• Journal of Aerospace System Engineering
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• v.13 no.3
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• pp.78-86
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• 2019

This paper describes the stiffness optimization of the torsion spring hinge of the large SAR antenna considering the deployment performance. A large SAR antenna is folded in a launch environment and then unfolded when performing a mission in orbit. Under these conditions, it is very important to find the proper stiffness of the torsion spring hinge so that the antenna panels can be deployed with minimal impact in a given time. If the torsion spring stiffness is high, a large impact load at the time of full deployment damages the structure. If it is weak, it cannot guarantee full deployment due to the deployment resistance. A multi-body dynamics analysis model was developed to solve this problem using RecurDyn and the development performance were predicted in terms of: development time, latching force, and torque margin through deployment analysis. In order to find the optimum torsion spring stiffness, the deployment performance was approximated by the response surface method (RSM) and the optimal design was performed to derive the appropriate stiffness value of the rotating springs.

• Journal of Astronomy and Space Sciences
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• v.22 no.4
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• pp.513-526
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• 2005

The objectives of this study are to perform extensive analysis on internal mass motion for a wider parameter space and to provide suitable design criteria for a broader applicability for the class of spinning space vehicles. In order to examine the stability criterion determined by a perturbation method, some numerical simulations will be performed and compared at various parameter points. In this paper, Ince-Strutt diagram for determination of stable-unstable regions of the internal mass motion of the spinning thrusting space vehicle in terms of design parameters will be obtained by an analytical method. Also, phase trajectories of the motion will be obtained for various parameter values and their characteristics are compared.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.2
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• pp.68-74
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• 2006

An experimental study was carried out to investigate the combustion characteristics of the slinger combustor. A combustion test rig was manufactured and installed in KARI combustor test facility. From the ignition test results, we found that there were two major factors influencing the ignition limits; by increasing the rotational speed and the air mass flow rate, a better ignition performance was attained. From the combustion test results, we obtained 99.6% combustion efficiency, 15% pattern factor, and 3% profile factor. The results in this work indicate that the ignition and combustion characteristics of a slinger combustor are markedly different from those of a conventional annular combustor.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.81-86
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• 2004

Between rolling airframe missile and swirling propulsion jet passing through convergent-divergent nozzle of the rocket motor, occur exchanges of angular momentum which result in the increase of roll speed of the missile. This phenomena in called jet roll damping. In the study jet roll damping was formulated from conservation equation of angular momentum. And the maximum value of the jet roll damping of KPSAM was estimated with assumed swirl velocity distribution at nozzle exit and compared with result of computation of axisymmetric compressible turbulent nozzle flow.

• Journal of Aerospace System Engineering
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• v.10 no.4
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• pp.75-83
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• 2016

This paper presents a survey of patents and an analysis of a conceptual study for the development of rotor drive systems in combined unmanned rotorcraft in. The patents were classified into 10 cases with respect to the rotor drive system development, and these are reviewed and analyzed in detail. The results describe development concepts for rotor drive systems for vehicles obtained through the patent analysis.

• Bulletin of the Korean Space Science Society
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• 2011.04a
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• pp.21.4-22
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• 2011

IVS (International VLBI Service for Geodesy and Astrometry) 통합분석센터는 개별 IVS 분석센터의 산출물을 통합하고 그 결과물을 IERS (International Earth Rotation and Reference Systems Service)에 제공하여 국제 지구기준좌표계를 구축하고 지구회전파라미터를 결정하는데 핵심적인 역할을 한다. 한국천문연구원(KASI)은 2008년 10월 IVS 통합분석센터로 선정되어 현재 통합 분석 시스템을 구축하고 있다. 정규운영에 앞서 통합용 분석 소프트웨어를 정비하고, KASI 통합분석센터의 통합해를 타 IVS 통합분석센터 통합해와 비교 검증하는 것은 필수적이다. 이 연구에서는 통합분석처리를 위해서 GPS 자료처리 소프트웨어인 Bernese 5.0을 IVS 산출물 형식에 맞추어 수정 보완한 후 활용한다. 이 발표에서는 1984년부터 현재까지의 IVS 분석센터의 장기간 산출물을 수집하고 Bernese 5.0을 이용하여 지구회전파라미터(X-극, Y-극, UT1-UTC와 각각의 시간변화율)의 통합해를 산출한 결과를 소개한다. 또한, 타 IVS 통합분석센터의 통합해와 비교 검증결과를 논한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.5
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• pp.357-365
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• 2013

In this study, forces and moments were measured on a projectile which consisted of a missile configuration body(shell) and a head installed control fins. The shell and the head were separated each other and the shell was rotated by an electric motor. The head rotated reversely against the rotational direction of the shell. The rotational force on the head was obtained from a couple of fixed fins of which angular displacement were set to the rotational direction equally. The air velocity was 40m/s on the experiment and the Reynolds number based on the diameter of head was $1.3{\times}10^5$. The other couple of fins were used to control the position and direction of the projectile by changing the angular displacement. From this experiment, the variation of force and moment were measured on the rotating projectile, and the effective amplitude and frequency were obtained through the FFT analysis.

• Aerospace Industry
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• v.69
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• pp.44-47
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• 1999

사람은 자신의 이동에 기계를 사용하기 시작했고 그 발전속도는 항공기의 발달로 극에 달한 느낌이다. 그러나 이러한 이동수단은 필연적으로 사고를 동반하는 것 또한 현실이다. 각종 이동수단 즉 교통수단 가운데서 사고 발생률의 면에서는 단연 항공기가 가장 낮다고 하지만 항공기 사고는 한번 나면 대형사고이고 인명의 살상이 많기 마련이다. 항공기 사고는 오늘날 사고 내용을 자세히 살펴보면 고정익기 보다는 회전익이 더 많고 성층권을 비행할 때 보다는 대기권을 운행할 때가 더 많다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.2
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• pp.7-16
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• 2004

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.4
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• pp.309-314
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• 2010

In this work, the helicopter price estimation formula from Harris & Scully is revised and updated for more accurate prediction of the current prices of helicopters which can be applied in the preliminary design stage. As many as 74 helicopter price and sizing data after the year 1997 are newly included to the out-dated coefficients in the cost estimation formula. In addition, the updated price estimation formula is added to Tishchenko's preliminary sizing method for price consideration in the preliminary design stage. Sikorsky's S-76C+ helicopter is used along with other various helicopters for comparison and validation of the sizing code as well as the new updated price estimation formula.