• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.6
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• pp.17-22
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• 2003

An airship is statically unstable, because it has no wing, relatively small tails and a large hull. Hence, an accurate prediction of dynamic stability is critical. In this study, dynamic stability data of the 50m Length Airship were acquired through forced oscillation wind tunnel tests. The tests were done in Birhle Applied Research Inc's Lange Amplitude Multi-Purpose(BAR LAMP) Facility located in Germany. The tests were composed with 16 static runs and 26 dynamic runs. As results, it is obtained that dynamic characteristics of the airship depend on the sideslip angle, the angular rate and its direction as well as the angle of attack. Generally, three directional moments have damping, but the normal force, the side force, and the cross-derivatives are unstable. The dynamic derivatives are not sensitive to the control surfaces, but nonlinear to the sideslip angle.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.155-172
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• 2002

Airship technical regulations for certification system of each countries are reviewed to assist the development of medium size airship that can be applied observation and communication relay with the ability of holding position at high altitude.

• Composites Research
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• v.18 no.2
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• pp.30-37
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• 2005

In this paper, geometrically non-linear finite element analyses were performed to study the mechanical behavior of the material system of the envelope of stratospheric airships. The microstructure of the load-bearing plain weave layer was identified and modeled. The Updated Lagrangian formulation was employed to consider the geometric non-linearity as well as the induced structural non-linearity for the fiber tows. The stress-strain behavior was predicted and the effective elastic modulus was calculated by numerical experiments. It was found the non-linear stress-strain curves were largely different from those by linear analysis. And non-linear elastic moduli were much higher than linear elastic moduli. The difference was more distinguishable when the tow waviness ratio was smaller.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2013.10a
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• pp.339-342
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• 2013

수면비행선박은 지면효과를 이용하여 해면과 가깝게 비행하면서 여객 및 화물수송이 가능한 복합운항형태의 선박을 말하는데, 이 수면비행선박의 원리와 수면비행선박의 안전운항을 위해서는 어떠한 항로표지시설이 설치되어야 하는지 관련 규정 및 군산지방해양항만청의 사례를 중심으로 조사 결과를 제시한다.

• Proceedings of the Korea Contents Association Conference
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• 2019.05a
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• pp.269-270
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• 2019

무장 비행 궤적 간 간섭을 식별하여 아군 무장간 충돌을 방지함으로써 단위 시간 당 교전 효과를 극대화하는 것은 다무장 대지 무기체계 운용에 있어서 필수적이다. 기존 연구에서는 연산 부하의 최소화를 목표로 3차원 무장 비행 궤적을 2차원 평면의 사격선으로 변환하여 간섭을 식별하는 알고리즘을 제안하였다. 그러나 기존 연구는 2차원 평면에서 사격선간 교차점이 발생할 경우 간섭으로 식별하고, 이에 대한 무장 할당을 해제함으로써 무장 활용도를 감소시키는 문제가 있었다. 이를 고려하여 본 논문에서는 교전 효과 최대화를 위한 효율적인 무장 궤적 간 간섭 식별 알고리즘을 제안한다. 제안하는 알고리즘은 2차원 평면에서 사격선간 교차점이 발생할 경우, 해당 사격선을 3차원 평면에서 비행 궤적 간 비교 연산을 수행하여 실제 간섭 여부를 식별함으로써 무장 활용도를 최대화하는 것이 가능하다. 성능 평가 결과, 제안하는 기법은 기존 기법에 비해 궤적 교차수는 최대 52.1% 감소하였으며, 그에 따른 표적 할당율은 최대 6.9% 향상됨을 보임으로써 그 우수성을 확인하였다.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.27-34
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• 2004

Tail-wing, gondola and thrust motor mount(EMS) were built by carbon/glass fiber composites. Structural strength & stiffness was verified by specimen tests. Static strength tests for each structural components were conducted separately. Boundary conditions are specially designed for each components to simulate exact joint conditions. Tests shows no detriment deformation at 100% DLL and no failure at 150% DLL.

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.87-93
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• 2013

The conceptual design lunar lander demonstrator has been developed to use as a test bed for advanced spacecraft technologies and to test a prototype planetary lander capable of vertical takeoff and landing. Size of the lunar lander demonstrator is the same as that of lunar lander conceptually designed, however, the weight of lunar lander demonstrator is designed in 1/6 scale in consideration of gravity difference between moon and earth. The thruster clustering and virtual flight test were performed in the demonstrator fixed on the ground. The demonstrator ground test has been conducted for two months in the test site for the solid motor combustion of the Goheung Flight Center. The purposes of ground test of demonstrator are to demonstrate and verify essential electronics, propulsion system, control algorithm, embedded software, structure and system operation technologies before developing the flight model lander. This paper is described about the virtual flight test including test configuration, test aims and test facilities

• Current Industrial and Technological Trends in Aerospace
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• v.8 no.2
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• pp.24-30
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• 2010

Space solar sails are a form of spacecraft propulsion using the radiation pressure of light from a star or laser to push enormous ultra-thin mirrors to high speeds. With respect to it, U.S.A, Japan, E.U. and Russia, etc. have performed a substantial research and the space flight test. On May 2010, JAXA succeeded in launching the world's first interplanetary solar sail spacecraft "IKAROS" to Venus. Currently, solar sail propulsion is aimed chiefly at accomplishing a number of non-crewed missions in any part of the solar system and beyond. This paper presents the technology trend of advanced countries on the development of the solar sails as a new propulsion method for the space investigation and travel.

• Journal of Digital Convergence
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• v.12 no.2
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• pp.119-128
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• 2014

This Study investigated the differences of risk assessment tool and personality assessment inventory (PAI) by recidivism types of juvenile delinquents, the psychological factors that have a influence of juvenile behaviors. 268 incipient Juvenile criminals who had committed crime in the areas of Seoul, were categorized in the three degree of recidivism types. The result showed the significant differences among risk assessment tool, such as family functioning risk factor, school risk factor, away-from-home risk factor, delinquent risk factor, and personal risk factor. PAI scores among the recidivism type showed the significant differences on SOM, DEP, PAR, SCZ, BOR, ANT, ALC, DRG, AGG, SUI, STR, NON, DOM, and WRM. The predictor variables explained a risk assessment tool were STR, ALC, DEP, DOM and WRM in PAI scales. And the interventions and preventions about juvenile delinquents discussed in psychological aspects.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.12 no.2
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• pp.1-15
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• 2004

In this study, we analyze technical requirements for a 50m unmanned airship order to assure safety in the test flight operation. The 50m class unmanned airship developed by Airship Group in Korea Aerospace Research Institute(KARI). The 50m class unmanned airship was developed as a scale-down model of 200m class stratosphere unmanned airship. This study reviews specifications and characteristics of 50m class unmanned airship and develops Airworthiness Requirements on the basis of current effective Aviation Act, Airworthiness standards, and relevant international documents. The developed requirements can be applied to the safety assessment of the 200m class stratosphere unmanned airship.