Fluid–structure interaction (FSI) analysis is often highly computationally expensive, making it infeasible to conduct iterative aeroelastic design studies or rigorous optimizations. This work develops a new method for aeroelastic analysis that can be more efficient in the determination of final structure/fluid equilibrium configurations, especially during design studies where attributes of a structure may be altered but those of the flow are unchanged. In this new scheme, referred to as the uncoupled static aeroelastic analysis method, the usual approach of performing fluid and structure analysis that increments in time in a coupled manner is replaced by many fully decoupled, and thus highly parallelizable, structural and fluid analyses. Surrogate modeling of results enables analytical determination of interpolation intersections between physical solution fields, such intersections being proposed as the solution to coupled FSI analysis. Since the fluid and structure result sets are calculated and stored separately, fluid results can be re-used without additional analysis when the structure considered is modified (e.g., as during a design study), enabling new solutions to be quickly obtained while avoiding the more expensive fluid evaluations. This new method is demonstrated herein on three examples: (1) a rigid baffle, (2) a cantilevered deformable baffle, and (3) an aeroelastic wing. For each, the solution found via the uncoupled method is shown to closely approximate the FSI solution. Parallelization of the evaluations required to generate data for the uncoupled method enables solutions to be obtained in significantly less time as compared to the coupled scheme.

流固耦合（FSI）分析通常在计算上非常昂贵，因此无法进行迭代的气动弹性设计研究或严格的优化。这项工作开发了一种用于空气弹性分析的新方法，该方法可以更有效地确定最终结构/流体平衡构型，尤其是在设计研究中，结构的属性可能会发生变化，但流量的属性不变。在这种称为非耦合静态气动弹性分析方法的新方案中，以耦合方式随时间递增的执行流体和结构分析的常用方法被许多完全解耦的，因此高度可并行化的结构和流体分析所代替。结果的替代建模能够分析确定物理解场之间的插值交点，这种交点被提议作为耦合FSI分析的解决方案。由于流体和结构结果集是分别计算和存储的，因此在修改所考虑的结构时（例如，如在设计研究期间），流体结果可以重复使用而无需进行其他分析，从而可以快速获得新的解决方案，同时避免更多昂贵的流体评估。本文在以下三个示例中演示了此新方法：（1）刚性挡板，（2）悬臂可变形挡板，以及（3）气动弹性机翼。对于每个，通过解耦方法找到的解决方案都显示为非常接近FSI解决方案。