• 한국항공우주학회지
• /
• 제33권7호
• /
• pp.40-50
• /
• 2005

본 논문에서는 이중 로터 풍력 발전 시스템에 대한 모델링 및 성능 예측 결과를 제시하였다. 공력 모델은 블레이드 요소 및 모멘텀 이론에 근거하였으며, 시스템 동역학 모델은 다몸체 역학을 적용하였다. 이중 로터 풍력 발전 시스템의 정상 상태는 물론 이중 여자 유도 발전기를 탑재한 발전 시스템에 대하여 풍속 변화에 따른 과도 응답을 분석하였고, 로터 회전수 및 발전 출력 제어를 위하여 주 및 보조 로터의 피치각 제어 전략의 도출 및 비선형 시뮬레이션 결과를 제시하였다.

• 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.

• 터널과지하공간
• /
• 제4권3호
• /
• pp.256-260
• /
• 1994

HLW canister array was designed by FLLSSM program, considering the thermal concentration. Rock properties were chosen as those of granite, the most possible bedrock for the repository in Korea. It was shown that repository area and excavation volumes can be determined by the pitch or distance between canisters. Pitch can be reduced to 0.6 m assuming the tolerance temperature as 200$^{\circ}C$. Thermal concentration was reduced as storage time for cooling the canister passed. After 10 years of storage the thermal problems seemed to be negligible.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
• /
• 한국우주과학회 2009년도 한국우주과학회보 제18권2호
• /
• pp.43.2-43.2
• /
• 2009

Electron microbursts are the intense electron precipitation which durations are less than one second. We measured the energy spectra of the microbursts from 170 keV to 340 keV with solid state detectors aboard the low-altitude (680km), polar-orbiting Korean STSAT-1 (Science and Technology SATellite). The data showed that the loss cone at these energies is empty except when microbursts abruptly appear and fill the loss cone in less than 50 msec. This fast loss cone filling requires pitch angle diffusion coefficients larger than ~ 10-2rad2/sec, while ~10-5 rad2/sec was proposed by a wave particle interaction theory. We recalculated the diffusion coefficient, and reviewed of electron microburst generation mechanism with test particle simulations. This simulation successfully explained how chorus waves make pitch angle diffusion within such short period. From considering the resonance condition between wave and electrons, we also showed ~ 100 keV electrons could be easily aligned to the magnetic field, while ~ 1MeV electrons filled loss cone partially. This consideration explained why precipitating microbursts have lower e-folding energy than that of quasi-trapped electrons, and supports the theory that relativistic electron microbursts that have been observed by satellite in-situ measurement have same origin with ~100 keV electron microbursts that have been usually observed by balloon experiments.

• Carbon letters
• /
• 제16권1호
• /
• pp.25-33
• /
• 2015

The prime objective of this research was to study the influence of hot-pressing pressure and matrix-to-reinforcement ratio on the densification of short-carbon-fiber-reinforced, randomly oriented carbon/carbon-composite. Secondary objectives included determination of the physical and mechanical properties of the resulting composite. The 'hybrid carbon-fiber-reinforced mesophase-pitch-derived carbon-matrix' composite was fabricated by hot pressing. During hot pressing, pressure was varied from 5 to 20 MPa, and reinforcement wt% from 30 to 70. Densification of all the compacts was carried at low impregnation pressure with phenolic resin. The effect of the impregnation cycles was determined using measurements of microstructure and density. The results showed that effective densification strongly depended on the hot-pressing pressure and reinforcement wt%. Furthermore, results showed that compacts processed at lower hot-pressing pressure, and at higher reinforcement wt%, gained density gradually during three densification cycles and showed the symptoms of further gains with additional densification cycles. In contrast, samples that were hot-pressed at moderate pressure and at moderate reinforcement wt%, achieved maximum density within three densification cycles. Furthermore, examination of microstructure revealed the formation of cracks in samples processed at lower pressure and with low reinforcement wt%.

• 설비공학논문집
• /
• 제9권2호
• /
• pp.180-188
• /
• 1997

The theoretical analysis and experiment with simulator were performed to obtain the temperature distributions in radiant heating panel and heat supply from hot water to heating space for the purpose of the development of comfortable living space from a point of view of the improvement of air quality and the enhancement of system efficiency. The relations of various parameters, such as pipe pitch, room temperature as well as flow rate and temperature of hot water and so on, with the rate of heat supplied, mean temperature and maximum temperature difference at panel surface were discussed. The effects of these parameters were also verified on the thermal performance of heating panel using the relations which could be used for the optimal design and operation of the radiant heating panel.

• International Journal of Aeronautical and Space Sciences
• /
• 제3권2호
• /
• pp.13-23
• /
• 2002

In this paper, we present a sliding mode control strategy for the re-orientation maneuver of rigid spacecraft containing rotating wheels. The wheels are considered as internal devices, and external inputs are employed for generation of control commands. The formulation is developed for a general case while particular example is applied to pitch bias momentum spacecraft with a single momentum wheel. The resultant control commands are used to take the gyroscopic effects into account which are caused by the rotating wheels. The controller designed demonstrates that the nutational motion of the pitch bias momentum spacecraft is effectively controlled. It is also assumed that the external control torque device is of on-off nature, and pulse width modulation technique is applied to construct proper control torque history.

• International Journal of Aeronautical and Space Sciences
• /
• 제9권1호
• /
• pp.129-136
• /
• 2008

An roll-pitch-yaw integrated autopilot for missiles is designed for compensation of dynamics coupling. The proposed autopilot is based on the classical control technique. The gains of the proposed autopilot are optimized by using co-evolutionary augmented Lagrangian method(CEALM). Several cost functions are compared in order to find feasible control gains. For a case that a bank angle of missiles is unknown, multiple models are used in the autopilot optimization. In nonlinear simulations as well as linear simulations, the proposed autopilot provided good performances.

• 대한치과의사협회지
• /
• 제51권10호
• /
• pp.551-555
• /
• 2013

The purpose of this study was to give a guideline for selecting the nickel-titanium (NiTi) file by review from many studies. Since the early 1990s, several instrument systems manufactured from NiTi have been introduced into endodontic practice. The specific design characteristics vary, such as tip shape and size, cross sectional view, helix angle, and pitch space. Some of the early systems have been removed from the market or play only minor roles; others are still widely used. New designs continually are produced, but the extent to which clinical outcomes will depend on design characteristics is difficult to forecast. In this study, I have reviewed the different design characteristics in respect of the safety and efficiency. With the review from many studies, I concluded that the clinicians must be understand the specific design characteristics for selecting the ideal NiTi rotary instruments.

• 한국항공우주학회지
• /
• 제33권9호
• /
• pp.73-80
• /
• 2005

본 논문은 피치 바이어스 모멘텀 방식을 사용하는 HAUSAT-2 위성의 모멘텀 휠 초기구동(Start-up)을 위한 방안을 연구 분석하고 초소형위성 HAUSAT-2에 적합한 새로운 초기구동 방법을 제안하였다. HAUSAT-2는 25kg급의 나노 위성으로 모멘텀 휠과 마그네틱 토커를 사용하여 3축 제어를 수행한다. 자세제어를 위해 모멘텀 휠은 공칭 속도로 회전하거나 회전속도가 변하게 된다. 모멘텀 휠을 장착한 위성에서 휠의 초기구동방법은 휠을 발사 전에 미리 일정한 속도로 회전하게 하거나, 궤도상에서 추력기와 같은 구동기로 자세를 안정화 시킨 이후에 휠을 공칭속도에 도달하게 하는 방법이 있다. 하지만 HAUSAT-2와 같은 초소형위성의 경우 전력제한으로 발사 전 휠을 구동하기 힘들며, 궤도상에서 자세 안정화 이후 휠을 구동하기 위해서는 자기토커만으로 자세를 안정화 해야 하는데 이 경우 시간이 오래 걸리는 단점이 있다. 따라서 본 논문에서는 좀더 빠르고 효율적으로 휠의 초기구동과 자세안정화를 하기 위해서 모멘텀 휠 구동 방안을 제안하였다. 이 방법은 위성이 발사체에서 분리된 후 초기 각속도 제어를 할 때 일정한 속도 증가율로 모멘텀 휠의 속도를 올려주어 공칭 속도에 도달하게 하며, 이 후 자세 안정화를 수행하게 된다. 이 방식을 사용하면 약 4 궤도 이내에 휠 초기구동과 자세 안정화를 성공적으로 이룰 수 있음을 확인 할 수 있었다.