• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.49 no.4
• /
• pp.263-272
• /
• 2021

In this study, aerodynamic coefficients obtained from Computational Fluid Dynamics (CFD) using wind tunnel test-like method is compared with coefficients obtained by actual wind tunnel test. Unsteady analysis has performed with using harmonic equation for motion of the external store. Aerodynamic database is generated based on CFD results to simulate 6 degree-of-freedom store separation analysis. Trajectory is obtained from simulation using both CFD-based and test-based database, and results are compared with trajectory from flight test result. It is concluded that generation of database based on CFD with wind tunnel test technique is valid from good agreement of the trajectory.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.33 no.10
• /
• pp.75-81
• /
• 2005

Jettison, grid and CTS test are widely used for the store and stage separation studies. This is an introductory paper on the experimental methodology and typical results of grid and CTS test used for the Korean 3-stage sounding rocket development. Thirteen separation trajectories were evaluated in the ONERA S2MA wind tunnel at Mach numbers of 2.0 and 2.8. The test result was applied as the basic database for the design of optimized separation device.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.45 no.7
• /
• pp.539-549
• /
• 2017

In this paper, experimental studies on the shroud separation were performed to investigate characteristics of the shroud separation at mach 3. Shroud separation tests were carried out in the vertical free-jet wind tunnel that is capable of testing separable structures. A shroud model was miniaturized to meet test objectives and test section dimensions of the wind tunnel. Pneumatic Locking and separation mechanisms were designed considering external force due to free stream. High speed cameras were used to record the shroud motion and unsteady shock patterns over the deploying shrouds during the shroud separation process. Also, unsteady pressures on the nose surface were measured by using the pressure sensors. Through the tests, the measurement data necessary for researches on the shroud separation technology were obtained. Shroud separation behaviors and characteristics of unsteady pressure on the nose surface for each external flow conditions were analyzed.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.32 no.5
• /
• pp.24-29
• /
• 2004

In this paper, we summarize the results of free drop wind tunnel test, separation analysis and flight test in order to verify the safety during the separations of an external fuel tank and the LAU-131 rocket launcher from XKO-l. The wind tunnel test was conducted to show the safety in free drop of the stores and to gather the trajectory data for fine tune of MSAP(Multi-body Separation Analysis Program). The enhanced MSAP was then used to predict the trajectories of the stores with and without the ejector forces. A correlation of MSAP results for free drop case was also made to show the safety of jettison with the free drop type bomb rack. Moreover, the flight test was conducted. and its results were compared to analysis results. Finally, the safe jettison boundary was determined from the flight test.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.38 no.8
• /
• pp.767-773
• /
• 2010

This paper describes development of a non-explosive separation device which can be equipped on small satellites. The spur geared micro DC motor, which has high reliability and advantage of price, is adopted as an actuator. The proposed separation device has resettability and it does not need extra jig to reload. In addition, the simple structure makes it easy to fabricate and assemble. To verify the performance of the proposed device, the response time tests, maximum preload tests and maximum shock level tests were performed. Also, through the vibration tests and thermal vacuum tests, feasibility of the proposed separation device was shown in launching and space environments. Therefore, we expect that the proposed separation device can replace the imported separation devices in near future.

• Proceedings of the Korean Society for Agricultural Machinery Conference
• /
• 2002.02a
• /
• pp.317-322
• /
• 2002

농가보급형 마늘쪽 분리기 개발을 위하여 마늘의 품종별 기하학적 특성을 분석하고, 나선 부착 원추 드럼식 마늘쪽 분리기를 제작하여 성능시험 및 농가 현장시험한 결과를 요약하면 다음과 같다. 1)종구용 통마늘의 크기를 조사한 결과 직경은 의성, 무안, 자봉이 각각 44.3, 51.9, 60.2mm로 나타났다. 2)통마늘의 최대 압축력 및 마늘쪽의 생물체항복 강도를 시험한 결과 수평방향 최대 압축력은 의성, 무안, 자봉마늘이 각각 185.1, 145.8, 148.5N이고, 마늘쪽의 생물체 항복강도는 의성, 무안, 자봉마늘이 각각 272.4, 336.2, 413.2N/$cm^2$로 통마늘은 의성종이 단단 하나 마늘쪽은 무안이나 자봉마늘에 비해 단단하지 않은 것으로 나타났다. 3)나선부착 원추 드럼 및 경사원통식 마늘쪽 분리장치를 제작하여 성능시험한 결과 1쪽 분리율이 의성, 무안, 자봉마늘에서 각각 58.2, 64.7, 95.2%이고, 손상율은 각각 2.0, 2.4, 1.9%이었으며 작업능률은 시간당 210kg(약 60접)이었다. 4)시작기를 전남무안의 재배농가에서 현장 시험한 결과 1쪽분리율은 75.9%, 손상율은 0.8%, 파종 후 출현율이 94.3%로 농가적응성 및 실용성이 높은 것으로 판단되었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.40 no.5
• /
• pp.439-445
• /
• 2012

The COMS(Communication, Ocean, and Meteorological Satellite) is subjected to shock loads when the stage or fairing of a launch vehicle is separated and the satellite is separated from the launch vehicle during the launch vehicle flight. And, after the satellite is separated from the launcher, the COMS is subjected to shock loads when the solar array is deployed, Ka-Band communication antenna is deployed, and meteorological imager radiator cover is released. In order to validate the satellite safety against these shock loads on ground, shock tests were performed. In this paper, the shock tests performed in the course of the COMS development are described, and the method to assess the test result is presented with an example of Geostationary Ocean Color Imager(GOCI). In Ariane-5 launch vehicle, the clampband release shock for satellite separation is lower than the fairing or stage separation. In this paper, the extrapolation method to take into account the maximum shock load from the launch vehicle by using the satellite separation shock test result is also introduced.

• Proceedings of the Korean Society of Applied Pharmacology
• /
• 1995.04a
• /
• pp.61-61
• /
• 1995

1993년 국내토양으로부터 분리동정된 Streptomyces속 균주중 항종양성이 우수한 균주 3주(DKM104, DKM117, DKM409)를 선정하고 이들을 대량 배양하여 종양억제인자를 분리하고 시험관내 종양세포 독성능 및 생체내 항암활성능과 이들 물질생산과 PLASMID DNA와의 관련성, $LD_{50}$등을 시험하여 새로운 항종양물질의 개발을 목적으로 하였다. 분리선별균주의 배양조건을 확립하였으며 배양여액을 국성이 적은 유기용매로부터 큰쪽으로 단계적으로 유효성분을 추출하여 Gel Chromatography를 이용하여 유효성분을 분획하였다. 시험관내 항종양능 시험은 MTT colorimetric검정법을 이용하여 $IC_{50}$값을 산정하였으며 생체내 항종양능은 마국의 NIC에서 권장하는 tumor panel system에 따랐다. 선정된 균주의 plasmid 분리는 alkalin lysis법을 채택하였으며 agarose gel electrophoresis로 plasmid profile을 시험하였다. Novobiocin등을 이용하여 Curing test를 시행하였고 독성실험은 $LD_{50}$량을 구해 항암효과 측정시에 Maximum dost로 투여하였고 최고용량을 기준으로 일정한 공비를 적응하여 3단계의 투여량을 설정하였다.(중략)

• Aerospace Engineering and Technology
• /
• v.4 no.2
• /
• pp.199-202
• /
• 2005

Separation motion of 1:2 downscaled nose fairing is simulated. In comparison with the experimental results, results of analyses on the separation simulation are verified and the characteristics of nose fairing separation are analyzed. The results shows about 5% analysis error.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.41 no.8
• /
• pp.673-679
• /
• 2013

Photogrammetric techniques were used to analyze separation characteristics of store in safe separation flight test. In this analysis, we used single camera method to analyze 6 degrees of freedom of separated store. We established instrumentation requirements based on theoretical background of photogrammetry and guidelines of MIL-HDBK-1763. We applied the photogrammetry to flight test and extracted separation trajectory. We empirically estimated the input variables uncertainties of photogrammetry and its effects on separation trajectory. Using this trajectory which includes the photogrammetric error, we analyzed the safety of separation.