The invention relates to the technical field of aviation aircraft fuel tanks, in particular to a wing built-in aviation fuel tank pressurizing device. The device includes an aviation fuel tank, a pressurizing insertion pipe is inserted into an inner cavity at the upper end of the aviation fuel tank; a mounting bracket is vertically mounted on the outer edge of the upper end of the aviation fuel tank; symmetrical second rotating grooves are formed in the left arc side face and the right arc side face of the connecting position of an upper end boss of the aviation fuel tank and the pressurizinginsertion pipe. The device has the beneficial effects that through cooperation of the lower inserting pipe of the buffer box, on the premise of preventing oil from flowing back, buffering of air inletpressurization is achieved, and through cooperation with the throttling valve, the pressurization rate is effectively controlled; by arranging the lining pipe driven by the motor, communication between the second through hole and the third through hole is achieved, the process of needing rapid pressurization is achieved, the pressurization rate is increased, the buffer time needed by pressurization is shortened, and the airplane can run more stably.