发表机构
Fédération ENAC ISAE-SUPAERO ONERA, Université de Toulouse; von Karman Institute for Fluid Dynamics; European Space Agency, ESTEC（图卢兹大学; 冯·卡门流体力学研究所; 欧洲空间局）
机构由 AI 辅助整理，请以论文原文为准。AI 中文总结
本文提出高保真DNS-FSI框架，用于微重力下刚-液-柔航天器动力学模拟，通过分区耦合与能量平衡诊断验证，并评估降阶模型在非线性环境中的控制性能。
AI 中文摘要
本文提出了一种用于微重力条件下刚-液-柔航天器动力学的高保真直接数值模拟（DNS）-流固耦合（FSI）框架。液-气两相流采用DIVA中实现的可压缩两相求解器进行模拟，并针对国际空间站（ISS）上进行的FLUIDICS实验进行了验证。柔性附件采用考虑几何刚化的旋转假设模态板模型描述。流体与结构算子通过带Aitken松弛的Dirichlet-Neumann定点算法耦合，并利用闭系统机械能平衡作为后验诊断指标来评估分区离散化的能量不平衡。该耦合策略针对实验自由衰减晃荡基准进行了验证，并通过能量平衡缺陷的空间敏感性研究评估了其数值一致性。对自旋机动进行了规定运动、刚性开环和柔性开环模拟的比较，以隔离结构反馈对晃荡响应的影响。从不同仿真架构中辨识出的降阶液体模型在嵌入相同的刚-柔被控对象时表现出不同的预测能力。基于从柔性仿真中辨识的降阶模型设计的控制器在非线性CFD-FSI环境中进行了回放。该降阶模型再现了所考虑机动的主要姿态和执行器响应，但未能恢复详细的非线性晃荡载荷历史。该框架为分析耦合航天器动力学、辨识控制导向模型以及评估超出其线性设计表示的基于降阶模型的控制策略提供了高保真环境。
英文摘要
This paper presents a high-fidelity direct numerical simulation (DNS)-fluid-structure interaction (FSI) framework for rigid-liquid-flexible spacecraft dynamics under microgravity conditions. The liquid-gas flow is simulated with the incompressible two-phase solver implemented in DIVA, validated against FLUIDICS experiments conducted aboard the International Space Station (ISS). The flexible appendages are described by a rotating assumed-mode plate model that accounts for geometric stiffening. The fluid and structural operators are coupled through a Dirichlet-Neumann fixed-point algorithm with Aitken relaxation, and a closed-system mechanical energy balance is used as an a posteriori diagnostic to assess the energy imbalance of the partitioned discretisation. The coupling strategy is validated against an experimental free-decay sloshing benchmark, and its numerical consistency is assessed through spatial sensitivity studies of the energy-balance defect. Prescribed-motion, rigid open-loop, and flexible open-loop simulations of a spin-up manoeuvre are compared to isolate the effect of structural feedback on the sloshing response. Reduced liquid models identified from the different simulation architectures exhibit different predictive capabilities when embedded in the same rigid-flexible plant. A controller synthesized from the reduced model identified from the flexible simulation is replayed in the nonlinear CFD-FSI environment. The reduced model reproduces the principal attitude and actuator responses for the considered manoeuvre but does not recover the detailed nonlinear sloshing-load history. The framework provides a high-fidelity environment for analysing coupled spacecraft dynamics, identifying control-oriented models, and assessing reduced-model-based control strategies beyond their linear design representation.
CommentsThis is a preprint version of the paper
