• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.5
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• pp.397-403
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• 2007

Insect and birds in nature flap their wings to generate fluid dynamic forces that are required for locomotion. To develop a feasible flapping MAV, it is of crucially important to study the fundamental relations between flapping motion and thrust generation. In this paper, the onset conditions of the thrust generation of a heaving flat plate is investigated using a Lattice-Boltzmann method. For a fixed heaving amplitude of h/C=0.5, the effect of reduced frequency on the thrust generation is investigated. For several values of heaving amplitude(h/C=0.25, 0.325, 0.50), the effect of reduced frequency on the thrust generation is also investigated. It can be said that Strouhal number is more important rather than reduced frequency in case of thrust generation. It is found that the critical Strouhal number over which the flat plate starts to produce thrust is around 0.1. Thrust is an exponential function of the Strouhal number.

• Proceedings of the Korean Vacuum Society Conference
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• 2013.02a
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• pp.564-564
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• 2013

홀 추력기는 플라즈마를 이용하는 전기추력기 중 하나로, 인공위성의 자세제어, 궤도수정, 궤도천이 뿐만아니라 행성간 임무수행을 위한 우주선의 엔진으로 사용된다. 홀 추력기 채널 내부에 발생된 Xe 이온들은 양극과 음극 사이에 존재하는 전기장에 의해 가속되어 추력을 발생시킨다. 이때 Xe 이온들은 자기장에 의해 감금된 전자와 중성 Xe 원자 사이의 충돌에 의해 발생하며, 실험적 및 이론적 연구를 통해 단일 전하를 띤 이온(Xe II)뿐만 아니라 다중 전하(Xe III 등)를 띤 이온도 생성되는 것으로 알려져 있다. 이온의 전하량 비율은 홀 추력기의 추력효율 및 연료효율에 영향을 미치며, 다중 전하를 띤 이온의 높은 에너지는 채널벽의 침식문제를 야기하는 등 홀 추력기 이온빔의 전하량 분석 연구는 물리적 연구측면 뿐만아니라 실용적인 측면에서도 매우 중요하다. 본 연구에서는 자기장과 그에 수직한 방향의 전기장에서 발생하는 로렌츠 힘을 이용하여 이온의 전하량을 분석할 수 있는 $E{\times}B$ 탐침을 설계 및 개발하였다. 개발된 $E{\times}B$ 탐침은 70 mm 길이의 집속기와 $148{\times}138{\times}90mm$의 본체, 40 mm길이의 콜렉터로 구성된다. $E{\times}B$ 탐침 설계에 가장 중요한 균일한 자기장 설계를 위해 전산모사를 통해 최적화 작업을 진행하였으며, 실험을 위한 진단계의 최적화와 초기 실험결과가 발표될 예정이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.1
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• pp.10-17
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• 2007

Numerical results from the "figure-of-eight" motion of Phormia-Regina in Part 1 indicate that vortical structure and vortex dynamics do play a critical role in lift and thrust generation. The aerodynamic force generation of insects' wing could be governed by aerodynamic parameters such as Reynolds number; kinematic parameters such as frequency, amplitude, and component of the figure of eight motion; and morphological parameters such as wing shape and the number of wing. In the present work, the effects of Reynolds number, reduced frequency and motion component are investigated in detail to clarify aerodynamic characteristics of insect wing. Through numerical results and their physical interpretation, the mechanism of aerodynamic force generation is presented more clearly. Rotation turns out to be the most important component in thrust generation and subsequent counterclockwise rotational circulation is closely related with thrust generation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.1
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• pp.1-9
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• 2007

Numerical simulation is conducted to investigate aerodynamic force generation mechanism for the "figure-of-eight" motion of Dipteran fly, Phormia-Regina. Wing trajectory is referred to experimental result, which was observed from the tethered flight under freestream condition. Numerical simulation shows that the lift is mainly generated during downstroke motion and the large amount of thrust is generated abruptly at the end of upstroke motion. In the present work, vortical structure in the wake and the pressure field around the airfoil are examined to understand the generation of lift and thrust. Consequently, the lift generation is related with the leading edge vortex which is developed by an effective angle of attack. And the thrust generation can be explained by vortex pairing in the flow field and by vortex staying in the pressure field.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.97-97
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• 2004

현재 KSLV-I에서 탑재부의 Pitch, Yaw, Roll의 3축 제어 및 2단부의 Roll 제어를 위해 사용되는 보조 추진 시스템은 구성이 단순하며, 신뢰성이 높은 것으로 알려져 있는 단일 추진제인 하이드라진을 이용하는 추진 시스템을 고려하고 있다. 이러한 하이드라진 추진 시스템은 추력실 전방에 설치되어 있는 추력기 밸브의 ON/OFF를 이용하여 추력을 조절하게 되는데, 이 때 추력기 밸브의 빠른 작동으로 인해 수격현상에 의한 급격한 압력 상승이 발생하게 되어 구조물의 손상을 발생하게 된다. (중략)

• Proceedings of the Korean Vacuum Society Conference
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• 2016.02a
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• pp.202-202
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• 2016

홀 플라즈마 엔진은 인공위성의 궤도유지 및 자세제어 등의 임무수행이나 우주선의 심우주 활용에 있어 필수적인 핵심 우주 부품이다. 홀추력기 연구개발의 최근 큰 관심사는 추력기의 장시간 운전성 확보 및 방전효율 향상이다. 최근 고리형 홀추력기에서 방전 영역 내 플라즈마와 유전체 벽 간의 충돌을 줄임으로써 전극 손상 및 전자온도 손실을 감소시키기 위한 연구가 활발히 진행되고 있다. 특히 전자석 코일을 활용해 방전 채널 벽면과 평행한 방향의 자기장을 형성하여 플라즈마와 유전체 벽 간의 상호작용을 감소시키는 연구들이 소개되고 있으며, 이러한 방법을 자기차폐(magnetic shielding)라 한다. 본 연구에서는 자기차폐 개념이 적용된 방전 소모전력 500 W급 고리형 홀추력기의 방전 및 추력 발생 특성을 연구하였다. 자기장구조 제어를 통해 유전체 벽과 플라즈마 간 상호작용을 감소시킨 결과, 500 V 수준의 방전 전압에서도 유전체 벽에서의 이차전자 발생에 의한 방전전류의 급격한 증가없이 안정적인 방전이 가능하였으며, 이러한 방전 형태는 기존의 자기차폐 개념이 적용되지 않은 일반 고리형 홀 추력기에서 구현하기 어려운 방전 상태이다. 추력기의 자기장 구조 최적화 조건에서 제논 가스 방전을 통해 얻은 최대 추력은 $22{\pm}1mN$, 비추력 $2200{\pm}70s$, 양극효율 $51{\pm}2%$로 매우 우수한 성능을 보여 주었다

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.92-98
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• 2006

An 1 lbf of NASA standard monopropellant thruster, MRE-1, is used for KOMPSAT (Korea Multi-Purpose Satellite) which is launched in 2006 and provides reliable and cost-effective means for attitude and maneuvering control system. The monopropellant thruster obtains required thrust by thermal decomposition process of propellant through catalyst bed. During firing, the decomposition plays a role of a heat source that may occur an excessive radiation heat transfer to peripheral structures and electronics in relatively low temperature condition.Therefore, the radiation heat shield is needed to prevent the critical radiative heat exchange between thruster and satellite during firing. This paper summarizes an overall development process of radiation heat shield from the design engineering up to the manufacturing.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.8
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• pp.729-736
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• 2009

In order to understand flow characteristics and flight mechanism of hummingbird's flapping flight, two-dimensional numerical analysis is carried out on the flapping motion of hummingbird, Selasphorus rufus. Hummingbird's flapping wing motion is realistically modeled from wind tunnel experimental data to perform numerical analysis. Numerical simulation shows that, as freestream velocity changes, wing trajectory is also adjusted and it substantially affects lift and thrust generation mechanism. According to this tendency, flight domain is separated as "low speed" and "high speed" regime, and each flight domain is studied for physical understanding. As a result, the lift generation during downstroke can be explained by the well-known effects, such as leading edge vortex effect, delayed stall, wake capture and so on. In addition, the lift generation during upstroke, the unique character of hummingbird, is also examined by detailed flow analysis. The thrust generation mechanism is investigated by examining the hummingbird's wing bone structure, vortex generation pattern and the resulting pressure gradient.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.364-367
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• 2011

The development of the DCS thrust unit during the attitude control thruster of the launch vehicle and guided missile is introduced. The DCS thrust unit using solid propellants based on a two-axis control is designed and through the thermo-structural and flow analysis is designed in detail. The performance of the thrust unit based on the detail design is demonstrated through a combustion test.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.40 no.4
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• pp.407-414
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• 2016

As wind turbines are getting larger in size with multi-MW capacity, the blades are getting longer, over 40 m, and hence the asymmetric loads produced during the rotation of the rotor blades are increasing. Some factors such as wind shear, tower shadow, and turbulence have an effect on the asymmetric loads on the blades. This paper focuses on a method of modeling the dynamic load acting on a blade because of thrust variation under wind shear. A method that uses thrust coefficient is presented. For this purpose, "wind shear coefficient of thrust variation" is defined and introduced. Further, we calculate the values of the "wind shear coefficient of thrust variation" for a 2 MW on-shore wind turbine, and analyze them for speeds below the rated wind speed. Then, we implement a dynamic model that represents the thrust variation under wind shear on a blade, using MATLAB/Simulink. It is shown that it is possible to express thrust variations on three blades under wind shear by using both thrust coefficient and "wind shear coefficient of thrust variation."