高轨大型航天器液体晃动等效建模方法研究  

Equivalent Modeling Methods for Liquid Sloshing in High-Orbit Large Spacecraft

作　　者：陈易之 于强 吕敬 李青[4] 郭建新[3] 王天舒[2] CHEN Yizhi;YU Qiang;LYU Jing;LI Qing;GUO Jianxin;WANG Tianshu(Beihang University,Beijing 100191,China;Tsinghua University,Beijing 100084,China;Beijing Institute of Control Engineering,Beijing 100094,China;Beijing Spacecraft System Design Department,Beijing 100094,China)

机构地区：[1]北京航空航天大学,北京100191 [2]清华大学,北京100084 [3]北京控制工程研究所,北京100094 [4]北京空间飞行器总体设计部,北京100094

出　　处：《空间控制技术与应用》2024年第5期77-83,共7页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(61333008)。

摘　　要：高轨航天器一般都带有大量液体燃料,在进行轨道机动时液体运动会对航天器的姿态产生不可忽略的扰动,建立简洁而精确的液体晃动动力学模型具有重要的工程应用价值.介绍在带有大型燃料贮箱的高轨航天器研制过程中液体晃动等效动力学建模若干问题的研究进展,包括应用于位保模式的任意形状三维贮箱液体晃动等效建模方法、姿态大角度机动下时变参数等效力学建模方法,给出基于静矩和惯量连续的变参数等效建模方法,并通过数值仿真验证了所提出方法的准确性.High-orbit spacecraft typically carry a large amount of liquid fuel,and during orbital maneuvers,the motion of the liquid can cause significant disturbances to the spacecraft's attitude.Developing a simple yet accurate dynamic model for liquid sloshing has important engineering value.This paper introduces several research advances related to equivalent dynamic modeling of liquid sloshing during the development of high-orbit spacecraft with large fuel tanks.These include the equivalent modeling methods for arbitrary-shaped 3D tanks applied to attitude maintenance modes,and time-varying parameter equivalent mechanical modeling methods for large-angle attitude maneuvers.The study presents a variable-parameter equivalent modeling method based on the continuity of static moments and inertia,and numerical simulations verify the accuracy of the proposed methods.

关 键 词：高轨航天器 液体晃动 等效建模 

分 类 号：V448[航空宇航科学与技术—飞行器设计]