• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.63-72
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• 2010

MOV(Main Oxidizer shut-off Valves) control the combustion of launch vehicle systems by the supply and the isolation of liquid oxygen to a main combustion chamber in launch vehicle systems. Moreover, the MOV should secure a constant flow rate of liquid oxygen for combustion instability in the steady operational state. Although it has been showed that a EM(Engineering Model) with a high discharge coefficient value compared with the TM(Technology Model) fills the overall performance requirements, additional design modifications in some critical parts of the EM were conducted to improve the performance. The configurations of the pressure-control body, the middle flange, and the rips of the inlet body of the EM were modified and the performance tests have been performed with test models. Consequently, the intended improvements have been verified by the performance tests.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.24 no.12
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• pp.1128-1139
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• 2013

KOMPSAT-5(KOrea Multi-Purpose SATellite-5) has a benefit of continuously conducting its mission in all weather and even night by loading SAR(Synthetic Aperture Radar) payload, which is different from optical sensor of KOMPSAT-2 satellite. During IOT(In-Orbit Test) periods, SAR image calibration should be conducted through ground target of which location and RCS is pre-determined. Differently from the conventional corner reflector, active transponder has a capability to change its internal transfer gain and delay, which allows active transponder to be shown in a pixel of SAR image with very high radiance and virtual location. In this paper, the development of active transponder is presented from design to I&T(Integration and Test).

• Current Industrial and Technological Trends in Aerospace
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• v.7 no.2
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• pp.121-130
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• 2009

In this paper, the attitude and orbit control subsystem technology of new GEO communication and observation satellite using Sun sensors are introduced and analyzed. COMS is new GEO communication and Earth observation satellite based on EUROSTAR 3000 space bus technology. The attitude and orbit control subsystem of COMS adopts a configuration using three BASS and three LIASS Sun sensors to acquire the attitude error information in the specific reference frames. These Sun sensors are used to acquire Sun direction and to control the spacecraft to keep the relative attitude with respect to a reference Sun direction in both transfer and operational orbits. In this paper, the mathematical models of BASS and LIASS are described as well as their operational implementation in the flight software.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2004.05a
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• pp.618-622
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• 2004

The vibration test system of SITC(Satellite Integration and Test Center) at KARI(Korea Aerospace Research Institute) has been used successfully for the environmental tests of a majority of korean space programs, such as KOMPSAT, Koreasat KITSAT, STSAT and KSR program since 1996. To meet the recent needs of large size test facility available for the vibrational tests of the huge launch vehicles and tole-communication satellites which will be developed in the near future, KARI undertook to construct the large size multi-electromagnetic shaking system with 3 $\times$ 3m head expander system. The new system will consist of three electromagnetic shakers which has 160 kN thrust force individually, and be able te sustain up to 8 tons test load and 300 kNm overturing moment. And to avoid the tremendous cost and effort to furnish the seismic block with large size and weight, it will adopt a Lin-E-Air type configuration with which the seismic block is less severe than a Solid-Truninon type. In addition, to fulfill the strong requirement of high overturning moment the additional guidance system including a central bearing system on a central support and several pad bearings around the head expander body is now considered. This paper describes the configuration and the design parameters of the multi-shaking system which is under development by KARI's engineers.

• Korean Journal of Remote Sensing
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• v.36 no.5_2
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• pp.939-948
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• 2020

CAS500-1 and CAS500-2 are high-resolution Earth-observing satellites being developed and scheduled to launch for land monitoring of Korea. The satellite information will be used for land usage analysis, change detection, 3D topological monitoring, and so on. Satellite image data of region of interests must be acquired in the stereo mode from different positions for 3D information generation. Accurate 3D processing and 3D display of stereo satellite data requires the epipolar image resampling process considering the pushbroom sensor and the satellite trajectory. This study developed an epipolar image resampling module for CAS-500 stereo data processing and verified its accuracy performance by testing along-track, across-track, and heterogeneous stereo data.

• The Bulletin of The Korean Astronomical Society
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• v.35 no.2
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• pp.56.1-56.1
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• 2010

MIRIS(Multipurpose InfraRed Imaging System)는 과학기술위성 3호의 주 탑재체로서 2011년 발사예정인 다목적 적외선 카메라 시스템이다. MIRIS는 우주관측 카메라와 지구관측 카메라로 구성되어 있으며, 우주관측 카메라는 $0.9-2.0{\mu}m$ 영역에서 3.67 deg. x 3.67 deg. FOV로 우리 은하평면 survey 관측과 우주배경복사(CIB) 관측을 수행할 것이다. 현재 MIRIS는 비행모델 개발 마무리 단계에 있으며, 검교정 시험, 열-진공 시험, 진동 시험 등을 수행하고 나면 2010년 말 위성 본체와의 조립을 진행할 것이다. 우주관측 카메라는 궤도상에서 태양, 지구의 적외선 복사와 망원경과 검출기 주변에서 발생하는 열잡음을 줄이기 위해 냉각이 필요하며, 제한된 위성의 무게와 부피, 전력등의 요구조건들 때문에 망원경 및 구조체의 복사냉각(Passive Cooling) 방법을 선택하였다. Passive cooling으로 우주관측 카메라의 망원경이 200K 이하로 냉각되면, dewar에 설치된 소형 냉각기를 가동하여 적외선 센서를 80K로 냉각한다. 위성체 내벽과 우주관측카메라의 각 구조체들 사이의 복사를 차단하기위해 30층의 MLI를 적용 하였고, 각 구조체들간의 열전도를 최소화하기위해 GFRP supporter를 적용하였다. 이 실험은 천문(연)에서 자체 제작한 열-진공 챔버를 활용하여 진행하였으며, 이미 인증모델에 대한 passive cooling 실험을 두 차례 실시하였고, 그 실험 결과를 반영하여 최종 비행모델에 대한 실험을 수행하였으며, 그 실험 결과에 대해 논의 하고자 한다.

• Aerospace Engineering and Technology
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• v.8 no.2
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• pp.140-148
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• 2009

MOV(Main Oxidizer shut-off Valves) control the combustion of launch vehicle systems by the supply and the isolation of liquid oxygen to a main combustion chamber in launch vehicle systems. Moreover, in the steady operational state, the MOV should secure a constant flow rate of liquid oxygen for combustion instability in the combustion chamber. Concerning the development of MOV, TM(Technology Model) has been manufactured and normal operations of the valve have been verified. However, the Cv of TM has been proved to be too low as compared with a design specification value. Therefore, CFD analysis have been performed by modification of the configurations of TM in order to increase sufficiently Cv of EM(Engineering Model), which is the following model of TM. The modifications of TM configurations such as partial scale-up of valve, increase of stroke length, and outlet angle of 120o would result in a considerable augmentation of Cv. It has been verified by flow capacity tests that the improved Cv of EM is min. 212, which is higher than Cv of TM, 161 by about 32%.

• Journal of Satellite, Information and Communications
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• v.8 no.1
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• pp.8-13
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• 2013

It is necessary to develop the next generation FTS which is suitable for our environment and effectively operates many launch vehicles. Standard tone, Secure tone, MHA, EFTS and DSSS are studied for the next generation FTS. FTS requires a high quality of performance and reliability because of their specific mission. And few FTSs are needed but the price is very expensive. Therefore we must investigate a part of the FTS whether the part can be reused for a part of the next FTS. In this paper, we use CCDF of the transmitted signal from FTS as the method to study a possibility of reusing HPA used in the present system. The simulation results show that PEP of Standard tone is 0.21dB and Secure tone and MHA has the same PEP. CPFSK's PEP is 1.81dB and PEP of DSSS using BPSK modulation is 2.6dB.

• Proceedings of the Korea Water Resources Association Conference
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• 2004.05b
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• pp.1434-1438
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• 2004

저수지 수질모형의 기초자료로서의 수체의 수리학적 인자는 물리적인 자료이므로 많은 실측 자료를 필요로 한다. 이러한 자료의 취득을 위하여 수체의 수심을 측정하고, 대상구역의 수계특성을 잘 반영할 수 있도록 수체를 분할하여 각 구간별 수체 중심, 특성길이, 연직 및 수평 단면적, 수표면적, 수체적, 수로경사 등을 구하여 사용한다. 이러한 자료의 취득은 여러 가지 어려움으로 인하여 조사지점이 조밀하지 못하거나 계간방법이 개발되지 못하는 등의 이유로 인하여 실제값과 상당한 차이를 나타내기도 하므로 이를 개선할 수 있는 방법을 제시하고자 한다. 최근에 개발된 다중 음향탐사기 (MBES)는 초음파를 발사하여 하상에서 반사한 파의 시간을 측정하고 거리로 환산하여 수심을 측정하는 것으로 여러 지점의 수심을 동시에 스캔할 수 있다는 장점이 있다. 또한 MBES는 수신기의 지향각이 존재하므로 파의 반사지점을 정확하게 파악할 수 있다. 단일 음향측심기는 측선을 따라 수심을 측정하므로 조사간격이 넓어 정확한 수로정보를 얻기에는 미흡한 점이 있으나 MBES는 수체 전체를 $1\times1m$ 당 $4\~5$ 번의 측정하고, 변화가 심한 호저면에서도 수심오차 $5\~8 cm$의 고분해능을 갖는다. 이를 이용하면 하상의 수심에 내한 3차원의 연속분포를 생성하고, 하상의 지형적인 특징을 조사${\cdot}$ 분석할 수 있으며 하상의 성상과정에 관한 기초자료로도 활용한 수 있다. 수체정보를 산정할 때 단일 음향측심법은 간접적으로 자료를 취득하므로 주관적인 견해 및 큰 오차를 내포하고 있으나, MBES는 Hypack Max를 이용하여 구획한 구간에 따른 수표면적과 연직단면적 및 수체적을 자동으로 계산한다. 그리고 측정한 자료의 raw data를 이용하면 각 구간에 대한 무게중심을 구하여 중점으로 사용 가능하고, 종방향의 구축을 산정하여 수로의 깊이 및 중심간 길이를 정확하게 계산할 수 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.8
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• pp.706-711
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• 2015

The fighter aircraft uses several different loading configurations for air-to-surface and air-to-air combat missions. To maintain wings-level flight with an asymmetric weapon configuration, a pilot controls a roll trim system. However, it is difficult to apply an accurate roll trim input for wings-level flight in the actual flight under disturbance. The inaccurate roll trim input degrades the performance of the roll autopilot system. In this paper, to solve this problem, an integrator was additionally designed in the command part of the roll autopilot system. The initial transient response was improved by scheduling the limiter to restrict the roll attitude error. As a result of the evaluation of the simulation for the designed flight control law, the roll attitude following performance was found to be improved in the autopilot system operation under the inaccurate roll trim condition.