Abstract: 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.

Key words: carrier-based transport category aircraft, aileron, flaperon, flight load, carrier suitability, maneuver simulation, slipstream, maximum available deflection