• Aerospace Engineering and Technology
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• v.12 no.2
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• pp.74-82
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• 2013

This paper deals with a single stage coilgun which is a variety of EML(ElectroMagnetic Launcher) and can be applied to launching a small satellite. We propose a mathematical and physical model in order to design a single stage coilgun and study physical characteristics related to design parameters. A proposed mathematical and physical model is verified by electromagnetic FEM software FEMM 4.2.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.47-53
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• 2017

One of the most common causes of failure of space launch vehicles is combustion instability. Combustion instability is a phenomenon that the pressure perturbation inside the combustion chamber is greatly amplified due to the interaction of the pressure perturbation inside the combustion chamber and the heat release perturbation. When this phenomenon becomes worse, an engine failure or launch vehicle crash occurs. In order to predict and avoid such combustion instability, understanding of the phenomenon is indispensable, and numerical, theoretical, and experimental approaches to combustion instability have been carried out worldwidely.

• Korean Journal of Remote Sensing
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• v.37 no.2
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• pp.359-365
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• 2021

GEO-KOMPSAT-2A (GK2A) AMI (Advanced Meteorological Imager) Best Detector Select (BDS) map is pre-determined and uploaded before the satellite launch. After the launch, there is some possibility of a detector performance change driven by an abrupt temperature variation and thus the status of BDS map needs to be evaluated and updated if necessary. To investigate performance of entire elements of the detectors, AMI BDS analyses were conducted based on a technical note provided from the AMI vendor (L3HARRIS). The concept of the BDS analysis is to investigate the stability of signals from detectors while they are staring at targets (deep space and internal calibration target). For this purpose, Long Time Series (LTS) and Output Voltage vs. Bias Voltage (V-V) methods are used. The LTS for 30 secs and the V-V for two secs are spanned respectively for looking at the targets to compute noise components of detectors. To get the necessary data sets, these activities were conducted during the In-Orbit Test (IOT) period since a normal operation of AMI is stopped and special mission plans are commanded. With collected data sets during the GK2A IOT, AMI BDS map was intensively examined. It was found that about 1% of entire detector elements, which were evaluated at the ground test, showed characteristic changes and those degraded elements are replaced by alternative best ones. The stripping effects on AMI raw images due to the BDS problem were clearly removed when the new BDS map was applied.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.850-853
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• 2011

The position indicator for cryogenic valves used in space launch vehicle should have high reliability and accuracy. Because the valves operate in cryogenic environment, the position indicator has to measure the valve status independently of the environmental factor, such as moisture and external contamination. We have developed the position indicator using a permanent magnet and reed switches to satisfy these requirements. We analyzed the characteristics of a permanent magnet and reed switches, then selected the appropriate components for cryogenic temperature. The shape and position of components were also considered to measure the open/close information of valve accurately Finally, the position indicator was applied to the valve prototype model, and verified the feasibility of design parameters.

• The Science & Technology
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• no.3 s.406
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• pp.8-9
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• 2003

4개의 날개 가진 공룡화석 발견/ 목성탐사선 갈릴레오호 임무 마감/ 돼지심장 양에 이식 성공/ 음향 냉장고 만든다/ 질소비료가 이산화탄소 증가의 주범/ 우주의 초창기 진화 과정 밝혀져/ 화성에 쌍둥이 로봇 발사 예정/ 지구에서 가장 먼 행성 발견

• 정보화사회
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• s.110
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• pp.24-29
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• 1997

현재 이리듐 시스템은 교환기, 지국국 장비 및 위성의 초기 제작이 완료된 상태이며 금년 1월 최초 위성 발사를 기점으로 '97년중 위성망 및 지상관문국의 건설을완료하고 '98년중 시험을 거쳐 '98년 9월 전세계적인 서비스를 개시할 예정이다.

• Aerospace Industry
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• v.82
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• pp.34-35
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• 2003

과학기술위성 1호에는 국내 최초로 우주를 관측하기 위한 원자외선 분광기가 탑제되어 있어 은하의 구조와 진화과정에 대한 연구를 본격적으로 시작할 수 있게 되었다.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.1
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• pp.1-8
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• 2013

A liquid-monopropellant hydrazine thruster has several outstanding advantages such as relatively-simple structure, long/stable propellant storability, clean exhaust products, and so on. Therefore hydrazine thruster has such a wide application as orbit and attitude control system (ACS) for space vehicles. A hydrazine thruster with the medium-level thrust to be used in the ACS of space launch vehicles (SLV) has been developed, and its ground firing test result is presented in terms of thrust, impulse bit, temperature, and chamber pressure. It is verified through the performance test that the response and repeatability of thrust are very excellent, and the thrust efficiencies compared to its ideal requirement are larger than 93%.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.288-293
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• 2010

This paper presents to calculate the lethality of missile for the simulation test program and to verify the simulation results. In order to calculate a reliable lethality we need may data and experiments of fuse and warhead, but in reality it is hard to perform a task. Therefore, this paper obtained from the reference paper to analyze the lethality data for the calculation of the lethality. We form the 6 DOF simulation model using the MATLAB/SIMULINK. And formed the autopilot algorithm using the vertical and horizontal acceleration feedback and PNG (Proportional Navigation Guidance) command be used to the guidance algorithm. Finally, we evaluate the results about three cases, front launch, side launch and rear launch to simulate the simulation program, and the target is designed to have a constant speed and direction.

• The Journal of the Acoustical Society of Korea
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• v.39 no.4
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• pp.342-350
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• 2020

Acoustic and vibration research activities for the structural development of Korean space launch vehicles are introduced in this paper. Various dynamic loads exerted on a launch vehicle during its operation are summarized. The acoustical design method of payload fairings which protect satellites from harsh launch environment was reviewed. Several acoustic research activities were performed to enhance the analytical prediction ability during the development period of the Naro and the Nuri launcher. Specifically, the following research activities are reviewed: a test and vibro-acoustic analysis of composite cylinders whose layup properties are varied, a research on low-frequency acoustic load reduction by an acoustic resonator array and an acoustic test on the cylinder part of the Naro payload fairing. A vibro-acoustic analysis result for the Nuri launcher was introduced and predicted acoustic and vibration levels and measured ones are shown to be in a good agreement.