• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.4
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• pp.10-15
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• 2010

Light gas guns have a large number of applications in various fields of engineering. A two-stage light-gas gun can produce an extremely high pressure in a very short interval of time. In general, the two-stage light-gas gun is made up of a high pressure tube, a compression tube and a launch tube, each stage being separated by diaphragms. This can be employed efficiently in the application of ultra-high pressure liquid jets. In the present study, experiments are carried out to investigate the projectile velocity and pressure behavior in the tubes according to the pressure changes at the frist diaphragm opening. In the present study result was found that the rupture pressure of the first diaphragm has a dominant influence on piston acceleration.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.15 no.6
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• pp.3455-3459
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• 2014

This paper reports the design and experiments for a high drive force of projectile in a coil gun system. Currently, the coil gun has been studied to apply an electromagnetic launcher. A coil gun launches a projectile by the attractive magnetic force of the electromagnetic coil. The drive force of projectile is proportional to the magnetic force generated by the electromagnetic coil. The current affects the life of the coil and the current limit exists. Therefore, the coil gun design, which does not exceed the current limit and the magnetic forces are at the maximum, is required. For this purpose, this study calculated the magnetic flux density and forces of the coil gun system and determined the current limit of the coil using the Onderdonk's equation. Based on the design result, a prototype was manufactured and an experiment was conducted to measure the muzzle velocity of the projectile. The fired projectile was analyzed using a CCD camera, and the muzzle velocity was 21m/s. In addition, a comparison of the experimental value and analysis value using commercial electromagnetic analysis software MAXWELL revealed an error of approximately 9.5%.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.12
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• pp.950-958
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• 2013

The Lunar orbiter is expected to be inserted into a ~300km low Earth orbit using Korea Space Launch Vehicle-II(KSLV-II). After the states are successfully determined with obtained tracking data, the Trans Lunar Injection(TLI) burn has to be done at appropriate epoch to send the lunar orbiter to the Moon. In this study, we describe in detail the mission scenario of the Korean lunar orbiter from the launch at NARO Space Center to lunar orbit insertion(LOI) stage following direct transfer trajectory. We investigate the launch window including launch azimuth, delta-V profile according to TLI and LOI burn positions. We also depict the visibility conditions of ground stations and solar eclipse duration to understand the characteristics of the direct transfer trajectory. This paper can be also helpful not only for overall understanding of ${\Delta}V$ trend by changing TOF and coasting time but for selecting launch epoch and control parameters to decrease fuel consumption.

• Defense and Technology
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• no.2 s.168
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• pp.26-35
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• 1993

대함유도탄을 요격하기 위해서는 운동 성능이 뛰어나며 속도가 빠른 유도탄을 단시간에 발사할수 있어야 합니다. 이러한 요구 사항에 의거, 사정 거리는 비록 짧으나 대함유도탄과 같은 소형의 유도탄을 추적 및 격파할수 있는 유도탄이 필요하게 되어 단거리 지대공유도탄이 출현하여 점방어를 담당하게 되었습니다. 단거리 지대공유도탄은 경량, 소형인 유도탄으로부터 대형의 유도탄들로 형태면에서 천태만상이며, 대함유도탄의 위협이 각국 해군에 어떻게 투명되었는가를 엿볼수 있습니다

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.11
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• pp.984-997
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• 2015

Chang'e-3 consisting of a lunar lander and exploration rover was launched on December 1, 2013 aboard a Long March 3B rocket flying from Xichang space launch center. Chang'e-3 was inserted into the lunar orbit after about a 5-day transit to the Moon and landed on the targeted landing site after orbiting around the Moon for 8 days. The successful landing of the Chang'e-3 gives a lot of help to analyze the future needs of the subsystem technologies and to figure out the trajectory from launch to lunar landing as well as operation sequences in the development of Korean lunar exploration is scheduled. Therefore, the configuration and analysis of overall mission of Chang'e-3 is performed based on the public information from the press and website. As a result, overall mission trajectory is reconstructed by solving boundary condition and then estimating control variable. Visibility status and eclipse status also analyzes so communication and power charge condition is as good as to operate lunar lander. Mass budget of the lander is derived using ${\Delta}V$ according to specific impulse.

• Current Industrial and Technological Trends in Aerospace
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• v.6 no.2
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• pp.116-124
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• 2008

Korea Aerospace Research Institute(KARI) is developing COMS (Communication, Ocean and Meteorological Satellite) which is scheduled to take off in June, 2009. COMS is the first geosynchronous satellite developed in Korea which is able to perform three missions 24 hours a day. The oceanic payload was transferred from France to Korea in November, 2008 and made it possible to integrate all three payload together. After the integration COMS is planned to be transferred to Guiana Space Center (on French territory) to be launched. In this paper the trend of domestic and international development of the multi-purpose geosynchronous satellite considering the COMS is the first operational geosynchronous multipurpose satellite in the world.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.82-85
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• 2008

When a projectile travels at high speed underwater, supercavitating flowarises, in which a huge cavity is generated behind the projectile so that only the nose, i.e., the cavitator, of the projectile is wetted, while the rest of it should be surrounded by the cavity. In that case, the projectile can achieve very high speed due to the reduced drag. Furthermore if the nose of the body is shaped properly, the attendant pressure drag can be maintained at a very low value, so that the overall drag is also reduced dramatically. In this study, shape optimization technique is employed to determine the optimum cavitator shape for minimum drag, given certain operating conditions. Simultaneous optimization technique is proposed for efficient cavitator shape optimization, in which the cavity and cavitator shape are determined in a single optimization routine.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.1
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• pp.1-10
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• 2010

Design and performance evaluation of $H_2O_2$ monopropellant thrusters to be used at reaction control of space launch vehicles were presented in this paper. Design thrust level was determined as 100, 250 Newton which is nominal thrust level for commercial space launch vehicles. Qualification thruster models including solenoid valves were developed after the reactor design were evaluated at engineering thruster models. Each thruster was evaluated by measurement of characteristic velocity, thrust, specific impulse, and pulse response times at sea level test condition.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2015.10a
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• pp.439-441
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• 2015

The ballistic missile is very threatening weapon system because it is difficult to detect and intercept due to fast speed. Recently, many countries worry about North Korea's ballistic missile launching tests especially the success of launching Kwangmyongsong-3 satellite by Eunha-3 long range rocket at 2012. This event means announcement of North Korea have capability to develop ICBM(Intercontinental Ballistic Missile) to all over the world. In this paper, it is surveyed and described that history, types and threat of ballistic missiles.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.40 no.1
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• pp.209-216
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• 2015

It is difficult to detect, track and intercept ballistic missile because of its high speed and short flight time from launching to target area. In order to increase the success rate of a ballistic missile interceptor, it is important to track the flight trajectory for a long time after the detection in the early launch. Radar Cross Section(RCS) of the target is important when the target to be detected by the radar, and the difference between the RCS value greatly changes depending on the viewing direction during the flight missile trajectory. In this paper, it is assumed that a ballistic missile is launched at east coast of North Korea, observe that missile by a land based radar and sea deployed radar. And it is analyzed and compared that RCS difference of ballistic missile.