• 항공우주정책ㆍ법학회지
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• 제22권2호
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• pp.3-25
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• 2007

In 2002 Republic of Korea successfully launched a self-made mined proportion rocket and it is expected that she will be able to have own space launching system by 2010. According to Article 14 of the Space Exploration Promotion Act, a new law should be established to impose the limit of compensation for the damage by space accident. Therefore, The Space Accident Liability Act was passed in Korean Congress on Nov. 22, 2007 and it will be enforced in six months. The purpose of this Act is to provide reparation for the damage of the third parties that a launch causes; and the Commonwealth should be insured against any possible space accidents to pay for such a damage. Here space accident means the damages to our life, body, and properties from the launching of space objects. There should be an actual loss to establish the compensation of Liability Act. Article 2 in Liability Act defines "damage" as follows: the term "damage" means loss of life, personal injury or loss of or damage to property of persons. Physical and material damages are included in the conception of damage. The meaning of a launching includes any test launch and launch for a real arrangement which will ultimately provides a wide range of compensation. Article 4 indicates that absolute liability should be imposed in compensating for damage by space accidents. Article 4 also indicates that a launching party should be absolutely liable to compensate for the damage caused by its space object on the surface of the Earth. In general, liability stands where fault is. But if the activity is ultra-hazardous and causes serious harm, the individual needs to compensate for the damage unlimitedly. Because of the many launchings for the Seattleite launching, a launching organization is obligated to the liability insurance in preparation for the space accidents. According to the Article 6 of Space Accident Liability Act, to be insured for the compensation for damage is obligatory. It says: "In accordance with Article 11 in the Space Exploration Promotion Act, the person who wants to receive an approval f3r launching needs to be insured in compensation for the possible damage by space accidents.

• 한국공간구조학회지
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• 제12권1호
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• pp.14-19
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• 2012

• 한국소음진동공학회논문집
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• 제22권9호
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• pp.889-895
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• 2012

A vertical launching system(VLS) is a system for holding and firing missiles on surface ships. When a missile is launched in VLS, relative motion between canister and missile and drag force induced by wind can cause initial unstability of a missile. Thus dynamic analysis of initial behavior of vertically launched missile should be performed to prevent collision with any structure of a ship. In this study, dynamic analyses of initial behavior of vertically launched missile are performed using Monte-Carlo simulation, which relys on random sampling and probabilistic distribution of variables. Each parameter related with dynamic behavior of a missile is modeled with probability variables and Recurdyn, a commercial software for multi body dynamic analysis, is used to perform Monte-Carlo simulation. As a result, initial behavior of a missile is evaluated with respect to various performance indexes in a probabilistic sense and sensitivity of the each parameters is calculated.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1988년도 한국자동제어학술회의논문집(국내학술편); 한국전력공사연수원, 서울; 21-22 Oct. 1988
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• pp.627-632
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• 1988

Through the introduction and understanding of the total system design and the system integration for sounding rocket with the purpose of the pure scientific research, that is, atmospheric research, resources observation, space observation and etc, the system will be operated easily, readily and effectively in the development and manufacturing of launching vehicles for the scientific satellite and communication satellite in the future.

• International Journal of Aeronautical and Space Sciences
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• 제16권1호
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• pp.102-109
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• 2015

In Korea, Lunar exploration program has been prepared with the aim of launching in the 2020's. As a part of it, a lunar lander demonstrator was developed, which was the model for verifying the system such as structure, propulsion, and control system, before launching into the deep space. This paper deals with the path tracking performance of the lunar lander demonstrator with respect to the thruster controller based on Pulse Width Pulse Frequency Modulator (PWPFM) and Pulse Width Modulator (PWM). First, we derived equations of motion, considering the allocation of the thrusters, and designed the path tracking controller based on Euler angle. The signal generated from the path tracking controller is continuous, so PWPFM and PWM modulator are adopted for generating ON/OFF signal. Finally, MATLAB simulation is performed for evaluating the path tracking ability. We compared the path tracking performances of PWPFM and PWM based thrust controller, using performance measures such as the total impulse and the position error with respect to the desired path.

• 한국의류산업학회지
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• 제11권1호
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• pp.112-120
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• 2009

The purpose of this study is to develop Andongpo apparel pattern design connected with the Apparel CAD system. It includes pattern making, grading, marking program. In this study, it will be able to make apparel pattern quickly and accurately by using Apparel CAD system. The results were as following : Computerization of the pattern making process is expected to provide higher accuracy and efficiency in apparel pattern making for narrow and expensive Andongpo. ESMOD pattern making method was selected as basic pattern. Tailored jacket patterns were developed for Andongpo. Refer to and . The jacket patterns developed is automatically depicted by inputting consumer's body size. Tailored jacket patterns for Andongpo were marked by using marking program in Apparel CAD system. The efficiency of marking appeared of 70% or more in Andongpo jacket patterns. This results is showed it has an effect on narrow and expensive Andongpo. 3tailored jacket patterns will be able to make a simulation by 3D Apparel CAD system. The results of this study is expected to provide higher consumer's satisfaction and internet brand launching. In addition, encouraging majority of the young to participate in using CAD program for Andongpo is regarded as beneficial for the reinforcement of competitiveness of traditional clothing business.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2003년도 The Fifth Asian Computational Fluid Dynamics Conference
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• pp.143-143
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• 2003

• Structural Engineering and Mechanics
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• 제17권2호
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• pp.245-266
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• 2004

Incremental launching method is one of the highly competitive techniques for construction of concrete bridges. It avoids costly and time consuming form work and centralizes all construction activities in a small casting yard, thus saving in cost and time against conventional bridge construction. From the quality point of view, it eliminates the uncertainty of monolithic behaviour by allowing high repetitiveness and industrial environment. But, from analysis and design point of view, the most characteristic aspect of incrementally launched bridges is that, it has to absorb the stresses associated with the temporary supports that are gradually taken on by the deck during its launch. So, it is necessary to analyse the structure for each step of launching which is a tedious and time consuming process. Effect of support settlements or temperature variation makes the problem more complex. By using transfer matrix method, this problem can be handled efficiently with minimal computational effort. This paper gives insight into method of analysis, formulation for optimization of the structural system, effect of support settlement and temperature gradient, during construction, on the stress state of incrementally launched bridges.

• 한국자동차공학회논문집
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• 제24권6호
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• pp.649-659
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• 2016

This paper describes control algorithm and control structure of vehicle control unit for range-extended electric vehicle equipped with engine-generator system, and specially presents methods which determine optimal operating points and decreases a vibration or a shock for operating the engine-generating system. The vehicle control algorithm is consisted of several parts which are sequence control, calculation of wheel demand torque, determination of operating points, and management of operating points and so vehicle controller has be made possible to efficiently manage calibration parameters. The control algorithm is evaluated by driving test modes, launching performance and operating engine-generator system and so on. In conclusion, this paper present methods for extending a mileage, improving a launching performance and reducing vibration or shock when the engine-generating system is starting or is stopping.

• 한국항행학회논문지
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• 제16권3호
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• pp.440-448
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• 2012

그룹 속도 분산 (GVD; group velocity dispersion)과 비선형 효과의 상호 작용에 의해 왜곡되는 파장 분할 다중 (WDM; wavelength division multiplexing) 신호를 보상하기 위해 광 위상 공액기 (OPC; optical phase conjugator)와 분사 제어 (DM; dispersion management)가 적용된 광전송 링크에서의 전체 잉여 분산 (NRD; net residual dispersion)의 최적치와 유효 입사 전력 범위를 도출하였다. 실제 광전송 시스템의 융통적 설계를 위해 한 쪽 반 전송 구획에서의 단일 모드 광섬유 (SMF; single mode fiber) 중계 구간(span) 당 잉여 분산 (RDPS; residual dispersion per span)이 랜덤하게 분포하는 광전송 링크를 고려하였다. precompensation으로 전체 분산을 조절하는 링크의 최적 NRD는 10 ps/nm이고 이 경우 유효 입사 전력 범위는 -8~1 dBm인 것을 확인하였다. 또한 postcompensation으로 전체 분산을 조절하는 링크의 최적 NRD는 -10 ps/nm이고, 유효 입사 전력 범위는 -7.5~1 dBm인 것을 확인하였다.