• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.5
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• pp.399-405
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• 2021

In the present study, ground tests and CFD simulations for a ducted fan system were performed to verify the hovering performance of the ducted fan system designed by KARI rotorcraft team. Six blades were composed for the ducted fan, and target rotating speed of the fan was decided to 4,000 RPM. Collective pitch angles were considered from 20 degrees to 36 degrees. The test data were obtained by increasing the rotating speed up to 4,000 RPM in 1,000 RPM increments. The CFD simulations were considered only 4,000 RPM of rotating speed. The hovering performance was represented by thrust, power, duct thrust ratio, and FM(Figure of Merit). Reliability of the performance results was ensured through the test and simulation results, and it was found that the target performance was achieved under conditions above 31 degrees of the pitch angle.

• Proceedings of the Korean Reliability Society Conference
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• 2000.11a
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• pp.211-218
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• 2000

진공청소기 제품의 시장불량을 조사한 결과 모터의 불량이 전체 불량 중 많은 부분을 차지하고 있으며 조금씩 증가추세를 보이고 있음을 알 수 있었다. 그러므로, 본 연구에서는 진공청소기 모터의 출하 전, 불량품 검출력을 향상시킬 수 있는 가속시험법을 개발하고자 하였다. 또한, 가속시험을 통해 사업부의 신뢰성시험 납기 단축 및 시험비용 절감 뿐아니라 모터에 대한 가속시험 기술력 확보를 목적으로 수행하였다. 가속수명시험 시 스트레스인자는 모터의 브러쉬 마모 가속을 위해 정격보다 높은 전압을 인가하였다. 가속모형으로는 전압스트레스를 인가하는 경우 일반적으로 사용되는 역자승(Inverse Power) 모형을 사용하였다. 가속시험 결과 정격의 120% 전압에서 가속계수 4.3이 얻어졌다. 이는 수출 모델의 경우 현재의 시험시간 42일을 10 일로 단축하여 76%의 시험시간이 절감되어 시험 가능 횟수가 4배로 증가되는 결과를 얻었다. 추가적으로 다양한 On/Off 시간 변환 시험을 실시하였으나 현시험법과의 고장 모드 (브러쉬 마모로 인한 회전정지) 및 고장유형이 일치하지 않음을 알 수 있었다. 이 결과는 On/Off 시간변환을 통한 가혹시험의 경우 주의를 필요로 함을 나타낸다.

• Journal of Korean Ophthalmic Optics Society
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• v.15 no.3
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• pp.213-217
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• 2010

Purpose: To emphasize the necessity of post-fitting by follow-up test, the mis-alignment was analyzed after initial wearing of toric soft contact lenses (TSCL). Methods: After trial contact lenses were worn to 87 eyes with myopic astigmatism for 1 week, we observed the alignment of axis mark on trial contact lenses using slit lamp and corrected the rotated axis by method of LARS. After final fitting, rotation ratio, rotation degree and rotation position were analyzed compared to initial prescription divided to amount of cylinderical and spherical powers. Results: Rotation ratio of TSCL's axis was increased as increment of both cylinderical powers and (-)spherical powers. An average of rotation degree was $10^{\circ}{\sim}13^{\circ}$ which was not related to amount of their powers. Rotation position of TSCL's axis was more to temporal than to nasal. Conclusions: Because mis-alignment of axis after TSCL wearing induce the poor sight, adjustment of axial alignment as a result of follow-up must be performed.

• Journal of the Korean Society for Marine Environment & Energy
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• v.14 no.4
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• pp.264-272
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• 2011

Shipbuilders carry out the operation test to check the conditions of the main propulsion system and auxiliaries for moored vessel in the quoy before the sea trial. The estimation of the thrust and torque for the partially submerged propeller should be prepared to ensure the safety of mooring line and the ship. In this paper, the variations of the thrust and torque according to the shaft submergence and the propeller rotating speed in bollard pull condition are investigated with the model test and the numerical analysis. Based on these resaearch, the empirical formula representing the physical phenomena of the partially submerged propeller is derived and validated through comparison to measurement results of full-scale propellers under the quoy operation test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.4
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• pp.253-260
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• 2013

Ice accretions on the surface around a rotorcraft air intake can deteriorate the safety of rotorcraft due to the engine performance degradation. The computational simulation based on modern CFD methods can be considered extremely valuable in analyzing icing effects before exact but very expensive icing wind tunnel or in-flight tests are conducted. In this study the range and amount of ice on the surface of anti-icing equipment are investigated for heat-on and heat-off modes. It is demonstrated through the computational prediction and the icing wind tunnel test that the maximum mass and height of ice of heat-on mode are reduced about 80% in comparison with those of heat-off mode.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.40 no.6
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• pp.595-602
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• 2016

An automotive wheel bearing is important part that translates rotating motion and bears vehicle weight. Recently, in accordance with the demands for $CO_2$ emission reduction and fuel economy regulation, the requirements for the weight reduction and miniaturization of vehicles has increased. Therefore, life evaluation technology of the bearings has increased in necessity. Since the bearing life is affected by many parameters such as bearing geometry, bearing specifications, and vehicle specifications, it is difficult to predict. In this paper, the bearing life was tested by varying the applied load and rotation speed and comparing them with the basic rating life and modified rating life that were suggested in ISO standards. From the results, it was found that there was a difference between the test life and theoretical life and modified rating life than basic rating life was to be relatively well predicted by test life.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.560-562
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• 2017

This paper presents the development and test results of a test rig for confirming the hover performance of the coaxial propeller which is applied to the drone in order to carry out the mission that requires high payload such as the development of the courier drones. the performance of each propeller was measured by varying the thrust and torque according to the H/D ratio. the Thrust sensor and torque sensor were used to measure the thrust and torque generated when the propeller rotated, and a photo sensor was used to measure the rpm. it used the data acquisition system to acquire data from each sensor, and used the Labview softwaer to control data storage, monitoring and BLDC motor control. In the test, each propeller meansured the figure of mefit according to the chansge of the interval at the same rpm.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.18 no.3
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• pp.724-729
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• 2017

The crashworthiness of the fuel tank of a rotorcraft is verified through the crash impact test. The crash impact test has a high risk of failure due to the application of an excessive load, which can seriously affect the overall development schedule of the aircraft. Therefore, a lot of effort has been made to minimize the possibility of failure in the actual test by carrying out a numerical analysis of the crash impact test of the fuel tank in the initial design stage. Recently, an external auxiliary fuel tank was added to increase the cruising distance. In this study, the numerical analysis results of the crash impact test based on several different shapes of the external auxiliary fuel tank are presented, in order to evaluate its crashworthiness. For the numerical analysis, smoothed particle hydrodynamics (SPH), which is one of the fluid-structure coupled analysis methods, is applied and the test conditions prescribed by US military standards are reflected in the analysis conditions. In addition, the material property data previously obtained by the specimen test of the actual fuel tank is applied to the numerical analysis. As a result, the equivalent stress of the fuel tank material itself and the metal fitting is provided and the possibility of acquiring data for designing the crash-worthiness of the external auxiliary fuel tank is evaluated by examining the behavior and working load of the internal mounted components.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.5
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• pp.482-489
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• 2010

This paper describes the test procedure, instrumentation, verification methodology and the results of the ground vibration test(GVT) and force vibration test(FVT) of the SmartUAV aircraft to estimate experimentally dynamic characteristics of the aircraft. Bungee cords are used to emulate free-free boundary conditions of the test aircraft. The SmartUAV is excited by three shakers and one-hundred frequency response functions(FRF's) is measured. The FRF's are reduced and analyzed to identify the dynamics parameters of the SmartUAV. To extract modal parameters of the SmartUAV such as, natural frequencies and damping ratios, the poly-reference least square complex exponential method is used in the time domain. The mode shape coefficients are estimated with the least squares frequency domain method to identify the vibration modes. The FVT was performed by fixed sine frequency with three shakers on the x, y and z direction and vibration characteristics of structures and detail equipments are measured.

• Tunnel and Underground Space
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• v.9 no.4
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• pp.328-336
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• 1999

To characterize the hydro-mechanical behavior of a rock joint, a rotary shear testing apparatus was devised in this study. Shear stress was driven by twisting the end of a sample in the rotary shear testing apparatus. The test results show that the rotary shear test underestimates the peak shear strength of a rock joint. The torque is known as a function of the radial distance from the axis of rotation, resulting in the radial variation of the shear stress. Fluid flow through rock joints is mainly dependent on the Joint roughness, contact area, initial aperture. To examine the dependency, the relationship between the hydraulic and the mechanical apertures for shear-flow was established by measuring the initial aperture. It shows that the mechanical aperture and the hydraulic aperture increase linearly with the dilatancy. The difference between the hydraulic and mechanical apertures describes the deviation from the behavior predicted by the parallel plate model.