• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2012년도 제38회 춘계학술대회논문집
• /
• pp.35-41
• /
• 2012

액체로켓 추력실의 성능 예측 및 초음속 노즐부 형상 설계에 활용 중인 in-house 해석 도구를 이용하여 재생냉각 연소기에 대한 성능/냉각 통합해석을 수행하였으며, 막냉각 유량 및 외곽 분사기열의 혼합비 변화에 따른 연소 성능과 냉각 성능 간 trade-off 경향을 고찰하였다. 향후 막냉각 및 주요 설계인자의 최적화 도구로 활용될 수 있도록 개발 연소기에 대한 시험 결과와의 비교 등을 통하여 수치해석 도구를 검증/개선해나갈 계획이다.

• 대한기계학회:학술대회논문집
• /
• 대한기계학회 2007년도 춘계학술대회A
• /
• pp.1143-1148
• /
• 2007

LRE(Liquid propellant Rocket Engine) is one of the important parts to control the motion of rocket. For operation of rocket in error boundary of the set-up trajectory, it is necessarily to control the thrust of LRE according to the required thrust profile and control the mixture ratio of propellants fed into combustor for the constant mixture ratio. It is not easy to control thrust and mixture ratio of propellants since there are co-interferences among the components of LRE. In this study, the dynamic model of LRE was constructed and the dynamic characteristics were analyzed with control system as PID control and PID+Q-ILC(Iterative Learning Control with Quadratic Criterion) control. From the analysis, it could be observed that PID+Q-ILC control logic is more useful than standard PID control system for control of LRE.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2010년도 제34회 춘계학술대회논문집
• /
• pp.202-205
• /
• 2010

이 연구에서는 아산화질소의 촉매 분해를 이용한 하이브리드 로켓의 자연 점화에 관한 연구를 수행하였다. 하이브리드 로켓은 촉매 점화기, 고체연료, 연소기, 노즐로 구성하였다. 아산화질소를 분해하기 위해 Ru 촉매를 $Al_2O_3$ 지지체에 함침법을 이용하여 담지하였고, 제조된 촉매의 반응온도에 따른 아산화질소 분해율을 측정하였다. 촉매 점화기의 작동조건에 따른 온도변화를 측정하였고, 하이브리드 로켓의 자연 점화에 대한 가능성을 확인하였다.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2003년도 제21회 추계학술대회 논문집
• /
• pp.137-140
• /
• 2003

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2002년도 제18회 학술발표대회 논문초록집
• /
• pp.50-54
• /
• 2002

With a view to estimating the effect of flows on evolving sprays and combustion in ramjet combustor and corresponding extent of combustion, ram air flows in combustion chamber is numerically experimented. Preconditioned three dimensional Navier-Stokes system of equations per transient, compressible, turbulent flows in IRR(Integral Rocket Ramjet) combustor is numerically integrated. Flow properties in the side-dump ramjet combustor, rectangular duct with two 60-deg curved inlets located radially at an angle of 180-deg, are addressed in terms of mixing quality and extent of combustion efficiency.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2008년도 제31회 추계학술대회논문집
• /
• pp.455-456
• /
• 2008

A numerical study was conducted on the effect of flame holder which could be added to the inlet duct of Integral Rocket-Ramjet. Two different types of flame holder installations, flame holder without sudden expansion region and flame holder with small sudden expansion region, were compared and showed different flame shapes and pressure rise in the combustor.

• 한국추진공학회지
• /
• 제11권5호
• /
• pp.31-36
• /
• 2007

연소 압력이 70 bar인 고압 축소형 연소기의 연소성능 특성을 알아보았다. 모든 연소시험은 하드웨어의 손상 없이 성공적으로 이루어졌다. 분사기의 혼합특성과 분사기 배열이 연소성능에 큰 영향을 미치는 요소임을 파악하였다. 연소기의 특성속도는 외부 혼합보다 내부 혼합 분사기에서 더 크게 나타났으며 단위분사기당 추진제의 유량이 감소함에 따라 특성속도도 증가하였다. 추진제 매니폴드 및 연소실에서 측정된 압력 섭동은 평균 연소압력의 3% 이하로 연소안정성 기준치 보다 낮은 값을 보여 안정적인 연소기임을 보였다.

• 한국연소학회:학술대회논문집
• /
• 한국연소학회 2014년도 제49회 KOSCO SYMPOSIUM 초록집
• /
• pp.311-313
• /
• 2014

High pressure combustion with multiphase--liquid, gas, and supercritical phase--mixtures are widely used technology in the high efficiency liquid propellent rocket engine. This is the typical characteristics differentiate from the combustor of conventional air-breathing engines. Therefore, successful research of high pressure combustion at supercritical condition is essential to develope a high efficiency liquid rocket engine. Numerical studies have been carried out to explore capabilities of numerical method for LOx-CH4 non-premixed flames at high pressure. In this paper, corresponding numerical results are presented and compared with experimental result of MASCOTTE facility.

• 한국항공운항학회지
• /
• 제15권4호
• /
• pp.38-44
• /
• 2007

This paper describes the structural safety of solid fuel in the Hybrid Rocket Motor (HRM). Hybrid rocket combustion has the distinct regression characteristics which include the process of thermal pyrolysis and fuel vaporization. Most of all, this regression characteristics would structurally affect the strength of the fuel having a multi-port configuration, and even may cause the breaking from the fuel grain. This problem would probably influence the performance and operating safety of HRM. Therefore, for the safe operation of HRM, the critical port radius which determines the structurally safe region was discussed from the heat analysis of the solid fuel.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2008년 영문 학술대회
• /
• pp.260-265
• /
• 2008

A numerical scheme for solid propellant rocket has been studied using preconditioning method to research unsteady combustion processes for the double-base propellant with a converging-diverging nozzle. The Navier-Stokes equation is solved by dualtime stepping method with finite volume method. The turbulence model uses a shear stress transport modeling. The species equation follows up the method of Xinping WI, Mridul Kumar and Kenneth K. Kuo. A preconditioned algorithm is applied to solve incompressible regime inside the combustor and compressible flow at nozzle. Mass flux was evaluated using modified advective upwind splitting method. The simulated result the comparison a fully coupled implicit method and a semi implicit method in terms of accuracy and efficiency. This report shows the result of solid rocket propellant combustion.