• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2005년도 제24회 춘계학술대회논문집
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• pp.159-167
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• 2005

Considering the increase of interest in $H_{2}O_2$ as a rocket propellant, a test facility and a rocket engine have been developed to research in areas of $H_{2}O_2$ mono-propellant propulsion. A detailed design-study of a $H_{2}O_2$ mono-propellant rocket engine of 100-N thrust is presented. Several firings attempted in early stage had some problems with misfire and chamber pressure decrease. Low environmental temperature and impurities included in hydrogen peroxide were considered to be the reasons. Addressing these points resulted in successful firing of the rocket engine and obtained thrust about $100\sim107-N.$

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2006년도 제26회 춘계학술대회논문집
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• pp.110-117
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• 2006

Considering the increase of interest in $H_2O_2$ as a rocket propellant, a test facility and a rocket engine have been developed to research in areas of $H_2O_2$ mono-propellant propulsion. A detailed design-study of a $H_2O_2$ mono-propellant rocket engine of 100-N thrust is presented. Several firings attempted in early stage had some problems with misfire and chamber pressure decrease. Low environmental temperature and impurities included in hydrogen peroxide were considered to be the reasons. Addressing these points resulted in successful firing of the rocket engine and obtained thrust about $100\sim107-N$.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.423-426
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• 2006

An analysis is made of flow and rocket motion during a supersonic separation stage of air-launching rocket(ALR) from the mother plane. Three-dimensional compressible Navier-Stokes equations is numerically solved to analyze the steady/unsteady flow field around the rocket which is being separated from the mother plane configuration(F-4E Phantom). The simulation results clearly demonstrate the effect of shock-expansion wave interaction between the rocket and the mother plane. To predict the behavior of the ALR according to the change of the C.G., three cases of numerical analysis are performed. As a result, a design-guideline of supersonic air-launching rocket for the safe separation is proposed.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 추계 학술대회논문집
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• pp.155-160
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• 2004

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. To solve the Euler equations, named CFD-FASTRAN that is commercial computation code. 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.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 추계학술대회논문집
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• pp.250-254
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• 2002

It is conducted to analyze vibration loads on KSR-III(KSR: Korea Sounding Rocket) and its major segments during their ground transportation and various handling process. These loads may be different from the real flight environment. Inadequate assessment of these loads can cause not only local damages on the rocket system but also the critical problem like flight mission failure. Therefore, transportation and handling loads must be considered during design and attenuated to ensure that the rocket structural damage does not occur. This work is concerned with the generation of criteria and prediction of transportation and handling loads for KSR-III. The results show that the shipping container is well designed to satisfy the design requirements. The maximum vibration level recorded during whole transportation and handling for KSR-III is less than 2g, the criteria of KSR-III movement condition.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2006년도 제27회 추계학술대회논문집
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• pp.415-418
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• 2006

하이브리드 추진제는 연소 중 연료의 후퇴율 및 연소 면적의 변화로 인해 O/F비가 변화하므로 이로 인해 설계 및 해석에 어려움을 가지게 된다. 본 연구에서는 요구임무를 만족하는 하이브리드 로켓모터에 대한 설계를 수행하였다. 하이브리드 모터의 기초 설계를 실시하고 그 결과를 이용하여, 일정한 산화제 유량이 공급된다는 가정 하에, 연소 시 연소면적변화에 따른 O/F비 변화를 고려한 하이브리드 모터의 내탄도 해석을 실시하였으며, 그 결과를 이용하여 로켓의 외탄도 해석을 실시하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2009년도 춘계학술대회 논문집
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• pp.417-418
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• 2009

Aiming at time-dependent performance prediction of Liquid Rocket Engine(LRE) system, Program for Dynamic Characteristic Prediction of LRE is overviewed, and a modeling and dynamic analysis of rocket engine system with reference to developed transient simulator for LRE is outlined.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년도 제30회 춘계학술대회논문집
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• pp.57-60
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• 2008

고체 추진기관 설계에는 고체 추진제 연소속도, 요구 추력, 연소관 압력, 연소시간, 탄의 직경, 길이, 무게, 최대 가속도와 같은 많은 설계요소 및 제약이 존재한다. 이러한 요소 및 제약의 최적화를 위해 내탄도/외탄도 해석을 위한 통합 설계 프로그램을 개발하였고 고체 로켓 모터의 시험을 통해 그 유용성을 확인하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2009년도 춘계학술대회 논문집
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• pp.414-416
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• 2009

In order to build a transient simulation program for a high thrust liquid rocket engine(LRE), a static performance simulation program for components were made. The components were the thrust chamber (combustion chamber and supersonic nozzle), centrifugal pump (impeller and volute casing), impulse turbine, and flow control devices (control valve and orifice). Simplified mathematical models based on classical thermodynamic and inviscid theories were used to remove complexity and enhance the utility of the program. We examined the results of each program qualitatively for validate each component modeling.

• 한국항공우주학회지
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• 제47권7호
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• pp.525-534
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• 2019

물로켓은 우주발사체와 동일한 기본원리를 가지는 가압식 액체추진제 로켓이다. 물로켓은 청소년용 과학교육 교보재 수준을 훨씬 넘어, 대학 수준의 액체 로켓 및 발사체 체계 공학 교육의 도구로 활용될 수 있다. 본 논문에서는 물로켓의 추진 및 비행 원리와 이론을 대학 학부의 로켓 공학 교육 수준에서 고찰하였다. 아울러 발사체와 발사대, 탑재체, 회수 및 고도 장치와 방법 등 체계 수준의 물로켓 설계와 운영에 대한 사항들을 정리하였다.