• 한국전기전자재료학회:학술대회논문집
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• 한국전기전자재료학회 2003년도 하계학술대회 논문집 Vol.4 No.1
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• pp.160-163
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• 2003

This paper describes on anodic bonding characteristics of MLCA(Multi Layer Ceramic Actuator) to Si-wafer using evaporated Pyrex #7740 glass thin-films for MEMS applications. Pyrex #7740 glass thin-films with same properties were deposited on MLCA under optimum RF magneto conditions(Ar 100 %, input power $1\;/cm^2$). After annealing in $450^{\circ}C$ for 1 hr, the anodic bonding of MLCA to Si-wafer was successfully performed at 600 V, $400^{\circ}C$ in - 760 mmHg. Then, the MLCA/Si bonded interface and fabricated Si diaphragm deflection characteristics were analyzed through the actuation test. It is possible to control with accurate deflection of Si diaphragm according to its geometries and its maximum non-linearity is 0.05-008 %FS. Moreover, any damages or separation of MICA/Si bonded interfaces do not occur during actuation test. Therefore, it is expected that anodic bonding technology of MICA/Si wafers could be usefully applied for the fabrication process of high-performance piezoelectric MEMS devices.

• 복식문화연구
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• 제16권3호
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• pp.425-431
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• 2008

The purpose of this study was to observe the changes of skirt length of knitted flare skirts when the seamless test garments were made which had been having full shape while being knitted and to change and amend the challenges in advance when those were knitted. For this study, I made 6 kinds of knitted test garments of wool 100% yarn with seamless knitting machine, which differed from each other by skirt angles ($90^{\circ},\;180^{\circ}$) and gauges (7G, 12G, 15G), and then I measured deflection changes of their length for 2 weeks. Findings and conclusions drawn from this study were as follows: First, the side seam line of full shape hecame somewhat longer than center. Second, 7G and $180^{\circ}$ knitted flare skirt showed the biggest length deflection changes. Third, there was no difference at rear waist deflection changes between front pattern and rear. Fourth, it was difficult to control the tensions of right and left strings as to the knitting directions.

• Advances in aircraft and spacecraft science
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• 제8권1호
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• pp.53-67
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• 2021

The increasing interest in the exploration of Mars stimulated the authors to study aerodynamic problems linked to space vehicles. The aim of this paper is to evaluate the aerodynamic effects of a flapped wing in collaborating with parachutes and retro-rockets to reduce velocity and with thrusters to control the spacecraft attitude. 3-D computations on a preliminary configuration of a blunt-cylinder, provided with flapped fins, quantified the beneficial influence of the fins. The present paper is focused on Aerodynamics of a wing section (NACA-0010) provided with a trailing edge flap. The influence of the flap deflection was evaluated by the increments of aerodynamic force and leading edge pitching moment coefficients with respect to the coefficients in clean configuration. The study was carried out by means of two Direct Simulation Monte Carlo (DSMC) codes (DS2V/3V solving 2-D/3-D flow fields, respectively). A DSMC code is indispensable to simulate complex flow fields on a wing generated by Shock Wave-Shock Wave Interaction (SWSWI) due to the flap deflection. The flap angle has to be a compromise between the aerodynamic effectiveness and the increases of aerodynamic load and heat flux on the wing section lower surface.

• 한국항공우주학회지
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• 제49권3호
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• pp.221-231
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• 2021

본 연구에서는 덕트 팬-상/하부 베인의 제자리 비행 공력 특성에 관한 수치적 연구를 수행하였다. 일정한 회전 속도, 블레이드 콜렉티브 피치각에서 상부 베인 꺾임각 변화에 따른 시스템 구성 요소별 공력 민감도를 분석하였다. 개별 베인 작동 메커니즘과 덕트-베인 공력 상호 간섭의 물리적 특성을 파악하고자 베인의 조종 성능과 덕트 공력하중 분포를 상세히 분석하였다. 마지막으로, 전기체의 조종 성능 개선을 위해 상부 베인의 새로운 작동 메커니즘을 제안하였다. 상부 베인 꺾임각 변화에 따라 상부 베인 측력과 롤링 모멘트는 선형 증가하였으나, 전기체 측력은 덕트에서 작용하는 반력에 의해 현저히 낮게 나타났다. 또한 덕트 수축부 가까이 위치한 상부 베인이 조종 성능 변화에 가장 큰 역할을 하였다. 덕트와 상부 베인 흡입면의 공력 상호 간섭에 의해 덕트의 음압이, 덕트와 상부 베인의 압력면 공력 상호 간섭에 의해 압력 회복이 발생하여 덕트의 비대칭 공력 증가의 원인이 되었다. 4개의 상부 베인을 0°로 고정시키거나 제거했을 때, 덕트의 비대칭 공력은 감소하고, 전기체의 롤링 모멘트는 80%까지 증가하여 공력 성능이 개선되었다.

• Advances in aircraft and spacecraft science
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• 제4권5호
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• pp.503-514
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• 2017

The attitude control of an aircraft is usually fulfilled by means of thrusters at high altitudes. Therefore, the possibility of using also aerodynamic surfaces would produce the advantage of reducing the amount of fuel for the thrusters to be loaded on board. For this purpose, Zuppardi already considered some aerodynamic problems linked to the use of a wing flap in a previous paper. A NACA 0010 airfoil with a trailing edge flap of 35% of the chord, in the range of angle of attack 0-40 deg and flap deflections up to 30 deg was investigated. Computer tests were carried out in hypersonic, rarefied flow by a direct simulation Monte Carlo code at the altitudes of 65 and 85 km of Earth Atmosphere. The present work continues this subject, considering the same airfoil and free stream conditions but two flap extensions of 45% and 25% of the chord and two flap deflections of 15 and 30 deg. The main purpose is to compare the influence of the flap dimension with that of the flap deflection. The present analysis is carried out in terms of: 1) percentage variation of the global aerodynamic coefficients with respect to the no-flap configuration, 2) increment of pressure and heat flux on the airfoil lower surface due to the Shock Wave-Shock Wave Interaction (SWSWI) with respect to the same quantities with no SWSWI or in no-flap configuration, 3) flap hinge moment. Issues 2) and 3) are important for the design of the mechanical and thermal protection system and of the flap actuator, respectively. Under the above mentioned test and geometrical conditions, the flap deflection is aerodynamically more effective than the flap extension, because it involves higher variation of the aerodynamic coefficients. However, tests verify that a smaller deflection angle involves the advantage of a smaller increment of pressure and heat flux on the airfoil lower surface, due to SWSWI, as well as a smaller hinge moment.

• 대한토목학회논문집
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• 제29권2D호
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• pp.295-303
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• 2009

본 연구에서는 가이드웨이의 특성이 중저속 자기부상열차의 주행성에 미치는 영향을 파악하는데 목적을 두고 있다. 이를 위하여 자기 공극의 피드백을 포함한 2자유도 차량에 대한 운동방정식을 구성하고, 최적능동제어기법을 적용하여 수치해석을 수행하였다. 매개변수 연구로 차량 속도, 레일조도, 교량 처짐, 경간의 연속성, 경간장 등이 UTM-01 자기부상열차의 응답에 미치는 영향을 파악하였다. 해석 결과를 보면, 차량 설계속도 내에서는 차량의 응답이 크게 증가하지 않고 일정한 수준을 유지하였으며, 차량의 응답은 주로 가이드웨이 처짐에 의하여 지배를 받은 것으로 나타났다. 결론적으로 차량 공극의 변화를 줄여서 주행성을 향상시키려면 가이드웨이의 최대 처짐을 작게 하고, 단순거더 보다는 연속거더 구조로 구성하는 것이 유리한 것으로 나타났다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.525-530
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• 2003

This paper is concerned with a control allocation strategy using the dynamic inversion which generates the nominal control input trajectories, and autopilot design using the time-varying control technique which is time-varying version of pole placement of linear time-invariant system for an agile missile with aerodynamic fin and thrust vectoring control. Dynamic inversion can decide the amount of the deflection of each control effector, aerodynamic fin and thrust vectoring control, to extract the maximum performance by combining the action of them. Time-varying control technique for autopilot design enhance the robustness of the tracking performance for a reference command. Nonlinear simulations demonstrates the dynamic inversion provides the effective nominal control input trajectories to achieve the angle of attack command, and time-varying control technique exhibits good robustness for a wide range of angle of attack.

• International Journal of Aerospace System Engineering
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• 제4권1호
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• pp.1-8
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• 2017

This paper proposes the load distribution control allocation technique. The proposed method is designed by combining a conventional control allocation method with load distribution ability in order to reduce the stress acting on ailerons. By designing the weighting matrix as a function of the load distribution rule, the optimal deflection angles of each surface to satisfy both control goal and load distribution can be achieved. Moreover, rule based fault-tolerant control technique is also proposed. The rules are generated by considering both dominant control surfaces and the ratio of load distribution among surfaces. The performance of the proposed method is evaluated through numerical simulations.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2013년도 춘계학술대회 논문집
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• pp.347-352
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• 2013

Seoul National University Flap (SNUF) blade is a small-scaled rotor blade incorporating a small trailing-edge flap control surface driven by piezoelectric actuators at higher harmonics for vibration attenuation. Initially, the blade was designed using two-dimensional cross-section analysis and a geometrically exact one-dimensional beam analysis, and material configuration was finalized. Flap deflection angle of ${\pm}45^{\circ}$ was established as the criterion for better vibration reduction performance based on an earlier simulation. Flap linkage mechanism design is carried out and static bench tests are conducted to verify the flap actuation mechanism performance. Different versions of test beds are developed and tested with the flap and chosen APA 200M piezoelectric actuators. Through significant improvements, a maximum deflection of ${\pm}3.7^{\circ}$ was achieved. High frequency experiments are conducted to evaluate the performance and transfer function of the test bed is determined experimentally. As the static tests are almost completed, rotor power required for testing the blade in whirl tower (centrifugal environment) is calculated and further preparations are under way.

• Structural Engineering and Mechanics
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• 제87권6호
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• pp.615-624
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• 2023

The focus of this study is on the structural behaviour of reinforced concrete beams in which basalt fiber and SBR latex were added and the cement was partially replaced with 10% of hypo sludge. Eight different mixes of reinforced beam specimens were tested under static loading behaviour. The experiments showed, the structural behaviour with features such as load-deflection relationships, crack pattern, crack propagation, number of crack, crack spacing and moment curvature. A stress-strain relationship to represent the overall behavior of reinforced concrete in tension, which includes the combined effects of cracking and mode of failure along the reinforcement, is proposed. The structural behaviour results of reinforced concrete beams with various types of mix were tested at the age of 28 days. The investigation revealed that the flexural behaviors of hypo sludge reinforced concrete beams with addition of basalt fiber and SBR latex was higher than that of control concrete reinforced beam. The specimen (LHSBFC) with 10% hypo sludge, 0.25% Basalt fiber and 10% SBR latex showed an increase of 5.08% load carrying capacity, 7.6% stiffness, 3.97% ductility, 31.29% energy dissipation when compared to the control concrete beam. The analytical investigation using FEM shows that it was in good agreement with the experimental investigation.