• Journal of Aerospace System Engineering
• /
• v.15 no.5
• /
• pp.98-105
• /
• 2021

This study presented the results of the static load tests conducted to verify the structural robustness of the composite oxidant tank for a space launch vehicle. First, we introduced the test equipment used in the static load test of the composite oxidant tank, and then described the test requirements that the composite oxidant tank must satisfy. In addition, we presented a test set-up diagram consisting of the static load test fixture, hydraulic pressure, control equipment, and data acquisition equipment, and the load profile of the static load test of the composite oxidant tank consisting of shear, equivalent compression, bending, and combination tests. As a result of load control, we verified the reliability of this test by showing the errors between the input load and the feedback load in each channel according to the increase of the test load, and the feedback error between the channel A and channel B of load cell in each load actuator. As a result of the static load test, the load of the actuator was properly controlled within the allowable error range in each test, and we found that the test specimen did not cause damage or buckling that causes significant structural defects in the required load.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
• /
• 1996.04a
• /
• pp.108-116
• /
• 1996

본 논문에서는 하중부와 방법을 추(dead weight)와 공압(pneumatic)을 이용한 방법에서 스프링을 이용한 방법을 추가하였으며, 압축형 스프링을 선택적으로 사용하여 마찰시험기 수직방향에서의 강성을 큰 변화 폭으로 변화시켰다. 또한 선행된 연구를 통하여 수직하중의 변동량에 크게 영향을 미치는 것으로 알려진 바 있는 디스크 시편의 misaligment 효과를 상사하고 극대화 하기 위하여 본 논문에서는 경사진 디스크 시편을 추가로 사용하였다. 상기조건으로 마찰시험기 시스템의 각 하중부과 방법과 수직강성 변화가 마찰특성에 미치는 영향을 실험적으로 측정 평가하였으며, 마찰시험기 동특성계 모델의 이론적 해석을 통하여 마찰특성 변화를 고찰하였다. 또한, 미끄럼 접촉 시의 수직력과 마찰력을 측정하고, 데이터의 통계적 처리방법에 따른 마찰계수의 변화 특성도 평가하였다.

• Journal of Aerospace System Engineering
• /
• v.15 no.1
• /
• pp.80-85
• /
• 2021

In this study, for conducting a static load test of an external fuel tank used for an aircraft, the flight load acting on the external fuel tank was converted to the test load and the suitability of the converted test loads was confirmed. In order to calculate the test load from the flight load, the external fuel tank was divided into several sections. Shear load, moment by unit shear load, and unit moment were calculated for each section. Test loads for each section were then calculated by computing the shear load, the moment of each section, and flight load condition. In actual static load tests, it might not be possible to impose the test load in the calculated position due to physical constraints. Therefore, after determining positions in which the load could be imposed in the actual test, the test load calculated for each section was redistributed to selected positions. Finally, a test load plan was established by applying a whiffle tree to enhance the efficiency of the test performance while making it easier to operate the actuator. The reliability of the test load plan was verified by comparing it with flight load conditions.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
• /
• 1995.06a
• /
• pp.37-47
• /
• 1995

본 논문은 마찰력을 측정하는 시스템에 동특성 변화를 주어서, 이에 의해 발생하는 마찰현상의 변화와 수직하중의 변동특성에 관하여 측정을 하였으며, 미끄럼속도 및 하중조건 변화와 미끄럼운동을 하는 두물체 재료조합 변화에 따른 상기의 마찰특성변화에 관하여 실험적 및 이론적 고찰을 행하였다. 시스템의 동특성 변화를 주기 위하여 시스템의 강성(Stiffness)의 변화를 주었고, 또한 수직 하중 부과 방법을 Dead weight를 이용한 방법과 공압(Pneumatic)에 의한 방법을 비교함으로써 관성력 및 감쇠(Damping) 특성에 변화를 주었다. 시험 대상의 물체들은 강(Steel) 및 폴리머류의 Rosin과 PTFE를 선정하여, 재료변화에 따른 마찰특성 변화를 유도하였다.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
• /
• 1998.04a
• /
• pp.335-341
• /
• 1998

In this study, the dynamic characteritics in various loading methods for wear tester were investigated experimentally. As for the dead-weight, the pneumatic, and the hydraulic method, the load control performance against external disturbances was estimated under the several loading conditions like the different sliding speed, the varied normal load, and the misaligument. The hydraulic loading method showed the most stable loading performance of all the loading methods in the experiment.

• Tribology and Lubricants
• /
• v.12 no.2
• /
• pp.55-64
• /
• 1996

Frictional characteristics with the change of loading method and normal stiffness at dry sliding surfaces were experimentally and theoretically evaluated in this study. For the study, a ball-on-disk typed test rig was built and implemented, which allowed a proper selection of loading mechanism and normal stiffness of the test rig. Loading method were varied from dead weight to pneumatic cylinder and spring loading, and the normal stiffness was varied by a spring of different stiffness. Test results showed that frictional characteristics at various loading methods were different even though the operating variables were the same. Discrepancy in the frictional characteristics, such as coefficient of friction and fluctuation in the normal load, were explained by the change in dynamic parameters of the test rigs. Results also showed that coefficient of friction, which defines as a ratio of frictional force divided a normal load, could be differently evaluated in the calculation when fluctuation in the normal load was significant.

• KEPCO Journal on Electric Power and Energy
• /
• v.3 no.2
• /
• pp.107-111
• /
• 2017

The reliability on high cycle fatigue damage mechanism for new blades manufactured by reverse-engineering is demonstrated by success-run test. Turbine blades always experience various dynamic loads in turbine operation, as well as being in resonance condition and forced by fluid-induced vibrations mostly during run-up/down, which may accumulate high cycle damage to the blades. The accidents caused by blade failure especially incur not only a lot of troubles to the machinery but also huge financial losses. Therefore it is necessary to verify the reliability of blades in advance for the safe use. The success run test for the reliability demonstration is designed and performed for the new blades using the technique known as resonant high cycle fatigue testing.

• Journal of the Korean Institute of Gas
• /
• v.9 no.2 s.27
• /
• pp.34-37
• /
• 2005

The membrane for LNG storage tank behaves linearly in macroscopic view, but behaves elasto-plastically in some local areas, and has the structure undergoing both tension and bending. That is, the membrane is not able to be evaluated with the fatigue characteristics of the material, and it is so difficult to evaluate the membrane with a real big model because of the difficulty of imposing complex loads. Therefore, a prediction formula fur the fatigue life of the membrane is proposed to use for the design of LNG storage tank.

• Journal of the Earthquake Engineering Society of Korea
• /
• v.9 no.1 s.41
• /
• pp.33-42
• /
• 2005

Even in moderate to low seismic regions like Korean peninsular where wind loading usually governs the structural design of a tall builidng, the probable structural impact of the 500-year design basis earthquake (DBE) or the 2400-year maximum credible earthquake (MCE) on the selected structural system should be considered at least in finalizing the design. In this study, seismic performance evaluation was conducted for concentrically braced steel highrise buildings that were only designed for wind by following the assumed domestic design practice. It was found that wind-designed concentrically braced steel highrise buildings possess significantly increased elastic seimsic capacity due to the system overstrength resulting from the wind-serviceability criterion and the width-to-thickness ratio limits on steel members. The strength demand-to-strength capacity study based on the response spectrum analysis revealed that, due to the system overstrength factors mentioned above, wind-designed concentrically braced steel highrise buildings having a slenderness ratio of larger than six can withstand elastically even the maximum credible earthquake at the performance level of immediate occupancy.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.41 no.12
• /
• pp.994-1001
• /
• 2013

Process of helicopter development is divided in design, manufacture and test & evaluation phase. Test & evaluation is performed step by step in order of component test, rig test, system ground test and flight test. After completing ground test and before first flight, US military specification requires 50hrs-PFAT in order to assure flight safety. PFAT is the test which requires tie-down and severe load imposition and it needs special ground test vehicle which is similar to helicopter prototype as well as much cost and period. In case of KUH, we have performed tailored PFAT considering KUH development environment. In this paper, we propose a proper way to perform the PFAT in accordance with development environment by giving KHU PFAT procedure and result.