舰载运输类飞机布局紧凑，副翼兼备增加升力（襟副翼）、提供滚转力矩等作用。根据CCAR-25增升装置和滚转情况的设计准则，并考虑机舰适配性要求，研究了某舰载运输类螺旋桨飞机的襟副翼和副翼飞行载荷设计方法。通过机动仿真获得襟副翼、副翼典型载荷情况，通过面元法获得不同动力影响下的气动特性数据和压力分布数据，结合理论方法与工程需要，计算、筛选出襟副翼和副翼的载荷边界作为其设计载荷。研究结果表明，算例飞机的襟副翼和副翼飞行载荷受滑流影响较小；襟副翼在各个设计空速的迎面突风情况下获得设计载荷；副翼在设计俯冲速度的最大可用偏度情况下获得设计载荷。
The carrier-based transport category aircraft usually has a compact layout, where the ailerons function both as the high lift device, i.e., the flaperon, and the supplier of rolling moment. According to the criteria for high lift device and rolling conditions in CCAR-25 and the requirements of carrier suitability, the design of the flight loads on the flaperons and ailerons of a carrier-based transport category propeller aircraft is herein studied. The typical loading cases of the flaperon and aileron are obtained from the maneuver simulation. The aerodynamic coefficients and pressure distribution data under a series of propeller slipstream strengths are obtained by the panel method. The design loads of the flaperon and aileron are calculated and selected from the load boundary in combination with the mathematical methods and engineering needs. The results show that the propeller slipstream has little influence on the flight loads of the flaperon and aileron of this aircraft; the design loads of the flaperon are obtained from head-on gust at each designed airspeed, and the design loads of the aileron are obtained from the maximum available deflection at the designed dive speed.
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