http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
자세제어 추력기 배기가스에 의한 태양전지판의 동적 영향 분석
채종원(Jongwon Chae),한조영(Cho Young Han),전형열(Hyoung Yoll Jun) 한국항공우주학회 2015 韓國航空宇宙學會誌 Vol.43 No.9
본 연구의 목적은 인공위성의 자세제어 추력기 배기가스가 태양전지판에 충돌하여 생기는 동적 영향인 교란력과 교란토크를 분석하는 것이다. 두 개의 매개변수인 태양전지판과 추력기 사이의 거리와 추력기의 경사각을 사용하는 Sweep Analysis를 실시하여 교란력과 교란토크 원(原)데이터베이스를 만들었다. 이 데이터베이스를 기반으로 이 두 개의 매개변수에 의해 달라지는 교란력과 교란토크의 특성을 기술하는 3차 다항 근사식을 만들고, 각 태양전지판의 각(角)위치에 대해 근사식의 계수들을 최종 결과로서 얻는다. 이 결과들은 자세제어계의 입력 자료로서 사용되어 추력기 배치 최적화에 사용된다. 정지궤도복합위성의 후보 태양전지판 두 종류에 이 분석을 적용하여, 교란력과 교란토크 결과를 비교 분석하였다. The purpose of this study is to analyse the dynamic disturbances(disturbed forces and disturbed torques) due to attitude control thrusters plume impingement on the solar arrays. To produce database of the dynamic disturbances a sweep analysis was done, in which the two parameters are used; the distance between the thruster and solar arrays and the thruster tilt angle. Based on the database, a third order polynomial approximation is computed to represent the characteristics of the disturbed forces and torques. The final results are the coefficients of the approximation for each solar array angle position. These results as input data are used to optimize the configuration of the attitude control thrusters. This analysis is appled to the two candidate solar arrays for Geo-Kompsat-2 satellite and the results of the disturbed forces and disturbed torques are compared and analysed.
채종원(Jongwon Chae),한조영(Cho-Young Han),유명종(Myoung-Jong Yu) 한국항공우주학회 2012 韓國航空宇宙學會誌 Vol.40 No.3
본 논문은 천리안 위성의 추진계를 간략하게 소개하고 천리안 위성의 발사 및 초기 위성 운용 수행 임무 중 위성 추진계의 일련의 과정에서 측정된 원격측정치를 제시한다. 일부 원격측정치는 기 개발된 프로그램의 계산결과와 비교하였다. 추진계의 압력변화는 주로 두 단계로 구성된다. 첫 번째 단계는 위성 추진계의 초기화, 즉 안전을 위해서 추진제 탱크 후단부터 추력기 상단까지 충전된 헬륨 가스를 진공인 우주공간으로 빼는 배출단계를 시작으로, 이 빈 배관망에 산화제와 연료를 각각 채우는 충전단계를 거치고 마지막으로 추진제 탱크의 압력을 일정한 압력까지 올리는 가압단계이다. 두 번째 단계는 목표궤도에 이를 때 까지 수행하는 액체원지점엔진의 연소 단계이며, 이 단계에서는 추진제 탱크의 압력을 일정하게 유지 하기 위해서 가압제인 헬륨을 사용한다. 이 프로그램은 향후에 개발되는 정지궤도복합위성의 기초 설계자료 생성에 사용할 수 있을 것이다. In this paper the Chemical Propulsion Subsystem of COMS is briefly explained and some telemetries acquired by a series operations of CPS during the Launch and Early Operation Phase of COMS are presented. The pressure and temperature of pressurant tank telemetries are compared with the results of the developed computer program. The changes in pressure are due to the two major phases. The first one is the initialization phases of CPS composed of the venting phase to vent the helium gas in the pipe network from the downstream of the propellant tanks to the thrusters for safety, the priming phase to fill the vented pipe network with oxidizer and fuel respectively and then the pressurization phase to pressurize the ullage of propellant tank to regulated pressure. And the other is the apogee engine firings in which COMS CPS is in the orbit raising phase to use helium as a pressurant to keep the pressure of propellant tank as the liquid apogee engine get fired until COMS reached to the target orbit. This program can be applicable to prepare basis design data of the next Geostationary Satellite CPS.
A FLUID TRANSIENT ANALYSIS FOR THE PROPELLANT FLOW IN A MONOPROPELLANT PROPULSION SYSTEM
채종원(Jongwon Chae) 한국전산유체공학회 2005 한국전산유체공학회지 Vol.10 No.2
A fluid transient analysis for the propellant flow in a monopropellant propulsion system is conducted by using the method of characteristics(MOC). It reviews algebraic simultaneous equations method and Cramer's rule method utilized to drive the compatible and characteristic equations to understand MOC extensively. The identification of fluid transient phenomena of propulsion system of Koreasat 1 is carried out through parametric studies. The valve response time is one of the dominant parameters governing the fluid transient phenomena. The results show that the shorter closing time induces the greater pressure response amplitude. And it shows that the installation of in-line orifice is effectively to limit the fluid transients in rapid valve response time and at high pressure. But it seems that the effect of orifice weakens at slow valve response time and at low pressures.
Jongwon Chae(채종원) 한국전산유체공학회 2006 한국전산유체공학회지 Vol.11 No.1
A fluid transient analysis on the Koreasat 1 & 2 pipeline system is conducted through numerical parametric studies in which unsteady friction results are compared with quasi-steady friction results and show relatively accurate prediction of the response curve with the unsteady friction. The code developed and used in this analysis has finished verification through comparing with the original Zielke model, the full and recursive convolution model and quasi-steady model as a reference. The unsteady friction is calculated by the recursive convolution Zielke model in which a complete evolution history of velocity field is no longer required so that it makes the fluid transient analysis on the complicated system possible. The results show that the application of quasi-steady friction to model cannot predict the entire response curve properly except the first peak amplitude but the application of unsteady friction to model can predict reasonably the response curve, therefore it is to know the characteristics of the propulsion system.
이원추진제 추진시스템의 배관망에 대한 비정상 마찰을 고려한 과도기유체 해석
채종원(Jongwon Chae),한조영(Cho Young Han),김정훈(Jung-Hoon Kim),전형열(Hyoung Yol Jun) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
A fluid transient analysis on the pipe network of bipropellant propulsion system is conducted through numerical parametric studies in which unsteady friction results are compared with quasi-steady friction results and also show the pressure drop results during the liquid apogee engine firing. The fluid transient analysis program has verified through comparing with the original Zielke model, the full and recursive convolution model and quasi-steady model as a reference. And the pressure drop program also has verified through comparing with results of the well-known program, EPANET2. The bipropellant propulsion system has two different fluids as fuel and oxidizer, and mostly they are hypergolic combination so that the valve opening and closing of the thrusters, that cause the pressure waves, shall take place simultaneously to get proper performance. The different physical properties of the fuel and oxidizer result in the different responsive to the same valve opening and closing. The response results may be helpful to know the characteristics of the bipropellant propulsion system and design it.