• Journal of the Korean Society for Precision Engineering
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• v.9 no.4
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• pp.154-166
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• 1992

A kinematic nonlinear multivariable launcher is modeled of which the azimuth and elevation axes are drived simultaneously and position control systems are designed for this system by the PD and LQG/LTR control methods. Also, the suitable command input fonction is suggested for the desired command following performance and the two control systems with disturbances and load variation are evaluated for the entire operating range by computer simulation. It is found that the two linear controllers can be used for the kinematic nonlinear multivariable launcher in the entire operating range and LQG/LTR controller is more effective for disturbance rejection.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.5
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• pp.65-71
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• 2005

Pyro-shock measurement system in launch vehicle is necessary to validate structural robustness and to prepare environmental qualification criteria for launch vehicle systems. This paper describes design, development and function test of prototype pyro-shock recorder to be employed on KSLV-I in the near future. Due to the limitation of telemetry transmission rate, pyro-shock recorder acquires and stores the shock sensor data with high sampling rate in short period and sends the data to the KSLV-I telemetry system with lower data rate. Signal conditioning in pyro-shock recorder is designed to enhance signal-to-noise ratio through proper placement of anti-aliasing filter.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.12
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• pp.101-108
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• 2005

The GPS(Global Positioning System) receiver for satellite launch vehicles which will be mounted on a launch vehicle can be applied to the flight safety system with its accurately calculated position and velocity data during vehicle's flight. This paper analyzes the performance of the GPS receiver such as SNR(Signal to Noise Ratio), fix mode, position and velocity error, number of visible and tracking satellites, and PDOP(Position Dilution of Precision) under temperature variation which is changed from -34$^{\circ}C$ to +71$^{\circ}C$.

• Proceedings of the KSRS Conference
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• 2008.03a
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• pp.53-58
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• 2008

인공위성을 통해 취득된 데이터들은 지상국의 수신처리시스템을 거쳐 표준영상으로 생산되며, 생산된 영상으로부터 사용자에게 의미 있고, 가치 있는 정보를 이끌어 내는 판독의 단계를 수행하게 된다. 본 연구에서는 원격탐사의 전반적인 이해를 돕기 위한 교육적 모델로서 캔샛 프로그램을 도입하였다. 캔샛 프로그램은 스탠포드대 로버트 트윙 교수의 제안으로 학생들에게 한 학기의 짧은 시간에 실제 인공위성의 설계, 해석, 제작, 조립, 시험, 발사, 운용 등 전반적인 시스템의 이해를 도모하기 위한 1Kg 이하의 캔 크기의 초소형 위성을 개발하는 교육 프로그램이다. 본 연구는 한국과학영재학교 R&E 프로그램의 지원으로 시작하였으며, 실제 초소형 위성 캔샛('KSAsat'으로 명명)을 직접 설계, 제작, 조립하고 최종적으로 발사 운용 시험을 수행하였다. 주 탑재체로 일반 상용 디지털 카메라를 장착하였으며, GPS, 광센서, 3 축 가속도계, 온도센서, 압력센서를 탑재하였다. 비행시험을 통해 성공적으로 영상을 취득하고, 각종 센서로부터의 데이터를 지상국으로 전송 받았다. 지상국을 통해 처리 되어진 데이터로부터 의미 있는 정보를 추출하는 판단의 단계를 거쳐 원격탐사의 전반적인 교육을 성공적으로 수행할 수 있었다. 본 논문에서 캔샛 프로그램이 원격탐사 교육에도 충분히 활용될 수 있음을 보였다.

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.73-80
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• 2013

In this study, a numerical analysis based on CFD methods has been conducted to predict the aerodynamic coefficients and aerodynamic loads of KSLV-II configuration designed at the system design phase. By the effects of exclusion of engine cowls of prior configuration, axial force and normal force decreased and center of pressure was much moved to the nose direction. Also, aerodynamic loads at flight and on the launch pad were predicted for structural load analysis. The computed results will be used for mission analysis and structural analysis at the next design phase.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1153-1155
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• 2017

The Launch Vehicle is made up of one system with several parts gathered together. In order to make the various parts developed in various organizations into one system, it is necessary to confirm all designs at certain point in time. Change after the design fix require controlled process to analyze the impact of the changes, to decide whether or not to make the change, and to verify that the change was implemented as intended. The configuration management procedure implemented in the above manner is also applied to the development process of KSLV-II. The CAD tool and PLM are linked with each other to perform configuration management for the 3D model, 2D drawing, and the configuration identification document.

• Standardization Trend in Telecommunications
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• s.24
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• pp.224-232
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• 1992

페이징 시스템의 발달과 시행은 오늘날 특정 영역 내에서의 진보가 다른 영역의 균형있는 발전에 얼마나 많이 의존하고 있는가를 보여주는 전형적인 예이다. 과거의 페이징 시스템은 한 공장의 근로자에게 혜택을 주었다. 위성을 이용하는 미래의 페이징 시스템은 전세계 모든 곳의 모든 사람에게 다양한 혜택을 제공해 줄 수 있게 된다. 점진적으로, 한 쌍의 킬로미터와 점선으로 연결된 전구와 벨은 처음으로 무선시스템으로 대체되어 한 국가라는 지역을 넘어서 서비스를 제공해 왔다. 디지털 기술의 개발을 포함해서, 무선 설비가 소형화 됨에 따라 이러한 일은 점차적으로 이루어져 왔다. 따라서 전기통신에 의한 우주 무선통신과 특히 정지위성 시스템의 엄청난 발전으로 전세계는 가까워지게 되었지만 거의 엄청난 비용과 이용자들이 갖춰야할 것들 때문에 이러한 영역에 접근하는 것은 거의 한정되어 방송용으로만 준비되어 왔다. 오랫동안 LEO 위성은 과학적, 군사적인 용도로만 이용되어 왔는데 그것은 이 위성이 원래 가지고 있는 문제점들로 하루마다 지평선 위의 아주 짧은 통행로와 관계된 것 때문이었다. 그러나 현재는 하나의 시스템을 형성하기 위해 수많은 LEO 위성들의 발사를 감당해 낼 수 있는 장치와 여러 영역에서의 공동작용(synergy) 덕분에, VHF대의 아주 저렴한 시설을 이용한 경제적, 기술적 장점을 인식하고, 혼신을 다하여 다이내믹 채널 활동지점 시스템(denamic channel activity assignment system)을 개발하였고, 마지막으로 말하지만 결코 가볍게 인식해서는 안될 WARC-92가 필요한 주파수대를 지정해야한다는 의도를 밝힌 것 등이 개인간의 통신을 전세계적으로 확대하는데 있어서 디딤돌이 될 것이다.

• Spatial Information Research
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• v.10 no.3
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• pp.407-419
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• 2002

In this study, the design of 4S-Van system is discussed fur the implementation of laser mapping system. Laser device is fast and accurate sensor that acquires 3D road and surface data. The orientation laser sensor is determined by loosely coupled (D)GPS/INS Integration. Considering current system architecture, (D)GPS/INS integration is performed far performance analysis of direct georeferencing and self-calibration is performed for interior and exterior orientation and displacement. We utilized 3 laser sensors for compensation and performance improvement. 3D surface data from laser scanner and texture image from CCD camera can be used to implement 3D visualization.

• Journal of Aerospace System Engineering
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• v.16 no.2
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• pp.1-12
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• 2022

The purpose of this study was to investigate the supply and demand structure of the domestic space industry through analysis of industrial concentration index, by sector and dependence on revenue by customer type. As a result of industrial concentration analysis, in the case of space application, a supply monopoly or oligopoly structure was revealed in fields such as satellite broadcasting, space insurance, and satellite navigation. In the field of space equipment manufacturing, referred to as the traditional space industry, a supply monopoly structure appeared only in the field of launch pads and test facilities. As a result of analyzing the dependence on revenue by customer type, the dependence on the demand in the space application field is diversified among foreign countries, private institutions, and others. However, in the case of space equipment manufacturing, it is highly dependent on the demand of public institutions, and it seems that there is a monopsony structure.

• Journal of Advanced Navigation Technology
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• v.6 no.1
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• pp.62-68
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• 2002

Mother ship must be able to know accident occurrence information rapidly to rescue crew who fall in sea. In this paper, designed and manufactured transceiver of prescribed 447 MHz is operating as low power radio station specified in Radio Regulation. So, it is available without special permission proceedings getting form probation so that the use of this system may be easy. the system has been started for operation when the sensor get in touch with water. The system transmits with modulation by 500Hz square wave, and the receiver alarms when the transmitted signal is received. Therefore, the system can be used for not only saving a life, but also for low speed of data transmission below 2,400 bps, and other purposes.