Aircraft noise is something humans don't want. In this study, based on the Rotax 914 engine used in Korea, the propeller blade angle was changed by 1 degree and the engine RPM was changed to review the three-wing “G Company” propeller and the three-wing GSC wooden propeller. Select the best propeller pitch angle by measuring the change in propeller noise and thrust and the change in engine RPM due to the change in noise and thrust. We would like to present a propeller pitch angle suitable for the location of the airfield and the operation of the aircraft. Based on this, we would like to help resolve noise complaints around the airfiled.

In order to solve the problem of improper thrust distribution of each thruster of underwater vehicle, the PSO optimization algorithm is used to solve the problem of thrust distribution. According to the spatial layout of the thruster, the algorithm model of the underwater vehicle propulsion system is established. The thrust input is carried out under the broken line search trajectory, and the simulation verifies the thrust allocation results of the PSO algorithm and the traditional pseudo-inverse method. The simulation results show that compared with the traditional algorithm. First of all, the PSO algorithm can set the physical threshold for each thruster to prevent the thruster from having too much thrust. Secondly, it can ensure that the thruster can turn with a reasonable torque to prevent the robot from drifting due to the large thrust gap. This paper provides a theoretical reference for thrust distribution of underwater salvage robot, and has practical engineering significance.

Most domestic pilots are trained at local airfields using propeller aircraft. Training aircraft are mainly trained in the airspace around the aerodrome, and mainly take-off and landing exercises that require a lot of practice among flight control skills. Aircraft noise is a sound that humans do not want. In this study, based on the Rotax 914 engine used in Korea, the propeller blade angle was changed by 1 degree for the 3-leaf “K company” propeller and the 3-leaf GSC wooden propeller, and the engine RPM was changed to examine the noise and thrust changes. The purpose of this study is to check whether noise and thrust loss are the least at the engine's maximum RPM, and to propose an aircraft operation plan in the noisy aerodrome area based on the values.

프로펠러축은 프로펠러 하중 및 편심추력의 영향으로 인해 정적, 동적, 과도상태 각각 거동의 패턴이 달라져 선미관 후부베어 링의 국부하중 변화를 일으킴으로써 선박 축계의 안정성에 큰 영향을 미치며, 결과적으로 축 지지 베어링의 손상위험을 증가시킨다. 이를 방지하기 위한 일련의 축계정렬연구는 선급강선규칙과 조선소 지침을 기반으로 준정적 상태에서 축과 선미관 베어링간의 상대적 경사각 과 유막유지, 선체변형에 따른 영향평가를 최적화 하는데 중점을 두어 진행 되어왔다. 그러나 보다 진일보한 형태의 추진축계의 안정성을 보장하기 위해서는 조타장치의 전타시 발생하는 급격한 선미유동장 변화와 같은 과도동적상태변화 조건에서의 상세 연구가 필요하다. 이 러한 관점 하에 본 연구에서는 50,000 DWT 중형 유조선을 대상으로 스트레인 게이지법과 변위센서을 이용하여 선박운전 중 대표적 과도 상태인 좌현 전타시의 프로펠러 축 거동이 선미관 베어링에 미치는 영향을 교차검증한 결과, 프로펠러 편심추력변동이 선미관 베어링의 하중을 일시적으로 저감시켜 베어링 하중을 완화시키는 것을 확인하였다.

Phaya-Thon-Zu temple has a unique architectural style connected by the three temples, and cultural values are highly as murals remain on some of the walls. However, various damages in internal walls and vaults have occurred due to earthquake and environmental influences. In order to analyze these damages, accurate structural analysis is required, but structural modeling is difficult, because Phaya-Thon-Zu temple is the complex masonry structure which is stacked with small bricks. Therefore, this study intends to analyze the causes of damages by examining collapse mechanism for cross section and longitudinal section of vaults in the entrance hall and shrine by using thrust line analysis, which is a geometric method, and to compare it with the actual damage situation.

The axial thrust acting on the turbocharger rotor is basically generated by the unbalance between turbine wheel gas forces and compressor wheel air forces. It has a significant influence on the friction losses, which reduces the overall efficiency and performance of high-speed turbocharger. Therefore, it’s important to calculate the thrust forces under operating conditions (surge, choke and etc.) in a turbocharger. The purpose of this paper is the development of numerical simulation methods which were verified by experimental results of axial thrust and thermally induced constraint tests of the turbocharger. The first FE model showed the relationship between thrust forces and strains by calculating the strains on specially designed thrust bearing and were compared with test results. And the second one is to identify the thermally induced strains in order to remove the thermal effects from measured strains. With these models, it’s possible to inversely predict the magnitudes of the axial thrust by directly measured strains and temperatures under operating turbocharger.

In this paper, the main objective is to determine the mechanical responses due to the axial forces on thrust bearing for an automotive turbocharger. The rotating shaft in a turbocharger is supported by the bearings, usually oil-lubricated radial journal bearings and a thrust bearing. The axial forces acting on the thrust bearing have significant influences on the mechanical friction losses, which reduces the efficiency and performance of high-speed turbocharger. There are simple well-known formulas such as Petroff’s equation for calculating the mechanical frictional losses in these types of bearings. However, it's difficult to estimate the accurate axial forces from this formula. Thus, this work determined the relationship between thrust forces and strains by measuring and calculating the strains on thrust bearing and compared both results. The result shown that behaviors of axial strain are changed linear and non-linear depend on the boundary condition. Therefore, it’s possible to predict the magnitudes of the axial forces by measuring the strains under operating turbocharger.

사고선박의 2차적인 피해를 줄이기 위해서는 사고선박을 안전한 곳으로 이동시키기 위한 예인선의 소요마력 산출이 요구되며, 길이 93 m 여객선형 대상선박에 대한 실선실험을 통하여 소요마력 산출에 대한 이론적인 계산식의 유효성을 검증하였다. 실선실험 결과는 이론계산 결과와 비교해 볼 때 상당히 일치되어 예선의 소요마력 산정을 위해 사용하기에 충분하다고 판단되며, 정적저항에서 공기저항, 마찰저항, 잉여저항과 더불어 프로펠러 고착저항이 상대적으로 큰 값으로 평가되었다. 피예인선은 예인과정에서 좌우 측면으로 30°정도까지 스윙운동 및 요우잉이 발생하였으며, 이로 인한 동적저항이 큰 값으로 평가되었다. 추후 안전율에 대한 연구가 필요할 것으로 판단되며, 저항의 정확한 예측을 통하여 안전율을 최소화함으로써 경제적인 예인선의 사용이 가능할 것으로 판단된다.

In neutron beam research, it is necessary for the shielding block and experimental equipment a dance floor in a nuclear reactor to travel in a fixed direction with little friction. However, precise travel is difficult to achieve due to factors such as vibration or gear backlash. We have imported air bearings from more developed nations to perform the role of moving instruments. In the beginning, an air bearing for use in three-dimensional measuring instruments similar to an air bearing was used; however, the performance was found to be insufficient. Accordingly, we collected data and conducted reverse engineering on this type of thrust pad. Through this process, it was confirmed that two issues were influencing the performance: the slant of the bottom of the air bearing and the bottom outside edge of the air bearing plate. The air bearing begins to move at 5 bar and moves smoothly without interruption at 7 bar. The result of this process was the development of a thrust pad which is superior in performance to the imported product and is being used in neutron beam research. We anticipate that this air bearing which has been developed will be used for experimental equipment which requires this type of precision in the future.

선체구조 부재에는 이중저의 거더 및 늑판등에서 유공을 가진 판이 많이 사용되고 있는데, 이는 중량 경감, 사람 및 화물의 이동, 배관 등의 목적이다. 보통은 강도상 큰 문제가 없는 부위에 위치하지만, 매로는 불가피하게 높은 응력이 작용하는 부위에 설치해야 할 경우가 있다. 이러한 판에 유공의 존재는 면내 하중에 의한 탄성좌굴강도 및 최종강도에 큰 영향을 주게 된다. 따라서, 유공판의 탄성좌굴강도 및 최종강도 평가는 선박의 초기 구조설계단계에서 구조부재 치수를 결정할 매, 검토해야 할 중요한 설계기준 중의 한가지가 된다. 그러므로, 유공판에 대한 합리적이고 신뢰적인 탄성좌굴강도 및 최종강도 설계식이 필요하게 되었다. 본 연구에서는 다양한 종횡비와 유공의 치수비 그리고 세장비의 영향을 고려하여 탄소성대변형 유한요소법을 근간으로 한 해석코드인 ANSYS(7.1)를 사용하여 시리즈해석을 수행하였다.

지금까지의 강구조설계에서는 일반적인 탄성좌굴개념을 적용하고 있다. 왜냐하면 현재까지의 실적선의 데이터와 경험적인 방법에 의해 도출된 여러 가지 룰에 의한 데이터가 상당히 신뢰할만한 정도를 갖고 있기 때문이라고 판단하기 때문이다. 그러나, 최근들어 판두께가 박판인 고장력강재가 선체에 폭넓게 사용되어지면서 탄성좌굴발생 시점이 빨라졌으며 이에따른 탄소성거동을 정확히 예측할 필요성이 대두되고 있다. 이에 본 연구에서는 선체의 이중저 판넬구조에서 압축하중을 받을때의 실제판부재의 주변지지조건을 네가지로 이성화하여 해석하였으며, 이때 실제 필연적으로 존재하게 되는 열가공에 의한 비대칭형 초기처짐을 적용하였고, 비선형해석기법으로서는 Arc-length method를 적용하였고 해석코드는 범용유한요소법 소프트웨어로 잘 알려진 ANSYS를 사용하였다.

The purpose of this study was to identify the influence of wedged insole and foot progression angle (FPG) on lateral thrust of knee in healthy subjects. Fifteen healthy male subjects were recruited from Suncheon First College, in Suncheon. The subjects randomly walked at the comfortable velocity under five conditions: bare footed, medio-lateral wedged insoles, toe-in and toe-out gait. The lateral thrust was measured by a accelerometer with telemeter during walking. Data was collected while each subject walked for about 10 gait cycle on a flat, level walkway at their normal speed. The middle three gait cycle were used for averaged peak value of lateral acceleration. The three averaged peak value of lateral acceleration were collected under each condition at heel strike. The results showed that averaged peak value of lateral acceleration increased significantly in medial wedged insole and toe-in gait and decreased significantly in lateral wedged insole and toe-out gait as compared with bare footed (p<.05). These results suggest that wedged insole as well as walking strategy, such as foot progression angle, may prevent progression of degenerative knee osteoarthritis.

좁은 틈새를 가진 원판밸브의 추력에 대한 이론적 해석 및 실험 결과로부터 다음과 같이 요약할 수 있다. 1. 원판 밸브의 틈새가 비교적 작은 경우(H/D sub(1)가 0.1 이하) 즉, 유량이 적을 때에는 점성류가 지배적이고 이론식으로부터 추력을 높게 예측할 수 있었다. 2. 압력의 영향에 대한 추력은 입구 압력이 낮을수록 이론결과와 실험결과가 잘 일치하고 높을수록 관성의 영향이 크게 나타나는 경향을 보였다. 3. 밸브 크기 변화에 대한 추력의 영향은 D sub(2)/D sub(1)=>4.6에서는 포물선적으로 감소하고 그 이하에서는 직선적으로 감소하였다.

To prepare for a future Korean lunar orbiter mission, semi-optimal lunar capture orbits using finite thrust are designed and analyzed. Finite burn delta-V losses during lunar capture sequence are also analyzed by comparing those with values derived with impulsive thrusts in previous research. To design a hypothetical lunar capture sequence, two different intermediate capture orbits having orbital periods of about 12 hours and 3.5 hours are assumed, and final mission operation orbit around the Moon is assumed to be 100 km altitude with 90 degree of inclination. For the performance of the on-board thruster, three different performances (150 N with Isp of 200 seconds, 300 N with Isp of 250 seconds, 450 N with Isp of 300 seconds) are assumed, to provide a broad range of estimates of delta-V losses. As expected, it is found that the finite burn-arc sweeps almost symmetric orbital portions with respect to the perilune vector to minimize the delta-Vs required to achieve the final orbit. In addition, a difference of up to about 2% delta-V can occur during the lunar capture sequences with the use of assumed engine configurations, compared to scenarios with impulsive thrust. However, these delta-V losses will differ for every assumed lunar explorer's on-board thrust capability. Therefore, at the early stage of mission planning, careful consideration must be made while estimating mission budgets, particularly if the preliminary mission studies were assumed using impulsive thrust. The results provided in this paper are expected to lead to further progress in the design field of Korea’s lunar orbiter mission, particularly the lunar capture sequences using finite thrust.