• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.8
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• pp.18-25
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• 2005

This paper describes a supersonic separation of air-launching rocket from the mother plane. Three dimensional Euler equations were numerically solved to analyze steady/unsteady state fluid flows. The results of simulation clearly demonstrate effect of shock-expansion wave interaction between the rocket and the mother plane. Moreover, important influential factors at separating stage of the rocket were extracted with a comprehensive analysis. Finally, from the consideration of supersonic-separation, a guideline to safety-separation is given to the design of supersonic air-launching rocket.

• Journal of Astronomy and Space Sciences
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• v.16 no.1
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• pp.79-88
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• 1999

The satellite experiences the severe launch environment such as vibration, acceleration, shock, and acoustics induced by rocket. Therefore, the satellite should be designed and manufactured to endure such severe launch environments. In this paper, we describe the structure of the KITSAT-3 FM(Flight Model) and the processes and results of the launch environmental test to ensure the reliability during launch period.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.168.2-168.2
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• 2012

위성체가 발사체에 실려 발사될 때에 매우 높은 가속도에 의한 정적, 동적 하중 및 공기의 저항에 의한 하중, 연소 가스 분출시 발생하는 음향에 의한 하중, 발사체로부터 분리될 때 발생하는 충격 하중 등 여러 가지의 극심한 하중을 겪게 된다. 이러한 발사 환경에 대한 안정성을 검토하기 위해 발사체 업체에서 제공하는 매뉴얼 상의 설계 조건을 이용하여 설계하고 해석하여 검증한다. 천리안 위성의 후속 위성으로, 해상도 및 채널 성능 향상된 차세대 기상탑재체를 탑재하고 현재 개발 중인 정지궤도 복합위성에 대해 발사환경을 고려한 개념 설계 및 초기 해석을 수행하였고, 개발 가능성 분석을 그 목적으로 한다.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.123-128
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• 2010

Science and Technology SATellite-3 (STSAT-3) is science purpose satellite which weighs below 170kg. This is classified as small satellite or micro satellite more specifically. The launch vehicles (launchers) for small satellite has their own requirements for environmental interface. Since the small satellites are usually launched with cluster or multiple payloads, the selection option for appropriate launcher is limited. Therefore, the satellite should be designed with the consideration of environmental requirements of these launchers. In this paper, the environmental requirement of most candidated launchers for small satellite is summarized and give satellite environmental requirement to accommodate all launchers requirements.

• Proceedings of the KSME Conference
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• 2005.11a
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• pp.92.2-92.2
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• 2005

• Transactions of the Korean Society of Mechanical Engineers A
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• v.36 no.11
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• pp.1473-1478
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• 2012

This paper presents the development of a fracture-type protector for carrying a reconnaissance robot to a remote target area. Instead of a conventional unlocking mechanism, a separation method based on the fracture of assembled parts was implemented in the proposed lightweight protector in order to improve the feasibility for a real battlefield. Simulations using the finite element model of the protector and the robot were performed to verify the fracture under the given loading conditions, and shock experiments using a drop table were performed to calculate shock transmittance through the protector to the robot. Several field tests for a 100-m flight proved that the proposed scenario (launching, flying, landing, and separation) was achieved successfully.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.177-180
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• 2010

Two-stage light gas gun, sorted with Ballistic Range System, is used to research spray characteristics of supersonic liquid jets. When high pressure tube was pressurized to the 135 bar, diaphragm films which composed with OHP film are ruptured. Expansion gases accelerate a projectile approximately 250 m/s at the exit of pump tube. And accelerated projectile collides with liquid storage part and liquid jets were injected into supersonic conditions. Supersonic liquid jets show the multiple jets and generate shockwave at the forward region of jets. Supersonic liquid jets of speed and shockwave angle have different value at each case. Supersonic liquid jets with minimum velocities are injected with M=1.53 at the geometry condition of L/d=23.8.

• Computational Structural Engineering
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• v.11 no.4
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• pp.147-154
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• 1998

강체 충격자가 납 표적에 33m/s ∼ 141m/s의 속도로 충돌할 때의 침투특성을 연구하기 위하여 Jognson 이론식을 이용한 이론해석과 AUTODYN 코드를 이용한 수치해석 및 실험장치를 이용한 실험측정을 실시하고 그 결과들을 비교 분석하였다. 실험장치로는 가스압력식 발사장치를 설계 제작하였으며, 실험용 충격자로는 충돌부위 형상이 반구형인 반구형 충격자와 원추형인 원추형 충격자 2종류를 사용하였다. 또한, 납재료에 대한 동적 유동응력을 얻기 위하여 홉킨스 압력봉실험을 수행하였다. 침투특성에 관한 연구결과, 이론적 해석결과는 저속 충돌범위(반구형 충격자 : 53m/s, 원추형 충격자 ; 73m/s)에서 실험결과치와 93%이상 잘 일치하였으며, 수치해석결과는 전체적인 충돌속도 범위에서 반구형 충격자인 경우 73%이상, 원추형 충격자인 경우 86%이상 일치하였다.

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