• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.769-771
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• 2011

The satellite payloaded on the 2nd stage of KSLV-I is planned to perform CCAM(Contamination and Collision Avoidance Maneuver) not to collide with KM(Kick Motor). At the moment, the satellite should pass through low density environment not to be contaminated by KM plume due to residual thrust. Therefore, it is necessary to predict the flow field of KM plume by residual thrust. In this paper, DSMC (Direct Simulation Monte-Carlo) method, which is widely accepted to simulate in rarefied regime, is used to compute the density field of KM plume by residual thrust and the result of DSMC simulation was compared with that of FLUENT to validate it.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.66-68
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• 2011

Chollian is a geostationary satellite, and its bipropellant propulsion system is mainly composed of one main engine for orbit transfer and fourteen thrusters for on-station operations. The Chollian was launched successfully at Kourou Space Center in French Guiana. After it separated from the launcher, the propulsion system was initialised automatically. Then three times of main engine firing were successfully performed, and the target obit insertion was accomplished. This paper details the major CPS events during LEOP phase for the Chollian satellite.

• Journal of Astronomy and Space Sciences
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• v.6 no.2
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• pp.101-108
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• 1989

The algorithm was developed for the estimation of orbital decay of the Soviet Satellite COMOS 1402 which divides into three body-COSMOS 14020-A, B and C-and fell down early in 1983. The perturbation effects due to the nonspherical geopotential and air drag were considered and the standard atmospheric model were built for obtaining the atmospheric density as a function of the height. The orbital elements of NASA GSFC during orbital decay used in estimation of orbital decay. We compared the estimation values with the published ones of the American State Department. In the case of COSMOS 1402-C, the estimated values accorded with the published ones but, in the case of COSMOS 1402-A, the decay time and the approximated position differed respectively one minute and two degrees in both latitude and longitude from the published ones.

• Journal of Practical Agriculture & Fisheries Research
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• v.23 no.1
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• pp.117-128
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• 2021

The skeletal muscle development of Hanwoo steer has been processed in the prenatal and postnatal periods. Bovine satellite cell located in perimysium of muscle tissues has differentially distributed in peripheral tissues. The study of postnatal development of satellite cells can help understand the genetic and functional regulation of meat characteristics. Factors affecting muscle size increase are related to the accumulation of DNA or synthesis of RNA proteins. In this study, we observed muscle development and differentiation after culturing bovine satellite cells derived from longissimus dorsi and semimembranosus regions of Hanwoo muscle tissue. In addition, RNA sequencing data were analyzed for differentially expressed genes (DEG) involved in intracellular muscle development and growth. The DEG of the two muscle tissues were compared according to 1day, 2day, 4day, and 7day. The overall gene expression level was confirmed by the heat map. Gene Ontology (GO) classification method was used to compare the expression level of gene groups affecting LD and SM development. The histology of GO was consistent with the time-cause change of LD and SM cell morphology. SM showed more active skeletal muscle development than LD. Even within the same time, SM expressed more genes than LD, thus synthesizing more muscle fibers

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2014.10a
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• pp.911-915
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• 2014

Pyrotechnic devices are widely used for space appendages. However, a cube satellite requirements do not permit the use of explosive pyrotechnic device. A nichrome burn wire release has typically been used for holding and release of deployable appendages of the cube satellite due to its simplicity and low cost. However, relatively low mechanical constraint force and system complexity for application of multi-deployable systems are disadvantages of the conventional mechanism. To overcome these drawbacks, we have developed a segmented nut type holding and release mechanism based on the nichrome burn wire release. The great advantages of the mechanism are much lower shock level and larger constraint force than the conventional mechanism using pyro. Flight model for on-orbit verification was developed and verified through release function test, vibration test and thermal vacuum test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.4
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• pp.17-26
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• 2005

Numerical investigation has been made on the aerodynamic characteristics of supersonic air-launching rocket, as a new concept launching mechanism. Parametric study on the variations of launching velocity, incident angle and mounting location of the rocket has been performed using three dimensional Euler equations. Influential factors at separating stage of the rocket were extracted through comprehensive analyses, and, the response surface models were constructed for those factors. From the study, the aerodynamic behavior of the air-launching rocket at supersonic speed and useful guidelines for the optimal mounting location of the rocket have been obtained.

• Proceedings of the Korea Information Processing Society Conference
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• 2006.05a
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• pp.635-638
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• 2006

현재 인공위성 영상은 지구에서 일어나는 변화를 탐지하기 위한 매우 효율적 수단으로 활용되고 있다. 지표에 대한 변화탐지는 원격탐사영상으로부터 지표변화를 찾아내 정량화하는 과정이 필요한데 이러한 정보를 추출하기 위해 본 연구에서는 웨이블렛을 이용한 텍스쳐 분석의 효율성이 연구되었다. 분석된 영상은 0.6m급 고해상도 위성영상으로 지진 전후로 하여 지진피해 지역을 탐지하기 위해 영상에서 관찰되는 풍부한 텍스쳐 정보를 활용하는 방법에 관한 연구가 이루어 졌다. 텍스쳐 특징을 추출하기 위해 GLCM이 이용되었는데 직접적인 GLCM의 적용보다는 웨이블렛변환 후 GLCM의 적용이 텍스쳐 특징을 보다 효과적으로 분리할 수 있는 방법임이 검사되었다. 이러한 웨이블렛 텍스쳐 특징 추출 후 상관관계에 기반한 변화탐지 기법을 적용하면 피해지역을 매핑할 수 있다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2005.05a
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• pp.250-253
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• 2005

This paper is investigates the separation shock of payload fairing. Separation test of subscale PLF using half separation device and half PLA is performed. Resulting shock loads at equipment bay and fairing joint are measured. Pyroshock estimation is performed using AUTOSEA Pyroshock Module. Input data to analysis model is obtained from the separation test results of subscale PLF. And model of AUTOSEA is updated comparing results between tests and analysis.. This enables us to validate the AUTOSEA model. Tuned model of subscale PLF and separation device is used to update full scale model, and the shock analysis result of full scale model is estimated in this paper. This paper also discusses the results regarding the difficulty of structural modeling and its numerical implementation in AutoSEA2 Software.

• The Proceeding of the Korean Institute of Electromagnetic Engineering and Science
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• v.25 no.2
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• pp.10-20
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• 2014

지금까지 대부분의 인공위성 또는 항공기 SAR 시스템은 하나의 위상 배열 안테나를 이용하며, 단 영상을 생성하고 판독하는데 주로 사용되었지만, 차세대 SAR 시스템은 다중 편파 관측이 가능하거나 이중 채널 또는 위상 배열 안테나의 분리 모드(split-antenna mode)를 통해 간섭기법의 적용이 가능한 시스템으로 발전이 이루어지고 있다. 이러한 측면에서 이 논문은 차세대 SAR 인공위성의 새로운 분석 기법 연구와 활용 증진을 위해, 유사한 기능을 보일 수 있는 이중 채널 항공기 SAR 시스템을 구축하고, 이로부터 단일 패스 간섭기법(single-pass interferometry)을 연구한 논문이다. 공간적으로 서로 다른 위치에 있는 두 개의 SAR 채널에서 동시에 수신된 레이다 신호를 간섭적으로 처리하여, 지형의 고도 정보를 추출하거나 이동하는 물체의 속도를 탐지할 수 있도록 알고리즘을 구현하였고, 새로운 활용 분야를 모색하고자 하였다.

• Journal of Satellite, Information and Communications
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• v.8 no.4
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• pp.159-163
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• 2013

In this paper, we propose a new method to deinterleave multi-stage stagger PRI signals of pulse radars using the electronic intelligence systems. While former algorithms were based on hardware PRI tracker only using the first deviation of the TOA of radar signals, this paper uses the first and the second deviation of TOA of radar signals and uses the PRI histogram method to deinterleave multiple PRIs of pulse radars. This algorithm can be used for deinterleaving various PRI signals at electronic intelligence systems.