스템부문B
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• 제55권10호
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• pp.498-504
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• 2006

Thrust force of linear motor is one of the important factor to specify motor performance. In this study, we optimized maximizing the thrust force of TFLM(Transverse Flux Linear Motor) using Response Surface Methodology by the table of orthogonal way. The Response Surface Methodology was well adapted to make the analytical model of the maximum thrust force and enable the objective function to be easily created and a great deal of the time In computation to be saved. Therefore, it is expected that the proposed optimization procedure using the Response Surface Methodology can be easily utilized to solve the optimization problem of electric machine.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2005년도 제25회 추계학술대회논문집
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• pp.487-490
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• 2005

고체 추진 로켓에 있어서의 추력제어는 액체 추진 로켓의 그것보다 한정되어 있다. 추진제의 혼합비는 물론 연소시간과 면적 등 연소에 관계된 모든 부분들이 이미 정해져 있기 때문에 당연한 결과이다. 이러한 고체 추진 로켓의 추력을 방향 제어하기는 고체 추진 로켓의 용도나 목적 대비 효율 측면에서 실용적이지 못한 부분이다. 하지만 고체 추진 로켓의 추력의 극대화하여 탑재물의 중량 한계를 늘리고 보다 많은 목적을 위한 탑재물의 증가는 당연히 이루어야 할 과제이다. 고체 추진 로켓에서의 추력을 노즐 형상의 설계를 통해 강구해 보았다.

• 한국가시화정보학회지
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• 제10권1호
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• pp.47-54
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• 2012

Single Stage To Orbit (SSTO) missions which require its engines to be operated at varying back pressure conditions, use engines operate at high combustion chamber pressures (more than 100bar) with moderate area ratios (AR 70~80). This ensures that the exhaust jet flows full during most part of the operational regimes by optimal expansion at each altitude. Aero-spike nozzle is a kind of altitude adaptation nozzle where requirement of high combustion chamber pressures can be avoided as the flow is adapted to the outside conditions by the virtue of the nozzle configuration. However, the thrust prediction using the conventional thrust equations remains to be a challenge as the nozzle plume shapes vary with the back pressure conditions. In the present work, the performance evaluation of a new aero-spike nozzle is being carried out. Computational studies are carried out to predict the thrust generated by the aero-spike nozzle in varying back pressure conditions which requires the unsteady pressure boundary conditions in the computational domain. Schlieren pictures are taken to validate the computational results. It is found that the flow in the aero-spike nozzle is mainly affected by the base wall pressure variation. The aerospike nozzle exhibits maximum performance in the properly expanded flow regime due to the open wake formation.

• Tribology and Lubricants
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• 제39권2호
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• pp.76-80
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• 2023

This paper describes an experimental investigation of the effect of cooling flow rate on gas foil thrust bearing (GFTB) performance. In a newly developed GFTB test rig, a non-contact type pneumatic cylinder provides static loads to the test GFTB and a high-speed motor rotates a thrust runner up to the maximum speed of 80 krpm. Force sensor, torque arm connected to another force sensor, and thermocouples measures the applied static load, drag torque, and bearing temperature, respectively, for cooling flow rates of 0, 25, and 50 LPM at static loads of 50, 100, and 150 N. The test GFTB with the outer radius of 31.5 mm has six top foils supported on bump foil structures. During the series of tests, the transient responses of the bearing drag torque and bearing temperature are recorded until the bearing temperature converges with time for each cooling flow rate and static load. The test data show that the converged temperature decreases with increasing cooling flow rate and increases with increasing static load. The drag torque and friction coefficient decrease with increasing cooling flow rate, which may be attributed to the decrease in viscosity and lubricant (air) temperature. These test results suggest that an increase in cooling flow rate improves GFTB performance.

• 수산해양기술연구
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• 제60권1호
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• pp.80-86
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• 2024

We analyzed the performance of hubless rim propellers based on the number of blades, maintaining a fixed pitch ratio and expanded area ratio, using computational fluid dynamics (CFD). Thrust coefficient, torque coefficient and efficiency according to the number of blades were analyzed. In addition, the pressure distribution on the discharge and suction sides of the blade was analyzed. As the advance ratio increases, the thrust coefficient decreases. The highest thrust was shown when the advance ratio was lowest. For the three, four, five and six-blades, the torque coefficient tended to decrease as the advance ratio increased. In the case of seven and eight-blades, the torque coefficient tended to increase as the advance ratio increased. The maximum efficiency was found when the advance ratio was 0.8. When the three-blade, it showed high efficiency at all advance ratios. A high pressure distribution was observed at the leading edge of the discharge blade, and a low pressure distribution was observed at the trailing edge. Applying a hubless rim-driven thruster with the three-blade can generate higher thrust and increase work efficiency.

• 한국항공우주학회지
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• 제38권10호
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• pp.998-1011
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• 2010

본 연구에서는 미래 한국의 달탐사에 대비, 제한추력을 이용한 최적의 지구-달 천이궤적 설계를 수행하였다. 보다 실제적인 임무 시나리오 설계를 위해 달 천이 (Trans Lunar Injection, TLI) 기동에 사용되는 발사체 상단 킥모터의 추력 성능을 제한하였다. 이를 바탕으로 지구 출발부터 달 근접에 이르는 지구-달 천이비행궤적이 설계되었으며, 제한추력을 이용하여 설계된 비행 궤적의 최적화 결과와 순간추력을 이용하여 최적화된 결과가 비교 분석되었다. 만약 순간추력을 이용해 도출된 예비 임무 설계의 결과가 제한추력을 가정한 임무 설계를 위해 응용될 경우, 가정된 제한추력의 크기에 따라 다양한 범위의 기동량의 차이가 발생 할 수 있어 이에 따른 충분한 고려가 이루어져야 함을 확인하였다. 본 연구에서 제시된 제한추력을 이용한 달탐사 임무궤적 설계/해석 결과는 미래 한국의 달탐사를 대비하는데 있어 다양한 사전 지식을 제공할 것이며 장차 상세한 임무설계를 위한 알고리즘의 기반으로 사용될 수 있다.

• 한국항공우주학회지
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• 제33권7호
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• pp.9-17
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• 2005

비정상 패널법을 이용하여 복엽기 형태 배치의 복식 플랩핑 에어포일들에 대한 후류의 형상 및 추력 특성을 연구하였다. 에어포일들에서 발생하는 후류 형상은 와핵 모델, 와핵 첨가법 그리고 4계 Runge-Kutta 법을 사용하여 계산하였다. 해석 결과는 유동 가시화, 엄밀해 그리고 전산 해석 결과와 비교하여 검증하였다. 복엽기 배치의 에어포일의 경우, 두께 및 캠버는 추력을 감소시키는 효과가 있었다. 플런징과 피칭 운동들 사이의 위상차가 90도 및 120도 일 때 최대 추력이 발생하였다. 플런지 속도 및 피치 크기가 클수록 추력은 증가하였다. 에어포일 사이의 거리가 감소할수록 추력은 증가하나, 0.6c 이하로 가까워질 경우 추력은 감소하였다.

• Physical Therapy Rehabilitation Science
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• 제10권2호
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• pp.205-211
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• 2021

Objective: This study aimed to identify the effects of assuming different knee angles and hip abduction during bridge exercise and hip thrust exercise on lower body muscle activity. Design: Cross-sectional study Methods: Thirty-three healthy adults (18 men and 15 women) were instructed to perform the bridge and hip thrust exercises while randomly assuming 120°, 90° and 60° of knee flexion and 0° and 30° of hip abduction. EMG data (%maximum voluntary isometric contraction) were recorded three times from the erector spinae (ES), gluteus maximus (GM) and biceps femoris (BF) muscles of participant's dominant side and the mean values were analyzed. Results: The results showed that, during the hip thrust compared to the bridge exercise, there was significantly greater gluteus maximus muscle activity in all hip conditions while the biceps femoris activity was significantly less, and the erector spinae muscle activity was significantly greater with 30° of hip abduction (p<0.05). With all exercises, the erector spinae and the biceps femoris exhibited significantly greater muscle activity with 60° of knee flexion compared to 90° and 120° of knee flexion (p<0.05), and significantly greater muscle activity with 90° compared to 120° of knee flexion (p<0.05). In the case of the gluteus maximus, greater muscle activity was exhibited with 120° compared to 60° of knee flexion with all hip abduction conditions (p<0.05). Conclusions: It was effective for muscle activation of main agonists such as the gluteus maximus and erector spinae during thrust exercise, and the change in knee flexion angle was effective for muscle activation of the gluteus maximus. Therefore, it is considered that this study can be used as a selective indicator of the target movement angle during hip strengthening exercise for specific muscles.

• 터널과지하공간
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• 제28권6호
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• pp.513-527
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• 2018

TBM은 사전에 예측하지 못한 지반조건의 변화에 대한 대응력이 재래식 공법과 비교할 때 상대적으로 낮기 때문에, 설계단계에서 TBM의 사전 성능예측과 공사기간 산정을 위한 굴진율 예측이 매우 중요하다. 기존 연구에서 구축된 211개의 TBM 데이터베이스에 신규 데이터를 추가하여 TBM의 핵심 제작 사양인 최대 추력, 커터헤드 최대 토크 및 회전속도, 커터헤드 구동력 사이의 상관관계를 지반조건에 따라 분석하였다. 기존 연구들에서와 같이 TBM의 최대추력, 최대토크, 구동력과 같은 기본 제작사양을 추정하는 데 있어 TBM 외경은 매우 중요한 정보임을 확인할 수 있었다. 국외의 TBM 데이터베이스로부터 도출된 회귀식과 본 연구로부터 얻어진 회귀식을 비교한 결과, 최대추력의 경우는 유사한 경향을 보였으나, 대단면 TBM에서 본 연구의 회귀식에서 추정된 최대토크가 국외의 회귀식보다 더 높게 추정하는 경향이 나타났다.