• 한국농업기계학회:학술대회논문집
• /
• 한국농업기계학회 2000년도 THE THIRD INTERNATIONAL CONFERENCE ON AGRICULTURAL MACHINERY ENGINEERING. V.II
• /
• pp.117-123
• /
• 2000

Using the modified DEM (Discrete Element Method), which we proposed in order to improve the accuracy of the simulation, soil behavior and reaction by lugs of rotating wheel and a soil cutting process by a high speed blade were calculated and compared with experimental data. The DEM is one of computational mechanics, where the object body is supposed as an assembly of small particles called elements and not a continuum as in the case of FEM. We can easily treat some discrete phenomena such as cracking, separating and sliding by the DEM. We had to modify the original mechanical model, which induced too free movement of elements, adding a tension spring, which would display the role of soil adhesion. The results of DEM simulations were successful from both the soil behavior and reaction points of view.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2014년도 추계학술대회 논문집
• /
• pp.173-174
• /
• 2014

Vibration disturbances generated by reaction wheels may cause serious problems in high precision pointing spacecraft missions. Implementation of vibration isolator is a practical solution to meet the high pointing stability requirement placed on precision payloads. In this paper, development of hybrid vibration isolator that combines passive and active component is described. Vibration isolation performance of the developed isolator is evaluated using reaction wheel disturbance model. Hybrid isolation results obtained using FxLMS algorithm show clear improvement compared to the results obtained using only passive means.

• 한국철도학회:학술대회논문집
• /
• 한국철도학회 2009년도 춘계학술대회 논문집
• /
• pp.1468-1472
• /
• 2009

This paper presents the influence of the airgap tolerance on performance of a linear induction motor. Construction tolerance of the plate affects directly to the cost and performance of the Linear metro. LIM has around 10[mm] large airgap with many restrictions such as construction tolerance, thermal expansion and bend of the reaction plate, abrasion of the wheel, and so on. In order to have steady performance, the airgap should be uniform. But it is impossible to maintain the secondary reaction plate be flat along with the long track. Therefore the influence of the flatness on performance of a LIM should be investigated.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2006년도 춘계학술대회논문집
• /
• pp.376-379
• /
• 2006

Reaction Wheel Assembly (RWA) is one of the major disturbance sources that have influence upon the Line of Sight (LOS) of payload. A micro-vibration induced by RWA is propagated through the satellite structure and decrease the LOS stability performance of payload. This effect shall be analyzed through the jitter analysis. If a requirement or specification of payload jitter level is found to be not satisfied according to the jitter analysis campaign, some modification or redesign should be done on the satellite structure or a couple of isolator should be attached on the RWA interface in order to reduce the transmitted vibration level of RWA. The purpose of ???RWA isolator test? is to roughly evaluate the performance of vibration suppression level with a passive RWA isolator made of rubber. For this test, actual RWA is used as a vibration source and a couple of cube-shaped rubber mount designed for satellite is used as a passive isolator. There may be several considerations in order to accommodate RWA isolator to spacecraft such as not only vibration reduction performance but also thermal conduction problem, mechanical size, RWA alignment problem, etc. But in this report the feasibility of RWA isolator is analyzed only in a vibration suppression point of view. As a result, high frequency vibration of RWA above 50Hz is perfectly attenuated with isolators, however, first harmonic components below 50Hz became larger due to the additional low frequency resonance modes of roll, pitch, yaw rigid body motion of RWA+bracket.

• 한국자동차공학회논문집
• /
• 제25권2호
• /
• pp.167-178
• /
• 2017

The steering wheel of a vehicle has a typical characteristic of automatically returning to its neutral state when the driver releases it. Steering returnability originated from the tire forces and kingpin moments. It is proportional to the reaction torque that is generated through the rack and column, which are dependent on suspension and steering geometry. It is also important to accurately predict and design it because steering returnability is related to steering performance. In this study, a detailed multibody dynamics model of a vehicle was designed by using ADAMS/Car and simulated for steering returnability. In addition, a tolerance analysis of the chassis system in terms of part dimension and properties has been performed in order to minimize the design parameters. The sensitivity of the selected design parameters was then analyzed via Design of Experiments(DOE). As a result, we were able to obtain the main parameters through a contribution analysis. It can be used to predict steering returnability and improve its performance, which is represented by the angle of restoration and laterality.

• 한국자동차공학회논문집
• /
• 제14권4호
• /
• pp.12-19
• /
• 2006

It is positively necessary to study on the stiffness of a 13degree-type impact tester in order to improve the fracture prediction of impact testing in wheels using FE(finite-element) analysis. The 13degree-type impact tester consists of an impact striker, a wheel fixer, a steel plate, and four cylindrical rubbers. Important parts of the tester are the steel plate and four cylindrical rubbers which play a role of absorbing impact energy during impact testing. Because of these buffers, the RF(reaction force) variation of the lower part in the 13degree-type impact tester showed the tendency like a damped harmony oscillation during impact testing. In order to investigate the stiffness of a 13degree-type impact tester, this work measured each stiffness of a steel plate and cylindrical rubbers. The stiffness of a cylindrical rubber was measured using a compressive tester. On the other hand, the stiffness of a steel plate was predicted by simulating experimental method using FE analysis.

• Journal of Welding and Joining
• /
• 제17권3호
• /
• pp.79-89
• /
• 1999

The study was carried out to examine in more detail metallurgical and mechanical properties of brazed joints of diamond cutting wheel. In this work, shank(mild steel) and sintered bronze-base tips were brazed with three different filler materials(W-40, BAgl and BAg3S). The machine used in this work was a high frequency induction brazing equipment. The joint thickness, porosities and microstructure of brazed joints with brazing variables(brazing temperature, holding time) were evaluated with OLM, SEM, EDS and XRD. Bending(torque) test was also performed to evaluate strength of brazed joints. Further wetting test was performed in a vacuum furnace in order to evaluate the wettability of filler metals on base metals9shank and tips). The brazing temperature had a strong influence on the joint strength and the optimum brazing temperature range was about $700~850^{\circ}C$ for the bronze/steel combinations. The strength of the brazed joint was found to be influenced by the three factors : degree of reaction region, porosity content, joint thickness. The reaction region was formed in the bronze-base tip adjacent to the joint. The reaction region resulted in a bad influence on the strength due to the formation of Cu5.6Sn, CuZn4, $\beta(CuZn)$ and CdAg, etc. Porosities increased as brazing variables(brazing temperature, holding time) increased, and the brazed joints with porosities of less than about 3-5% had an optimum strength for the bronze-base tip.

• 한국항공우주학회지
• /
• 제48권2호
• /
• pp.147-158
• /
• 2020

본 논문에서는 저궤도 위성에서 추력기를 이용하여 반작용휠 모멘텀을 덤핑하는 방법에 대해서 살펴본다. 추력기를 사용한 모멘텀 덤핑은 주로 정지궤도위성에서 사용되는데 특정 시간에만 추력기로 자세제어와 모멘텀 덤핑을 동시에 수행하는 방식으로 이뤄진다. 저궤도 위성은 수시로 모멘텀 덤핑을 해야 하므로 정지궤도위성의 방식을 사용하는 것은 바람직하지 않다. 본 연구에서는 저궤도 위성에 적용 가능하도록 항상 추력기로 모멘텀 덤핑을 수행하고 덤핑 시의 자세제어는 반작용휠로 수행하는 방법을 살펴본다. 추력기의 밸브 개폐횟수를 줄이기 위해서 최대 크기의 펄스로 추력기를 구동하는 방법을 제안한다. 추력기로 인해 자세오차가 크게 증가하는 것을 방지하기 위해서 추력기의 구동 간격을 조정하였다. 시뮬레이션을 통해서 본 논문에서 제안한 방법의 효과를 검증하였다.

• 한국항공우주학회지
• /
• 제46권9호
• /
• pp.760-766
• /
• 2018

위성에 작용하는 외란으로 인해서 반작용휠에 원치 않는 모멘텀이 쌓인다. 이를 해소하기 위해서 위성의 축방향으로 설치한 세 개의 자기토커를 이용한다. 자기토커는 지구 자기장과 상호 작용하여 간접적으로 토크를 생성한다. 따라서 모멘텀 덤핑시 자기토커와 자기토커 주위에 형성되는 지구 자기장을 동시에 고려해야 한다. 높은 경사각을 가지는 저궤도 위성이 지구지향을 할 때 위성체의 피치축으로는 매우 약한 지구자기장이 형성된다. 이 경우 하나의 자기토커에 과부하가 걸려서 모멘텀 덤핑 성능이 떨어진다. 본 연구에서는 자기토커의 배치를 변경하여 지구지향자세에서 모멘텀 덤핑 성능을 향상시키는 방법에 대해서 살펴본다.

• 한국항공우주학회지
• /
• 제47권5호
• /
• pp.371-378
• /
• 2019

정밀지향위성은 반작용휠로 자세제어를 수행하며, 반작용휠의 모멘텀 덤핑은 3개의 자기토커로 이뤄진다. 본 논문에서는 자기토커 고장 시의 모멘텀 덤핑 영향성에 대해서 살펴본다. 높은 경사각을 가지는 궤도에 위치한 위성이 지구지향자세를 유지하고 있을 때 피치축 방향 자기토커가 고장나면 모멘텀 덤핑이 불가능하다. 하지만 다른 방향의 자기토커가 고장나면 성능 저하만 있을 뿐 모멘텀 덤핑은 여전히 가능하다. 피치축 방향의 자기토커가 고장났을 때도 위성자세변화를 통해서 모멘텀 덤핑을 할 수 있다. 또한 자기토커 배치를 변경하면, 어느 자기토커가 고장나더라도 모멘텀 덤핑이 항상 가능하다.