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이상복(Sang-Bok Lee),노태성(Tae-Seong Roh) 한국추진공학회 2014 한국추진공학회 학술대회논문집 Vol.2014 No.12
본 연구에서는 우주발사체용 액체 로켓 추진 시스템의 성능 해석 프로그램을 개발하였다. 우주발사체 시스템 해석 및 설계 프로그램에 활용될 수 있도록 프로그램의 입출력 변수를 구성하였다. 개발된 프로그램은 액체로켓엔진의 성능과 탱크의 크기와 중량을 예측하며, 단순화된 우주발사체 시스템 해석프로그램과의 연동을 통해 논리적인 오류 없이 연동됨을 확인하였다. 추후 공력 구조 등 타 분야의 정밀도 높은 프로그램과 연동하여 다분야통합최적설계에 활용될 수 있을 것으로 판단된다. In this study, the system analysis program of liquid propellant propulsion system for space launch vehicle. The input and output variables have been set to be applied in the launch vehicle analysis program. The developed program can obtain performance of liquid rocket engine, size and weight of the propellant storage tanks. It was ascertained that the program can be interconnected with simplified launch vehicle program without logical fallacy. This program is expected to be applied in the multi-disciplinary design optimization of launch vehicle with other disciplinary such as aerodynamic, structure and trajectory.
이상복(Sang-Bok Lee),손민(Min Son),서종철(Jongcheol Seo),임태규(Taekyu Lim),노태성(Tae-Seong Roh),구자예(Jaye Koo),김귀순(Kuisoon Kim) 한국추진공학회 2013 한국추진공학회지 Vol.17 No.4
The system analysis and design program of the liquid rocket engine has been developed for preliminary conceptual design process. The program analyzes the engine system and obtains optimal design variables by optimization methods such as genetic algorithm for the higher specific impulse and thrust to weight ratio using given input parameters and requirements. For the users convenience, the GUI has been offered. The 3-dimensional model for the visualization of results has been interconnected with the CATIA program. The results are expected to be applied to the design process of the space launch vehicle for the analysis and selection of the propulsion system.
액체로켓엔진 통합 설계를 위한 에너지 발란스 프로그램 개발
이상복(Sang-Bok Lee),노태성(Tae-Seong Roh) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.11
액체로켓엔진 단계식 연소 사이클에 대한 에너지 발란스 프로그램을 개발하였다. 엔진을 추력실, 터보펌프, 터빈, 예연소기, 공급계 부품 등으로 모듈화 하여 각 모듈 프로그램을 제어하는 방식을 사용하였다. 이를 통해 에너지, 질유량, 압력의 균형을 맞추었으며 대표적인 단계식 연소 사이클인 스페이스 셔틀 메인 엔진의 자료를 바탕으로 비교 검증하였다. The energy balance program which can balance the relations among energy, mass flow, pressure in the staged-combustion cycle of the liquid rocket engine has been developed. The modular approach has been chosen for the analysis; the engine cycle consists of the elements from the predefined component analysis program. The engine with the staged-combustion cycle has been decomposed into several principal component modules, such as a thruster chamber, turbopumps, turbines, supply system components and a pre-burner. The program has been verified with comparison of the results to the selected data of the space shuttle main engine.
장진성(Jin-Sung Jang),성형건(Hyung-Gun Sung),유승영(Seong-Young Yoo),노태성(Tae-Seong Roh),최동환(Dong-Whan Choi) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.11
1-D 강내탄도 전산해석 코드인 IBcode를 이용하여 점화제 주입유량 조절을 통한 화포 약실 내 차압 감소방안 연구를 수행하였다. 대구경 화포의 경우 추진제의 점화를 위해 고온의 점화제를 뇌관의 주입구를 통해 약실에 주입시킨다. 따라서 각 주입구를 통해 주입되는 점화제의 유량이 약실 내 추진제의 연소에 영향을 미치게 된다. 기존의 뇌관의 경우 각 주입구의 점화제 유량이 일정하게 설계되어 있다. 이에 본 연구에서는 각 주입구에서의 점화제 유량을 다르게 하여 추진제의 연소에 차이를 주었다. 해석 결과 점화제 주입유량을 탄저 쪽 방향으로 증가시킬 경우 점화제 주입유량이 일정할 경우에 비해 강내 차압이 감소함을 확인하였다. Study on differential pressure in the chamber of cannon by adjusting the mass flow of ignition-gas has been conducted using the 1-D interior ballistics numerical code called IBcode. In case of large-caliber cannon, high temperature ignition-gas is injected to the chamber through the side hole of the primer to ignite the propellant. Therefore, mass flow of injected ignition-gas affects the propellant combustion in the chamber. Mass flow of each side hole of the current primer was uniformly distributed. In this study, differences of propellant combustion with different mass flow of each side hole have been imposed. Results in case of the mass flow increase in the direction to the base show that the differential pressure decreases compared to the uniformed mass flow.
장진성,성형건,노태성,최동환,Jang, Jin-Sung,Sung, Hyung-Gun,Roh, Tae-Seong,Choi, Dong-Whan 한국군사과학기술학회 2012 한국군사과학기술학회지 Vol.15 No.3
Performance analysis of the interior ballistics has been conducted using the 1-D numerical code called IBcode according to the various conditions such as length of ignition-gas injector, amount of ignition-gas, mass of projectile, and drag force of projectile. In case of the length of ignition-gas injector, the 25~100 % of the full-injector length has been considered as well as the mass & mass flow of the ignition-gas. The mass of the projectile 5~70 kg and its drag force of 0~69 MPa have been also considered. Variables such as breech & base pressure, negative differential pressure and muzzle velocity for the performance analysis have been sorted, too. Firing conditions for the optimal performance have been investigated through these variables.
장진성(Jin-Sung Jang),성형건(Hyung-Gun Sung),노태성(Tae-Seong Roh),최동환(Dong-Whan Choi) 한국추진공학회 2012 한국추진공학회지 Vol.16 No.1
The position effect of the solid propellant in the combustion chamber on the decrease of the differential pressure has been investigated using the IBcode. Generally the metallic cartridge or CCC (combustible cartridge case) are used to load the propellant of the gun propulsion system. The position of the cartridge(propellant) is, therefore, a major factor for the interior ballistics in case the combustion chamber is larger than the cartridge. In this study, three different positions in the empty space of the chamber have been considered. As results, the case of the propellant located in the region near the base and breech has shown that the negative differential pressure and the difference between the breech pressure and the base pressure are much higher than those of the case of the propellant located in the center of the chamber. The case of the propellant in the center of the chamber is, therefore, more profitable to improve the performance of the interior ballistics.