Aircraft ultra-large attitude angle pitching rolling dual-mode oscillation wind tunnel test system and method

The invention relates to an aircraft ultra-large attitude angle pitching rolling dual-mode oscillation wind tunnel test system and test method, and belongs to the technical field of test aerodynamic measurement. Comprising a pitching oscillation driving device, a follow-up device, a rolling driving force measuring device and an aircraft model, and the pitching oscillation driving device and the follow-up device are arranged outside a wind tunnel and are respectively connected with the rolling driving force measuring device arranged in the wind tunnel to form a test system. The aircraft model is driven to realize any pitching amplitude oscillation motion simulation in a horizontal plane; the rolling driving force measuring device is located in the aircraft model, is an electromagnetic suspension force measuring device, suspends and drives the aircraft model to realize any rolling amplitude oscillation simulation along the axis of the aircraft model, and completes six-component dynamic aerodynamic force measure