• Current Industrial and Technological Trends in Aerospace
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• v.4 no.2
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• pp.86-97
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• 2006

일본은 1954년 도쿄대학의 이도가와 교수가 로켓연구반을 구성하여 연구와 실험을 시작한 후 1955년 8월에 펜슬로켓을 제작하여 수평비행실험을 시작하였다. 이후 베이비 로켓, 카파 로켓, 람다 로켓으로 이어지는 개발과정에서 1970년 람다로켓인 L-4S-5 로켓으로 인공위성 ‘오수미’를 발사하는데 성공하여 자체 위성발사국의 지위를 얻었다. 그러면서 미국으로부터 발사체 기술을 받아 N-1 로켓을 개발하여 1975년에 성공적으로 발사하였다. 이후 자체적으로 기술개발에 성공한 H-I 로켓에 이어 일본의 기간 발사체가 된 H-II A 로켓에 이르기까지 일본은 우주발사체 개발을 지속적으로 꾸준히 발전시켜왔다. 본 논문에서는 일본의 기간 발사체가 된 H-II A 로켓 및 H-II B(H-II A 능력향상형 로켓)에 이르기까지 일본의 로켓 개발과정을 설명하고 또 H-II A 로켓이 어떻게 일본의 기간 로켓이 되었는지 또 H-II A 능력 향상형 로켓, H-II B 로켓의 향후 에 대하여 논의하고자 한다.

• Journal of Aerospace System Engineering
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• v.13 no.3
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• pp.70-77
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• 2019

This study presents the numerical investigation of the trajectory of rocket launched from a helicopter. The nonlinear mathematical model of armed configuration of UH-60 helicopter was developed while Hydra 70 unguided rocket was modeled to simulate the rocket behavior. The effects of various inflow models on the launched rocket trajectory are obtained. Similarly, rocket launch simulation was performed to determine the unsafe flight maneuver condition where the rocket trajectory is critically close to the helicopter main rotor tip path plane.

• Aerospace Industry
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• v.16
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• pp.21-23
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• 1994

세계열강들이 인공위성 발사를 위하여 각종 최신 로켓의 제조 발사경쟁이 한창인 가운데 일본은 지난 2월 1일 H2형 대형 로켓을 발사하여 구미계나 미소 각국과 거의 비슷한 실력을 발휘했다고 보도 했다. 여기 동 H2형 일본 로켓의 성능과 실험 등에 관한 보도 기사를 간추려 본다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.7
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• pp.525-534
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• 2019

Water rocket is a pressurized liquid propellant rocket that shares the same basic principles of space launch vehicles. Water rockets can be used as an engineering educational material for the liquid rocket principles and the launch vehicle systems, far beyond the scope of K-12 level science education. In this paper, the principles and theories of water rocket propulsion and flight dynamics was investigated at the level of undergraduate rocket engineering classes. Also, the system level design and operation of water rocket is summarized by including the components of launch vehicle, launch pad, payload and recovery as well as altitude measurement methods.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.748-751
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• 2010

To launch rocket on launch pad, propellants and gases are charged into the rocket by remote control system. Using pneumatic pressure-reducing regulators, kinds of gases with various pressure levels are supplied into launch pad. As most of operations for launching the vehicle are remotely controled in the launch control room, pressure pulsations due to rapidly gas supply at the upstream of regulators can make the required operating pressure range missed and cause damage to the regulators. In this paper, the optimum design methods of pressure regulators of pressure-reducing system on launch pad using high-pressure gases were investigated to solve the aforementioned problems and for stable gas supply to launch pad.

• Defense and Technology
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• no.8 s.174
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• pp.30-35
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• 1993

과학 1호로 로켓의 추진기관 개발을 통하여 항공우주연구소는 고체 추진제 로켓 모타 설계에 필요한 소프트웨어의 개발 및 그 활용, 그리고 경제적인 로켓 모타의 개발방법 등등 많은 것을 배웠습니다 또한 이는 앞으로 우주개발을 위한 새로운 로켓 추진기관 개발에 좋은 경험이 되었습니다 더욱 뜻깊은 것은 이번 과학 1호 로켓의 발사는 명실공히 산.학.연의 종합적인 연구체계로 이루어졌다는 것입니다

• 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 Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.820-824
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• 2010

The purpose of this study is to develop basic technology of hybrid rocket vehicle by constructed and launched. This small hybrid rocket using HDPE/LN2O and Aluminium steel for its body (weight : 12.5 kg, diameter : 114 mm, height : 1.8 m) was designed. The fuel grain and injector were designed for 50 kgf thrust and burning time 2.5 sec. This rocket was loaded the data acquisition device for obtaining data of pressure and velocity during its flying and equiped an automatic ejector system using spring/motor and timer to collect the rocket more safely after launching. It was launched successfully, but found some problem that the rocket's weight was heavier than expected and the thrust was not enough to reach the designed altitude and analyzed its flight path way.

• Proceedings of the KIEE Conference
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• 2002.07d
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• pp.2656-2658
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• 2002

로켓과 지상장비의 각 모듈 사이에서 교환되는 데이터와 제어 정보, 상호작용 등을 정확하게 기술하기 위해 UML 객체 지향 방법을 이용해서 로켓 발사시스템을 모델링한다. 이렇게 만들어진 상위레벨 객체 모델을 기반으로 해서 발사통제 시스템에서 지시하는 명령들의 시퀀스로서 발사 시나리오를 구성한다. 본 논문의 UML 객체 다이어그램과 발사 시퀀스 다이어그램은 로켓과 지상장비를 운영하고 통제하는 다양한 작업에 유용하게 사용될 수 있다.

• The Journal of the Acoustical Society of Korea
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• v.39 no.4
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• pp.331-341
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• 2020

At liftoff, launch vehicles are subject to harmful acoustic loads due to the intense acoustic waves generated by propulsion systems. Because these waves can cause electronic and mechanical components of launch vehicles and payloads to fail, predicting and mitigating acoustic loads is an important design issue. This article presents the latest information about the generation of acoustic waves and the acoustic design methods applicable to the launch pad. The development of the Japanese Epsilon solid launcher is given as an example of the new methodology for launch pad design. Computational fluid dynamics together with 1/42 scale model testing were performed for this development. Effectiveness of the launch pad design to reduce acoustic loads was confirmed by the post-flight analysis.