标题： 使用CFD仿真和强迫振荡模型计算垂直起降飞行器的纵向动态导数 显示英文标题

标题： Computing Longitudinal Dynamic Derivatives of a VTOL Aircraft Using CFD Simulations and Forced-Oscillation Model

摘要： 本研究使用先进的CFD仿真和强迫振荡测试，对飞机过渡阶段的动态空气动力学导数进行了全面评估。 两个案例被研究：一种三维战斗机（标准动态模型，SDM）和一种UT24 eVTOL模型。 通过谐波振荡技术分析从垂直悬停到前飞巡航的过渡阶段，以捕捉非定常空气动力学力和力矩。 网格敏感性研究和多区域网格划分策略确保了仿真的准确性，而ANSYS Fluent有限体积求解器和耦合压力速度算法提供了高保真结果。 动态导数来源于攻角、飞行路径和旋转运动的变化，实验和数值数据验证了该方法。 研究结果为鲁棒控制设计和稳定性分析提供了有价值的见解，支持未来在城市空中交通和航空航天工程中的进步。 总体而言，这种方法在优化关键过渡阶段的飞机性能方面表现出巨大的潜力。 这些结果为未来的创新铺平了道路 显示英文摘要

摘要： This study presents a comprehensive evaluation of dynamic aerodynamic derivatives during aircraft transition phases using advanced CFD simulations and forced oscillation testing. Two case studies are examined: a three dimensional fighter aircraft (Standard Dynamic Model, SDM) and a UT24 eVTOL model. The transition phase from vertical hover to forward cruise is analyzed with harmonic oscillation techniques to capture unsteady aerodynamic forces and moments. Grid sensitivity studies and multi zone meshing strategies ensure simulation accuracy, while ANSYS Fluent finite volume solver and coupled pressure velocity algorithms provide high fidelity results. Dynamic derivatives are derived from variations in angle of attack, flight path, and rotational movements, with experimental and numerical data validating the approach. The findings offer valuable insights for robust control design and stability analysis, supporting future advancements in urban air mobility and aerospace engineering. Overall, this approach demonstrates substantial promise for optimizing aircraft performance during critical transition phases. These results pave the way for future innovations