【Task】
A aircraft (50), a first wing located on opposite sides of the long axis (68) and a second wing (70), first and front opening is attached to the upper surface of the first wing (68) first control surface (52) and a second control surface which is front opening that is attached to the upper surface of the second wing (70) and (54) comprise, each first hinge (56) and the second hinge (58 ) is inclined with respect to the direction perpendicular to the long axis of the aircraft (θ1, θ2). How to control the yaw of the aircraft are also provided. Method, in the upper surface of the first wing of the aircraft, and the process of deploying the first of the inclined spoiler was front opening, in the upper surface of the second wing of the aircraft, a second, inclined spoiler was front opening a step of deploying and alternately moving the first and second spoiler, a step of generating a yaw moment. Without causing any downward force, generating a yaw moment, the tip is applied to swept wing behind the center of gravity of the aircraft. An advantage of the present invention, to counter the downward force produced by the upper spoiler, one conventional spoiler spoilers must (front portion is hingedly connected, the rear is open) to the bottom side of the ratio to to, is that the radar cross section is small.