• Journal of Satellite, Information and Communications
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• v.12 no.1
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• pp.58-63
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• 2017

In this paper, Easily the nation's rapidly expanding and the popularization of unmanned aerial vehicle drone can fly. But in Korea, divided country to cameras lately, and national characteristics and constraints in many relevant laws and in particular, address public concerns.Appears, along with many. Unmanned aircraft drone called industrial revolution in the sky and pitfalls to look at the domestic law in relation to the situation and to find a way to resolve them.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.31-34
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• 2003

To trace the working point of pressure-fed rocket propulsion system, direct analogy model was suggested, by which propellant mass flow rate and combustion chamber pressure were calculated from propellant tank pressures, levels and flight acceleration. In this paper, the analysis of KSR-III flight test results was taken by example, and it can be described that working point transition tendency of pressure-fed rocket propulsion system can be calculated by this direct analogy model.

• Journal of the Korea Institute of Military Science and Technology
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• v.1 no.1
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• pp.166-188
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• 1998

본 논문에서는 쿼터니온 궤환 개념이 기존의 오일러각 궤환 개념에 비해 추력벡터제어(Thrust Vector Control) 방식을 사용하는 전술 유도탄 자세제어에 보다 효과적으로 적용될 수 있음을 보인다. 오일러각 궤환 방식을 택한 기존의 자세제어기에서 오일러각 궤환 부분을 쿼터니온 궤환으로 적절히 바꾸어 주게 되면 자세명령 크기 변화에 따른 시간응답 특성의 변화를 줄일 수 있으며, 쿼터니온 궤환 방식을 택할 경우, 우주비행체 자세제어 분야에서 활발히 연구되고 있는 고유축(Eigen Axis) 회전에 의한 자세변환을 수행할 수 있는 자세제어기 설계가 가능하다. 고유축 회전은 최단경로에 의한 자세변환 개념이므로, 이러한 능력을 갖춘 자세제어기는 신속한 자세변환이 필요한 전술 유도탄의 초기비행에 매우 효과적으로 이용될 수 있다. 더욱이, 제어법칙에 공력모멘트를 보상하는 항을 추가하게 되면 변화가 심한 공력 모멘트가 유도탄의 회전운동에 미치는 영향을 줄일 수 있어 고유축 회전성능을 보다 개선시킬 수 있다. 우선, 오일러각 궤환보다 쿼터니온 궤환이 유리한 점을 논하고, 쿼터니온 궤환에 근거한 자세제어기의 설계 개념과 제안된 제어기에 의해 구성되는 폐루우프에 대한 안정성 문제를 다룬 후, 시뮬레이션을 통해 그 타당성을 검증한다.

• 한국전산유체공학회:학술대회논문집
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• 2010.05a
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• pp.32-36
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• 2010

This paper dealt with the flow simulation for the optimum designed propeller for Micro Aerial Vehicle, using a commercial CFD program(FLUENT). The propeller was modeled by the Multiple Reference Frame(MRF) method. For the validation of the computational method, the flow field analysis results for the propeller were compared with the flow analysis results, which are using Xfoil, for the optimum design, and with the wind tunnel data of a similar propeller model. By these validation processes, the reliability of MRF method was confirmed.

• 한국전산유체공학회:학술대회논문집
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• 2006.10a
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• pp.126-129
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• 2006

Many researchers have made an effort to explain flight mechanism of flapping insects. As a result, several unsteady mechanisms about lift generation in insect flight have been proposed. But it has a limits to elucidate insect's forward flight and abrupt thrust, because most of these are about insect's hovering flight. For this reason, the objective of this paper is to simulate "Figure-of-eight motion" of insect's wing during tethered flight for comprehending aerodynamic property in insect's forward flight.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2003.06a
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• pp.709-712
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• 2003

The existing technical limitation makes engineer imitate nature to solve engineering problems. Recently Micro Air Vehicle(MAV) imitating the mechanism of birds or insects is being developed. Especially Ultra Flite supported by DARPA is studying hummingbird aerodynamics to relate that information to MAV. To drive MAV bender piezoelectric(PZT) actuators are used due to the convinience of control and the small size. But the displacement of the PZT actuators are very small, and the wing driving mechanism which amplifies the stroke generated by the PZT actuators has constraints in design and manufacture because of the small dimension. In this paper a wing design concept and a efficient driving mechanism are proposed. Electroactive polymers(EAPs) are used as wing mechanism actuators. Using OpenGL the mechanisms are simulated graphically. Also a prototype actuator is being developed and verified by digital Mockup with CATIA. Basic kinematics of the mechanism is studied.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.188-196
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• 2007

A composite case was designed to satisfy the required condition of KSLV-I kick motor system. we performed the structure and combustion tests to insure the reliability of the case before the production of the flight model. The hydraulic, vacuum and non destruction testes as the structure test were carried out to confirm the strength of the components of the case and the characteristics of the thermal and structure were investigated through the ground combustion test.

• Proceedings of the KSME Conference
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• 2008.11a
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• pp.1441-1445
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• 2008

Insect flight is adapted to cope with each circumstance by controlling a variety of the parameters of wing motion in nature. Many researchers have struggled to solve the fundamental concept of insect flight, but it has not been solved yet clearly. In this study, to find the most effective flapping wing kinematics, we conducted to analyze CFD data on fixing some of the optimal parameters of wing motion such as stoke amplitude, flip duration and wing rotation type and then controlled the deviation angle by fabricating wing tip motion. Although all patterns have the similar value of lift coefficient and drag coefficient, pattern A(pear-shape type) indicates the highest lift coefficient and pattern H(pear-shape type) has the lowest lift coefficient among four wing tip motions and three deviation angles. This result suggest that the lift and drag coefficient depends on the angle of attack and the deviation angle combined, and it could be explained by delayed stall effect.

• Proceedings of the KSME Conference
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• 2008.11a
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• pp.1566-1569
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• 2008

The flow visualization is conducted in order to investigate an unsteady flight characteristic of a model dragonfly. The flapping wings are analyzed using smoke-wire and high speed camera. The results of this experiment show that three mechanisms and high incidence angle of the wings are responsible for the lift. The leading edge vortex, which is induced by the rapid acceleration of the wing at the beginning of a stroke, causes the lift enhancement. The delayed stall during the stroke and the fast supination and pronation of the wing near the end of each stroke are also responsible for the lift generation.

• Journal of the Korea Institute of Military Science and Technology
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• v.11 no.3
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• pp.5-12
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• 2008

This paper presents the features of an impact angle constrained open-loop optimal trajectory which is given by a function of initial conditions and optimal guidance gains. Using missile motion described by linearized kinematic equations and a proper form of performance index, an inverse optimal problem is suggested to investigate the gains related to the performance index. The flight trajectory and time-to-go can be shaped in terms of the optimal guidance gains. The results are evaluated by 3-DOF simulation.