随着火箭运载能力、卫星工作寿命和深空探测器任务复杂度的不断提高，液体推进剂占航天器总质量的比重也不断增加．液体推进剂的晃动影响着航天器的运动稳定性和姿轨控系统的可靠性，是航天器动力学中一个备受关注的问题．充液航天器中晃动的液体是一个分布参数系统，理论上是无穷维的，而工程上希望建立的数学模型是简单、低维的，因此对液体晃动等效力学模型的研究经久不衰．另外，液体推进剂对航天器的结构动特性有着重要的影响，在建立充液航天器的结构动力学模型时需要考虑液体推进剂与贮箱等结构的耦合效应．本文首先结合液体晃动动力学理论和航天工程实际，从理论研究、数值研究和实验研究等三个方面综述了国内外在充液航天器液体晃动动力学领域的研究现状，并以此为基础介绍了航天工程中液体晃动等效力学模型的应用进展情况；然后，以液体运载火箭为例概述了国内外在充液航天器液固耦合建模方面的成果，介绍了求解液固耦合问题的数值方法和应用软件；最后，根据航天器工程的发展需求，对充液航天器液体晃动和液固耦合动力学的进一步研究方向提出了一些建议．%As the capacity of launch vehicles, the lifespan of satellites and the complexity of deep space missions increase, the mass proportions of liquid propellant in spacecrafts are enhanced accordingly. Sloshing of liquid propellant in spacecrafts might affect the motion stability and the attitude and orbit control system, which is of particular concern in spacecraft dynamics. The sloshing liquid in a liquid-filled spacecraft is a distributed parameter system which is theoretically infinite dimensional, however, a simplified and reduced model is preferred in engineering. Therefore, equivalent mechanical models for liquid sloshing are continually studied. Moreover, the fluid-structure interaction between liquid propellant and tanks has important effects on the structural dynamics of spaeecrafts, which is also of concern in liquid-filled spacecraft dynamics. First in this paper, the liquid sloshing studies are respectively reviewed regarding theoretical researches, numerical studies, experimental investigations and equivalent mechanical models. Then the numerical methods and application programs in fluid-structural interaction modeling are summarized. Finally, further research directions are suggested based on the development needs of spacecraft engineering.
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