剩余推进剂排放对卫星表面污染量的计算  

Computation of satellite surface contamination from space emission of remained propellant

作　　者：何培杰[1] 陆宏圻[1] 向清江[1] 

机构地区：[1]武汉大学动力与机械学院,湖北武汉430072

出　　处：《武汉大学学报（工学版）》2005年第6期123-127,共5页Engineering Journal of Wuhan University

基　　金：湖北省自然科学基金(2004ABA009);中国航天科技集团公司一院一部委托项目资助

摘　　要：分析了某运载火箭的第三级火箭在星箭分离后,贮箱内剩余推进剂排放的物理过程;应用Euler理论的多相流体模型,建立了剩余推进剂排放气-粒两相湍流流动的数学模型;计算了剩余推进剂排放对卫星造成的最大污染量,为推进剂排放方案的实施与否提供理论依据.The physical processes of remained propellant space emission from the tank of the third stage rocket after the separation of satellite-rocket for a launch vehicle are analyzed. The mathematic model of turbulent gas-particle flows of remained propellant space emission is established by applying multi-phase fluid model of Euler theory. The maximum contamination of satellite surface from space emission of remained propellant is calculated. The theoretical criterion is provided for performing the remained propellant expelling scheme.

关 键 词：剩余推进剂 羽流污染 多流体模型 气固两相流 

分 类 号：O357[理学—流体力学]