HYBRID APPROACH FOR ESTIMATING COUPLING EFFECT BETWEEN PROPELLANT SLOSHING DYNAMIC AND SPACECRAFT GNC

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(英文)

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 estab- lished 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 pertur- bative 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.

基于等效力学模型理论与计算流体力学技术,提出了一种用于估算航天器中推进剂晃动的力学影响的方法。以计算流体力学技术为依托,建立了晃动的等效力学模型并将其整合为晃动模块,以便在航天器导航控制回路的仿真分析中应用。该模块体现了航天器运动特征参数与推进剂晃动动力响应之间的映射关系,使其在用于分析晃动与控制系统之间的耦合效应时,比直接应用计算流体力学分析软件更为方便。该方法的正确性与优势通过检验算例得到了验证。通过在实例中应用,证明了该方法可方便地用于确定晃动的影响和检验数种防晃设计的有效性。