• 수산해양기술연구
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• 제9권1호
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• pp.1-18
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• 1973

중층트를 어구(漁具)의 소해심도(掃海深度)를 일정(一定)한 적정어획속도(適正漁獲速度)에서 기동성(機動性)있게 변화(變化)시키기 위하여 기초적인 모형어구(模型漁具)의 수조실험(水槽實驗)과 특별(特別)히 고안한 깊이바꿈틀을 이용(利用)한 이차(二次)에 걸친 해상시험(海上試驗)을 통(通)하여 연구한 결과를 요약(要約)하면 다음과 같다. 1. 중층(中層)트롤의 그물어구의 깊이 y는 끌줄의 길이 L과 단위(單位) 길이의 끌줄, 깊이바꿈틀 및 그물의 각(各) 수중중량(水中重量) $W_r,\;W_o,\;W_n$과 각(各) 항력(抗力) $R_r,\;R_o,\;R_n$ 사이의 관계(關係)는 차원해석법(次元解析法)에 의하면 다음과 같다. $$y=kLf(\frac{W_r}{R_r},\;\frac{W_o}{R_o},\;\frac{W_n}{R_n})$$ 단(但), k는 상수(常數)이고 f는 함수이다. 2. 단위 길이당(當)의 수중중량(水中重量) $W_r$, 길이 L인 끌줄 끝에 항력(抗力) $D_n$, 수중중량(水中重量) $W_n$d인 수중저항분를 매달고 끌줄의 다른 한 끝을 수면(水面)에서 예인(曳引)할 때,. 끌줄의 형상(形狀)을 현수곡선이라고 보면, 수중저항분의 깊이 y는 다음과 같다. $$y=\frac{1}{W_r}\{\sqrt{{D_n^2}+{(W_n+W_rL)^2}}-\sqrt{{D_n^2+W_n}^2\}$$ 3. 중층(中層)트롤의 그물어구(漁具)깊이의 변화(變化) ${\Delta}y$는 예강(曳綱)의 길이 L을 바꾸거나 추(錘) ${\Delta}W_n$를 부가(附加)하면 다음과 같다. $${\Delta}y{\approx}\frac{W_n+W_{r}L}{\sqrt{D_n^2+(W_n+W_{r}L)^2}}{\Delta}L$$ $${\Delta}y{\approx}\frac{1}{W_r}\{\frac{W_n+W_rL}{\sqrt{D_n^2+(W_n+W_{r}L)^2}}-{\frac{W_n}{\sqrt{D_n^2+W_n^2}}\}{\Delta}W_n$$ 단(但), $D_n$은 그물어구의 항력(抗力)이다. 4. 끌줄 상(上)의 중간점(中間点)에 추(錘) $W_s$를 부가(附加)할 때 중층(中層)트롤 그물어구의 깊이바꿈 ${\Delta}y$는 $${\Delta}y=\frac{1}{W_r}\{(T_{ur}'-T_{ur})-T_u'-T_u)\}$$ 단(但) $$T_{ur}^l=\sqrt{T_u^2+(W_s+W_{r}L)^2+2T_u(W_s+W_{r}L)sin{\theta}_u$$ $$T_{ur}=\sqrt{T_u^2+(W_{r}L)^2+2T_uW_{r}L\;sin{\theta}_u$$ $$T_{u}'=\sqrt{T_u^2+W_s^2+2T_uW_{s}\;sin{\theta}_u$$ $T_u$ 추(錘)를 부가(附加)하지 않았을 때 끌줄 상(上)의 중간점(中間点)에 있어서의 예인어선(曳引漁船) 쪽을 향하는 장력(張力)이고, ${\theta}_u$는 장력(張力) $T_u$와 수평방향(水平方向)과 이루는 각도(角度)이다. 5. 어떠한 형태(形態)의 저예강용(底曳綱用) 전개판(展開板)도 성능(性能)에 있서어 차이는 있으나 전중량(全重量)을 가볍게 하고 저변(底邊)에 무게를 달아 안정(安定)시키면 중층예강용(中層曳綱用)으로 사용(使用)할 수 있다는 것이 모형(模型) 실험(實驗)결과 밝혀졌다. 6. 모형(模型) 그물(Fig.6)의 수조실험(水槽實驗)에서는 예강속도(曳綱速度) v m/sec, 강고(綱高) H cm 및 수유저항(水流抵抗) R kg 사이에는 다음과 같은 간단(簡單)한 관계식(關係式)이 성립(成立)한다. $$H=8+\frac{10}{0.4+v}$$$R=3+9v^2$$ 7. 특별(特別)히 고안한 십자(十字)날개형(型) 깊이바꿈틀과 H날개형(型) 깊이 바꿈틀을 비교(比較)한 결과(結果) 전자(前者)보다 안정성(安定性)이 우월하였다. 8. 그물어구(漁具)의 유수저항(流水抵抗)이 매우 크며 또 거의가 항력(抗力)으로 볼 수 있으므로 깊이바꿈틀의 종류에 관계없이 그물어구의 소해심도(掃海深度)는 대단히 안정(安定)된 상태를 유지하였다. 9. H날개형(型) 깊이바꿈틀의 수평(水平)날개 면적율 $1.2{\times}2.4m^2$로 하였을 때 유수저항(流水抵抗) 2 ton의 그물 어구를 2.3kts로 예인(曳引)하면서 영각(迎角)을 $0^{\circ}{\sim}30^{\circ}$로 변화(變化)시킨 결과(結果), 끌줄의 길이에 관계없이 약(約) 20m의 깊이바꿈을 얻을 수 있었다.

• Journal of Microbiology and Biotechnology
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• 제26권7호
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• pp.1163-1172
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• 2016

The Ω-loop is a nonregular and flexible structure that plays an important role in molecular recognition, protein folding, and thermostability. In the present study, molecular dynamics simulation was carried out to assess the molecular stability and flexibility profile of the porcine trypsin structures. Two Ω-Loops (fragment 57-67 and fragment 78-91) were confirmed to represent the flexible region. Subsequently, glycosylation site-directed mutations (A73S, N84S, and R104S) were introduced within the Ω-loop region and its wing chain based on its potential N-glycosylation sites (Asn-Xaa-Ser/Thr consensus sequences) and structure information to improve the thermostability of trypsin. The result demonstrated that the half-life of the N84S mutant at 50℃ increased by 177.89 min when compared with that of the wild-type enzyme. Furthermore, the significant increase in the thermal stability of the N84S mutant has also been proven by an increase in the T_m values determined by circular dichroism. Additionally, the optimum temperatures of the wild-type enzyme and the N84S mutant were 75℃ and 80℃, respectively. In conclusion, we obtained the thermostability-improved enzyme N84S mutant, and the strategy used to design this mutant based on its structural information and N-linked glycosylation modification could be applied to engineer other enzymes to meet the needs of the biotechnological industry.

• 대한기계학회논문집A
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• 제28권3호
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• pp.281-288
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• 2004

The hybrid composite material (Al/GFRP laminates) are applied to the fuselage and wing in a aircraft. Therefore, Al/GFRP laminates suffer from the cyclic bending moments. This study was to evaluate the effect of fiber stacking angle on the fatigue crack propagation and delamination behavior using the relationship between crack growth rate (da/dN) and stress intensity factor range (ΔK) in Al/GFRP laminates under cyclic bending moment. The variable delamination growth behavior in case of three different type of fiber orientations, i.e., [Al/O$_2$/Al], [Al/+45$_2$/Al] and [Al/90$_2$/Al] at the interface of Al layer and glass fiber layer was measured by ultrasonic C-scan images. As results of this study, It represent that the delamination shape should turns out to have more effective characteristics on the fiber stacking angle. The extension of the delamination zone in case of [Al/+45$_2$/Al] and [Al/90$_2$/Al] were not formed along the fatigue crack profile. The shape of delamination zone depend on fiber stacking angle and the variable type with the delamination contour decreased non-linearly toward the crack tip at the Al layer.

• 부모자녀건강학회지
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• 제11권1호
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• pp.37-48
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• 2008

Purpose: The purpose of this study was to investigate the Enneagram personality types, ego-identity, self-efficacy and interpersonal relations among adolescents in high school. Methods: The participants were 322 high school students. Data were collected through self-report questionnaires, which were constructed to include demographic-environmental factors, Enneagram personality types, ego-identity, self-efficacy and interpersonal relations. The data were analyzed using descriptive statistics and pearson correlation coefficients. Results: In the nine Enneagram personality types, type 9 was highly measured. In the triadic center of Enneagram personality types, gut type was highly measured. In the wing, 9W1 was highly measured and the disruption rather than integration was highly measured. The most development level was level 5. The score of ego-identity was 3.25, the score of self-efficacy was 3.32 and the score of interpersonal ralations was 3.50. The correlation of ego-identity, self-efficacy and interpersonal relations showed significantly positive correlation with all. Conclusion: There were correlating relationships among ego-identity, self-efficacy, interpersonal relations in high school students. Based on the outcomes of this study, it is necessary to study on the relationship between Enneagram personality types and related variables. Also, We need to develop program that improve ego-identity, self-efficacy and interpersonal relations according to Enneagram personality types.

• 천문학회보
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• 제41권1호
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• pp.70.3-70.3
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• 2016

Active galactic nuclei (AGNs) typically show a non-thermal continuum locally represented by a power-law and many prominent emission lines in the UV and optical regions. AGNs are classified by two types, where Type I AGNs exhibit both broad and narrow lines and only narrow lines are observed in Type 2 AGNs. The unification models of AGNs invoke the existence of a molecular torus just outside of the broad line region. In the presence of a high column HI region associated with the molecular torus, we propose that significant fraction of broad line photons near Lyman series can be scattered by atomic hydrogen in the torus. In particular, $Ly{\alpha}$ being the strongest emission line, strong linear polarization may develop around $Ly{\alpha}$ through Rayleigh scattering. We adopt a Monte Carlo technique to investigate the polarized transfer of $Ly{\alpha}$ in a thick HI region with the shape of a torus. We consider the range of HI column density N_HI = 1020-23 with fixed geometric parameters of the torus such as the inner and outer radii and the height. We present the polarized spectra and angular distribution of Rayleigh scattered radiation around $Ly{\alpha}$. We find that the $Ly{\alpha}$ core part is polarized in the direction perpendicular to the symmetry axis whereas in the far wing part it is polarized in the parallel direction. It is concluded that the unification of AGNs implies that $Ly{\alpha}$ can be uniquely polarized through Rayleigh scattering.

• 항공우주시스템공학회지
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• 제17권2호
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• pp.1-8
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• 2023

회전익 항공기의 동력전달축은 경량화를 위하여 중공축을 적용하였으며 선형탄성 파괴역학을 이용해 균열 전파 거동을 예측할 수 있다. 본 논문에서는 유한요소해석을 통하여 원주방향 관통형 균열을 가지는 중공축의 균열성장수명을 예측하였다. 비틀림을 부여하고 균열을 고려한 요소를 형성하여 2차원 유한요소모델을 생성하였다. 초기 균열 길이를 정의하고 균열 길이를 증가시켜 유한요소해석을 수행해 균열 선단의 응력확대계수를 도출하였다. 응력확대계수가 중공축을 구성하는 재료의 파괴인성을 초과하기 직전의 길이를 한계 균열 길이로 정의한다. 응력확대계수 핸드북을 통해 응력확대계수를 계산하여 한계 균열 길이를 도출하고 균열성장속도식을 수치적분하여 각각의 균열성장수명을 비교해 제안한 유한요소해석 기법을 검증하였다.

• 제어로봇시스템학회논문지
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• 제22권9호
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• pp.705-709
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• 2016

Micro-electro-mechanical systems (MEMS) gyroscopes are widely used in various robot applications. However, these conventional gyroscopes need to vibrate the proof mass using a built-in actuator at a fixed resonance frequency to sense the Coriolis force. When a robot is not moving, the meaningless vibration of the gyroscope wastes power. In addition, this continuous vibration makes the sensor vulnerable to external sound waves with a frequency close to the proof-mass resonance frequency. In this paper, a feasibility study of a new type of gyroscope inspired by insect halteres is presented. In dipterous insects, halteres are a biological gyroscope that measures the Coriolis force. Wing muscles and halteres are mechanically linked, and the halteres oscillate simultaneously with wing beats. The vibrating haltere experiences the Coriolis force if the insect is going through a rotational motion. Inspired by this haltere structure, a gyroscope using a thin mast integrated with a robot actuation mechanism is proposed. The mast vibrates only when the robot is moving without requiring a separate actuator. The Coriolis force of the mast can be measured with an accelerometer installed at the tip of the mast. However, the signal from the accelerometer has multiple frequency components and also can be highly corrupted with noise, such that raw data are not meaningful. This paper also presents a suitable signal processing technique using the amplitude modulation method. The feasibility of the proposed haltere-inspired gyroscope is also experimentally evaluated.

• 한국의류학회지
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• 제27권3_4호
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• pp.407-417
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• 2003

The purpose of this study is to develop designs and patterns of a functional brassiere. For this purpose, women who have protruding and drooping breasts with 75B for their brassiere size were sampled. The fitting test for the fitness and function of test brassiere and control brassiere were carried out twice and compared the results from the both in terms of front, rear and side looks. The results of this study can be summarized as follows; 1. The results from measuring the level of sag and spread, and volume and protrusion of breasts shows that there are some distinctive differences in the measurements before and after wearing the test brassiere and the test brassiere is proved to be very effective in correcting breasts' shapes. 2. Front look: Since the two front cutting lines of the test brassiere served to have the curved main part pressing against the breasts, it could support breasts to more than satisfactory level. In addition, upperline panel and side panels of the test brassiere were found to have the upperline of the upper cup pressed against the breasts and at the same time it pressed and gathered the flab around upper part of the breasts and armpits that helped to rearrange the shape of the breasts. It is also proved that the two-pieced test brassier was found to be more functional in supporting the lower cup of the breasts. 3. Rear look: The test brassier was made up of two wide U-shaped wings with 2.5cm tape on its lower sides. Each wing has 4 lines and 3 hems (5.5cm). For this reason, the test brassiere was tighter and better fitted on its back. 4. Side look and entire look: The wings of the test brassiere might look wider than that of the control brassier which has conventional straight-shaped wings, but it was analyzed that the test brassiere held the upper and lower sides of the wings more effectively to be more pressed against the breast. Therefore, the test brassiere scored higher in terms of adjusting to body movements, while the control brassiere looked better in overall terms. 5. The functional brassier fur protruding and drooping breasts developed from the experiments of this study is a full side stretch brassiere which covers the entire breasts satisfactorily. The pattern drafting methods are suggested in to .

• 한국항공우주학회지
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• 제36권6호
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• pp.541-549
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• 2008

피로해석은 반복하중 하에서의 항공우주 구조물에 대한 구조적 파괴를 예방하기 위해 수행된다. 본 논문에서는 틸트로터형 무인 항공기에 대하여 피로수명에 대한 평가를 하였다. 먼저 틸트로터형 무인항공기의 기동에 맞는 하중 스펙트럼을 생성해 내었으며, F.C.L. 부품중 하나인 플랩퍼론 연결부위에 대하여 피로해석을 수행 하였다. 틸트로터형 무인항공기는 크게 두 가지 기동 형태로 나눌 수 있는데, 이 착륙시의 헬리콥터 형태와 순항시의 고정익 형태가 되겠다. 전체적인 피로하중 스펙트럼을 만들기 위해서 헬리콥터 형태에는 FELIX를, 고정익 형태에서는 TWIST를 사용하였다. 한편으로는, S-N 실험점이 해석에 사용될 때 재료수명의 전 영역에 대한 S-N 회귀식을 얻기 위하여 크리깅 메타 모델이 사용되었다. 그리고 최소 자승법을 이용한 이차 회귀식에 대한 S-N 커브 역시 생성하였다. 더욱이 이 커브들이 갖고 있는 정확도를 측정하기 위하여 결정 계수법을 사용하였다. 마지막으로는 플랩퍼론 연결 부위에 대한 피로수명 결과를 MSC. Fatigue와 비교하였다.

• 한국산학기술학회논문지
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• 제19권11호
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• pp.568-573
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• 2018

무인항공기는 유인항공기에 비해 가격이 저렴하고, 운용이 용이하기 때문에 최근 공간정보 구축, 농업, 어업, 기상관측, 통신, 엔터테인먼트 분야 등에서 광범위하게 사용되고 있다. 특히, 공간정보 구축 관련 분야에서 무인항공기는 데이터 취득의 신속성과 경제성 때문에 많은 주목을 받고 있다. 하지만 무인항공기를 이용해 제작되는 정사영상에는 건물이나 산림부분의 왜곡현상이 발생하며, 공간정보 분야의 원활한 활용을 위해서는 이러한 문제를 해결할 필요가 있다. 본 연구에서는 다양한 조건에서 무인항공기 정사영상의 왜곡을 파악하기 위해 고정익, 회전익, 수직이착륙형의 무인항공기를 활용하여 건설현장, 도심지역, 산림지역 등 다양한 대상지역을 촬영하고, 정사영상을 제작하여 분석하였다. 연구를 통해 무인항공기 영상의 중복도가 왜곡현상의 가장 큰 요인이며, 비행고도가 높을수록 왜곡현상이 감소함을 알 수 있었다. 또한 왜곡현상의 개선을 위한 DTM(Digital Terrain Model)을 활용하는 원시영상의 해상도를 낮추어 정사영상의 왜곡을 감소시킬 수 있는 방안을 제시하였다. 향후 왜곡 없는 고품질 무인항공기 성과물은 정밀측량분야의 무인항공기 적용 확대에 크게 기여할 것이다.