• Journal of KSNVE
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• v.7 no.5
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• pp.717-724
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• 1997

본 글에서는 위성체의 수명 중 초기의 매우 짧은 기간이지만 위성체의 성공 여부를 좌우하는 발사환경에 대한 기본적인 개념을 파악하고 이를 지상에서 구현하는 방법론에 대하여 언급코자 한다.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.39 no.6
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• pp.611-615
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• 2015

Anti-aircraft gun system is used for low-level air defense system and has more than twin guns with high firing rate in order to maximize the capability of defense. Gun's vibration and bullet's variance has a critical effect on accuracy and hit probability of weapon system such as anti-aircraft gun system with high firing rate. Typical mechanism to reduce the amount of vibration and shock during gun-fire process is very important design factor. In this paper, the suspension characteristics of the vehicle are studied for the improvement of isolating performance of gun firing system with high firing rate. Gun fire test for the vehicle is conducted and computational models using Recurdyn and Adams are created based on test results. Through this study, results of computational analysis are compared with the real test results, which includes type, location and quantity of suspension and gun mechanism are selected for anti-aircraft gun. From the result of this study, we could make basic design and consider the proper component of the system such as suspension and gun spring.

• Bulletin of the Korean Space Science Society
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• 2011.04a
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• pp.33.1-33.1
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• 2011

이 논문에서는 비선형댐퍼를 이용한 광학탑재체 품질개선 방법에 대해 다루었다. 인공위성은 발사 시에 높은 진동하중에 견디어야 하며, 임무 수행 중에는 광학탑재체가 영상을 획득할 수 있도록 지지해주어야 한다. 그러나 인공위성은 자세제어, 데이터 송신, 탑재체 능동냉각을 위한 진동하중 가진 원을 보유하고 있어, 이를 광학탑재체 노출 시 영상품질이 저감되기 쉽다. 이 논문에서는 비선형 댐퍼를 이용해 발사 시에 높은 진동하중에 견디며, 발사 후에는 진동을 절연시켜 영상품질을 개선시키는 방법에 대한 연구를 수행하였다.

• Journal of KSNVE
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• v.17 no.5
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• pp.16-26
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• 2007

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.45-45
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• 2004

현재 개발 중인 저궤도 소형인공위성 발사체, KSLV (Korea Space Launch Vehicle)에 최초로 실리게 되는 ‘발사체 검증위성, KoDSat’ (KSLV Demonstration Satellite)은 발사과정 중에 위성체가 겪게 되는 진동 및 음향레벨 크기를 측정하여 지상국으로 전송하게 된다. 또한 위성체 내부에 설치한 카메라를 이용하여 발사체에서 분리되는 과정을 촬영하여 지상으로 동영상 데이터를 전송하게 된다. 열제어계의 목적은 어떠한 임무기간 동안에도 위성체의 모든 요소들이 각각의 허용 온도범위 내에서 유지되도록 하는데 있다. (중략)

• Proceedings of the KIPE Conference
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• 2018.07a
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• pp.243-245
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• 2018

발사체 및 인공위성에서 발사시부터 우주까지 도달하는데 다양한 환경이 주어진다. 본 논문에서는 발사체의 단분리 및 페어링 분리시 생기는 충격 환경과 대기가 발사체 표면에 충돌하여 생기는 진동 환경에 대한 배터리 내부 변화를 분석한다. 환경시험을 반영한 전기적 모델링을 설계하고 전기적 파라미터를 기반으로 배터리 열해석과 실제 배터리팩 내부 열을 측정하여 비교 및 분석한다.

• 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.

• Journal of Satellite, Information and Communications
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• v.5 no.1
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• pp.69-74
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• 2010

As a part of development process of the COMS, an acoustic vibration test was performed in order to verify that the COMS is safe from the acoustic loads coming from the Ariane-5ECA launch vehicle when it is launched. In this paper, the acoustic vibration test preparation which was performed during the development of the COMS is explained, and through the evaluation of the test results, it was verified whether the COMS is safe from the acoustic load that the COMS will experience during the launch. Through detail evaluation of the acoustic loads on the solar array, Ka band communication payload antenna and feed, GOCI(Geo-Stationary Ocean Color Imager), MI(Meteorological Imager), it was confirmed that the COMS is safe from the acoustic loads from launch vehicle.

• Journal of Aerospace System Engineering
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• v.11 no.1
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• pp.1-7
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• 2017

While a satellite is carried into orbit by a launch vehicle, it is exposed to the severe launch environment with random vibrations and shock. Accordingly, these vibration sources affect electronic equipment, particularly the printed circuit board (PCB) in the satellite. When the launch load impacts the PCB, it causes negative behavior. This causes perpendicular bending around the boundary of fixation points that finally leads to the failure of solder joints, lead wires, and PCB cracks. To overcome these issues, the electronic equipment design must meet reliability requirements. In this paper, Steinberg's method is used to derive allowable and maximum deflection to verify design from a life perspective concerning the control board of the Antenna Pointing Driver (APD) mounted on KOMPSAT-3.

• Journal of KSNVE
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• v.27 no.1
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• pp.12-19
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• 2017