The invention discloses a wing tilting rotating control mechanism and an aircraft. The wing tilting rotating control mechanism includes rotating shafts, rotating shaft brackets and limiting members. The rotating shafts are used for being fixedly connected with wings and driving the wings to rotate. The rotating shaft brackets are used for being fixedly disposed on the aircraft and being rotatablyconnected with the rotating shafts, and limiting portions are arranged at the positions at which the rotating shaft brackets are rotatably connected with the rotating shafts. The limiting members arefixedly connected with the rotating shafts, and the limiting members are provided with first limiting surfaces and second limiting surfaces which correspond to the limiting portions. The first limiting surfaces or the second limiting surfaces can separately abut against the limiting portions following the rotation of the rotating shafts, and rotating force is continuously applied on the rotating shafts to enable the first limiting surfaces or the second limiting surfaces to continuously abut against the limiting portions. The wing tilting rotating control mechanism has the technical effect that the positions of the wings relative to a fuselage can be stably limited, no limiting phantom is achieved, and the flight quality of the aircraft is ensured.