南京航空航天大学学报（英文版）2009，Vol.26Issue(2)：137-146,10.
航天器推进剂晃动与控制系统之间耦合效应的混合型估算方法
HYBRID APPROACH FOR ESTIMATING COUPLING EFFECT BETWEEN PROPELLANT SLOSHING DYNAMIC AND SPACECRAFT GNC
摘要
Abstract
An approach based on equivalent mechanics theory and computational fluid dynamics (CFD) technology is proposed to estimate dynamical influence of propellant sloshing on the spacecraft. A mechanical model is established by using CFD technique and packed as a "sloshing" block used in spacecraft guidance navigation and control (GNC) simulation loop. The block takes motion characteristics of the spacecraft as inputs and outputs of perturbative force and torques induced by propellant sloshing, thus it is more convenient for analyzing coupling effect between propellant sloshing dynamic and spacecraft GNC than using CFD packages. An example demonstrates the accuracy and the superiority of the approach. Then, the deducing process is applied to practical cases, and simulation results validate that the proposed approach is efficient for identifying the problems induced by sloshing and evaluating effectiveness of several typical designs of sloshing suppression.关键词
等效力学模型/计算流体力学技术/推进剂晃动Key words
equivalent mechanical model/computational fluid dynamics (CFD) technique/propellant sloshing分类
航空航天引用本文复制引用
齐乃明,董锴,李运迁,赵宝山..航天器推进剂晃动与控制系统之间耦合效应的混合型估算方法[J].南京航空航天大学学报（英文版）,2009,26(2):137-146,10.基金项目
航天科技创新基金(CASC200902)资助项目.Foundation item: Innovation Foundation of Aerospace Science and Technology(CASC200902). （CASC200902）
