Accurately evaluating the aerodynamic performance of a battle-structure-damaged aircraft is essential to enable the pilot to optimize the flight control strategy. Based on CFD and rigid dynamic mesh techniques, a numerical method is developed to calculate the longitudinal and longitudinal-lateral coupling forces and moments with small amplitude sinusoidal pitch oscillation, and the corresponding dynamic derivatives of two fragment-structure-damaged and two continuous-rod-damaged models modified from the SACCON UAV. The results indicate that, at the reference point set in this paper, additional positive damping is generated in fragment-damaged configurations; thus, the absolute values of the negative pitch dynamic derivative increase. The missing wingtip induces negative pitch damping on the aircraft and decreases the value of the pitch dynamic derivative. The missing middle wing causes a noticeable increase in the absolute value of the pitch dynamic derivative; the missing parts on the right wing cause the aircraft to roll to the right side in the dynamic process, and the pitch-roll coupling cross dynamic derivatives are positive. Moreover, the values of these derivatives increase as the damaged area on the right wing increases, and an optimal case with the smallest cross dynamic derivative can be found to help improve the survivability of damaged aircraft.

准确评估受战斗结构损坏的飞机的空气动力学性能对于使飞行员能够优化飞行控制策略至关重要。基于CFD和刚性动态网格技术，开发了一种数值方法来计算小振幅正弦节距振动的纵向和纵向-横向耦合力和矩，以及两个破损结构和两个连续杆的相应动力导数。从SACCON无人机改装的损坏模型。结果表明，在本文设定的参考点处，在片段损坏的配置中会产生附加的正阻尼。因此，负螺距动态导数的绝对值增加。缺少的翼尖会在飞机上引起负的俯仰阻尼，并降低俯仰动态导数的值。缺少的中翼导致俯仰动态导数的绝对值显着增加；右机翼上的缺失部分会导致飞机在动态过程中向右侧滚动，并且俯仰-滚动耦合的横向动态导数是正的。此外，这些导数的值随着右机翼受损面积的增加而增加，并且可以找到具有最小横向动态导数的最佳情况，以帮助提高受损飞机的生存能力。螺距-辊耦合的交叉动态导数为正。此外，这些导数的值随着右机翼受损面积的增加而增加，并且可以找到具有最小横向动态导数的最佳情况，以帮助提高受损飞机的生存能力。螺距-辊耦合的交叉动态导数为正。此外，这些导数的值随着右机翼受损面积的增加而增加，并且可以找到具有最小横向动态导数的最佳情况，以帮助提高受损飞机的生存能力。