The DLR Future Fighter Demonstrator (FFD) is a highly agile, two-seated aircraft with twin-engines equipped, a reheat and a design flight speed extending into the supersonic regime (up to $Ma=2.0$). Based on a given conceptual design, the presented work focuses on the aeroelastic modeling, including structures, masses and aerodynamics. Using the models, a comprehensive loads analysis with 688 maneuver load cases, covering the whole flight envelope, is performed. Comparing the results obtained from aerodynamic panel methods (VLM and ZONA51) with higher fidelity results obtained from CFD, the necessity of CFD based maneuver loads analysis in preliminary design of such fighter configuration is shown, as it leads to physically different as well as higher loads. The rigorous application of CFD is a heavy burden during the preliminary design, but this work demonstrates that it is doable as of today. Finally, the model is subject to structural optimization, demonstrating that the differences in loads result in a heavier primary structural net mass with $\approx 3.3t$ for the approach based on aerodynamic panel methods and $\approx 4.1t$ for the CFD based approach. Because all remaining models are unchanged, this difference in mass can be clearly attributed to the physical differences in the flow solutions obtained from the panel methods and CFD.

DLR 未来战斗机演示器 (FFD) 是一种高度灵活的双座飞机，配备双引擎，再加热和设计飞行速度延伸到超音速状态（高达$米A=2.0$). 基于给定的概念设计，所提出的工作重点是气动弹性建模，包括结构、质量和空气动力学。使用这些模型，对涵盖整个飞行包线的 688 个机动载荷案例进行了全面的载荷分析。将空气动力学面板方法（VLM 和 ZONA51）获得的结果与 CFD 获得的更高保真度结果进行比较，表明在这种战斗机配置的初步设计中基于 CFD 的机动载荷分析的必要性，因为它导致物理上的不同以及更高的载荷. CFD 的严格应用在初步设计期间是一个沉重的负担，但这项工作证明它在今天是可行的。最后，对模型进行结构优化，$\approx 3.3吨$对于基于空气动力学面板方法的方法和$\approx 4.1吨$对于基于 CFD 的方法。因为所有剩余的模型都没有改变，所以这种质量差异可以清楚地归因于从面板方法和 CFD 获得的流动解决方案的物理差异。