• 한국자동차공학회논문집
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• 제14권6호
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• pp.184-189
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• 2006

Tumble flow test rig has been used as the useful tool in the developing intake system because major flow pattern induced by intake port of DOHC engine is tumble. Angular momentum of in-cylinder tumble flow can not be directly measured by impulse torque meter in the test rig like that of in-cylinder swirl flow due to rotational axis of the flow. Therefore the adaptor to transform tumble to swirl flow must be adapted in the test rig. In this study, using the commercial CFD code STAR-CD, we studied the effects on measured results due to the variation of the major design variables in the adaptor, tube length(L), tube diameter(D) and cylinder height(H). The effect of the attached angle($\theta$) of the test head to the adaptor also was simulated.

• 한국생산제조학회지
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• 제22권6호
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• pp.957-962
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• 2013

This paper presents a performance testing device for safety fences of domestic professional baseball stadiums. Safety fences of professional stadiums have been fabricated and installed without adhering to any safety regulations, safety fences demonstrate critically low safety performances and many outfielders are severely injured every season. In this study, we designed and fabricated a performance testing device for safety fences and investigated its validity and reproducibility. A HIC (head injury criterion) was used for the statistical analysis of colliding data. We found that the optimal expulsion pressure and eliminated the accelerometer by replacing it with a velocity sensor using an estimation of the correlation between the momentum data obtained from velocity sensor and the impulse data from the accelerometer.

• 한국소음진동공학회논문집
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• 제18권7호
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• pp.764-774
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• 2008

A fire-out-of-battery(FOOB) mechanism, which is a new recoil technology, can reduce dramatically the level of a recoil force compared to the conventional recoil system. The FOOB mechanism pre-accelerates the recoil parts in direction opposite of conventional recoil before ignition. This momentum of the recoil parts due to pre-acceleration can reduce the firing impulse. In this paper, the dynamics of the recoil system with this FOOB mechanism is formulated and simulated numerically. The results of the simulation show that the FOOB system can reduce the recoil force and stroke compared to the conventional system under normal condition. When the fault modes happen, the FOOB system may not perform well and may be damaged seriously due to excessive recoil force and stroke. Hence, the control of the fault modes is necessary to achieve the normal operation of the FOOB system. The results that an additional MR damper enables the FOOB system to perform well under all firing condition.

• 한국운동역학회지
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• 제23권2호
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• pp.131-139
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• 2013

Naejirgi is one of the fastest, most forceful and most often being used kicks in Taekkyon games, The purpose of this study was to investigate kinetic factors on two types of Naejirgi kick, one of which uses knee bending of supporting leg and the other uses little it. 12 taekkyoners (11 males and one female) who are the students of Y University participated in this study. They have been practicing on Taekkyon for five years or more. Positions of CoM, the elapsed time of each phase, vertical ground reaction forces, joint moments and impulses of supporting leg were analyzed for this study. The results were as follows; in Naejirgi with knee bending of supporting leg than without knee bending of supporting leg, the vertical motion range of whole body CoM was larger during phase 2 and 3, the elapsed time of phase 4 were longer, players stayed longer in the nearest location to opponent, during phase 4 the vertical ground reaction forces of supporting foot were larger, and joint extension moments and angular impulses of supporting leg (especially knee) were larger. In conclusion supporting knee bending is not a useful strategy for Naejirgi, because players stay longer in the nearest position to opponent and consumed more muscle force and energy for producing the vertical momentum which is unnecessary for pushing down the opponent.

• Composites Research
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• 제22권4호
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• pp.27-32
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• 2009

본 연구에서는 충돌속도가 다르지만, 총 충돌에너지는 동일하게 유지한 상태에서 충돌을 가했을 때 발포 고분자의 응력-변형률 관계와 충돌에너지 흡수 특성에 관하여 고찰하였다. 이는 충돌시 관성과 변형률 속도에 변화를 주어 재료의 반응거동 및 특성을 파악하기 위함이다. 두가지 다른 밀도(64 $kg/m^3$, 89 $kg/m^3$)를 갖는 발포고분자시편에 대한 준정적시험과 충돌시험이 수행되었다. 또한 Sherwood-Frost 모델과 임펄스 모멘텀 이론의 두가지가 연성된 방정식을이용하여 발포고분자의 구성방정식으로 제안하였다.\ 제안된 구성방정식을 이용하여, 응력변형률 선도를 구하고, 충돌시험결과와 비교하여, 본 구성방정식이 우수하게 결과를 예측할 수 있는 것으로 나타났다.

• 한국항공우주학회지
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• 제47권11호
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• pp.753-760
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• 2019

스파크제트 액츄에이터(Sparkjet Actuator), 혹은 플라즈마 합성 제트 액츄에이터(Plasma Synthetic Jet Actuator)는 능동 유동 제어 장치의 일종으로 신쎄틱 제트와 같은 기존의 능동 유동 제어 장치에 비해 더 강한 제트를 분출할 수 있기 때문에 초음속 유동 제어에 대한 가능성이 높다고 여겨지고 있다. 스파크제트 액츄에이터는 아크 플라즈마를 이용하여 캐비티(Cavity) 내부에 고온, 고압 유동을 발생시키고 이를 오리피스(Orifice) 혹은 노즐 목을 통해 분출시킴으로써 제트를 만들어낸다. 본 연구는 캐비티 내부에 위치한 전극의 위치를 변화시킴으로서 스파크제트 액츄에이터의 추력 및 유동 특성에 생기는 변화를 수치적으로 확인하였다. 전극 위치가 캐비티의 바닥에 가까워질수록 충격량이 증가하였고 캐비티 내부 평균 압력이 높게 유지되었다. 전극 위치가 캐비티 전체 높이의 25% 위치에 있을 때 2.515 μN·s의 충격량이 발생하였고 75% 위치에 있을 때 2.057 μN·s의 충격량이 발생하였다. 전극 위치가 캐비티 전체 높이의 50%에 있을 때보다 충격량이 각각 대략 9.92%와 -10.09% 정도 변화하였다.

• 한국작물학회지
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• 제28권4호
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• pp.419-424
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• 1983

밀양 2003, 한강찰벼, 태백벼 및 진흥을 공시하여 벼알의 인장강도를 측정하고, binder 수확시 포장손실과 지상 25, 50, 75, 100, 150cm 및 200cm에서 콘크리트 바닥에 이삭을 낙하시켜 낙하높이별 탈립율을 조사하여 충격력과 탈립율과의 관계를 구하고 인장강도의 년차변이를 조사하여 다음과 같은 결과를 얻었다. 1. 평균인장강도는 밀양 2003 0.743 Newton, 한강찰벼 1.078N, 태백벼 1.573N, 진흥 1.775N이었다. 2. 인장강도가 낮을수록 binder 수확시 탈립손실이 많았으며 탈립손실이 없는 인장강도는 약 1.7N이상이었다. 3. 벼의 binder 절단부위의 수분함량은 엽초가 76.7-77.8%, 간이 76-87%이었다. 4. Binder 수확시의 포장손실율은 한 이삭을 약 40cm 높이에서 콘크리트 바닥에 떨어뜨렸을 때의 탈립율과 같았다. 5. 충격력($\chi$, NewtonㆍSec)과 탈립율(Y, %)과의 관계는 밀양 2003에서 Y=-25.73+4958.4$\chi$ ($r^2$=0.987), 한강찰벼에서는 Y=-12.97+2258.3$\chi$ ($r^2$=0.979), 태백벼에서 Y=-5.24+840.4$\chi$ ($r^2$=0.976)이었다. 6. 인장강도는 동일품종에서도 년차간에 유의적변이를 보였는데 그 변이폭은 탈립성이 큰 품종에서 작았다.

• 한국운동역학회지
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• 제26권3호
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• pp.243-248
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• 2016

Objective: The aim of this study was to determine the kinematical characteristics of somersault with twist in the Lou Yun and Akopian motions and to provide useful information to gymnastic athletes in men's vault. Method: The study subjects were 12 male adult top athletes. After 12 trials (7 Lou Yun and 5 Akopian trials) filmed by using two digital high-speed camcorders set at 90 frames/sec, kinematical data were collected through the direct linear transformation (DLT) method. The mean differences in biomechanical variables were compared during the second flight upward phase. The kinematic characteristics of somersault with twist in the Lou Yun and Akopian motions were identified. Results: In Lou Yun motion, the vertical release velocity through horse breaking was not difficult to obtain, so the athletes had enough time to prepare for the twist. Therefore, the Lou Yun motion has an advantage to make a cat twist in the pike posture. In the Akopian motion, obtaining the horizontal velocity through horse pushing was so easy that the Akopian athletes attained a large angular impulse and angular momentum. Therefore, the Akopian motion has an advantage to making a tilt twist in the body tilting posture. Conclusion: This study suggests that gymnastic athletes should control their body segment movements in order to increase the twisting angular velocity of the whole body, which requires regulation of the longitudinal moment of inertia of the body. Moreover, athletes should prepare for the shoulder and hip twists early in order to make the landing position in advance.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.703-712
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• 2004

A variant of the magnetoplasma jet engine (magjet) is here proposed for airbreathing flight in the hypersonic regime. As shown in Figure 1, the engine consists of two distinct ducts: the high-speed duct, in which power is added electromagnetically to the incoming air by a momentum addition device, and the fuel cell duct in which the flow stagnation temperature is reduced by extracting energy through the use of a magnetoplas-madynamic (MPD) generator. The power generated is then used to accelerate the flow exiting the fuel cells with a fraction bypassed to the high-speed duct. The analysis is performed using a quasi one-dimensional model neglecting the Hall and ion slip effects, and fix-ing the fuel cell efficiency to 0.6. Results obtained show that the specific impulse of the magjet is at least equal to and up to 3 times the one of a turbojet, ram-jet, or scramjet in their respective flight Mach number range. Should the air stagnation temperature in the fuel cell compartment not exceed 5 times the incoming air static temperature, the maximal flight Mach number possible would vary between 6.5 and 15 for a magnitude of the ratio between the Joule heating and the work interaction in the MPD generator varied between 0.25 and 0.01, respectively. Increasing the mass flow rate ratio between the high speed and fuel cell ducts from 0.2 to 20 increases the engine efficiency by as much as 3 times in the lower supersonic range, while resulting in a less than 10% increase for a flight Mach number exceeding 8.