BALANCING AN AIRCRAFT WITH SYMMETRICALLY DEFLECTED SPLIT ELEVATOR AND RUDDER DURING SHORT LANDING RUN
This article investigates methods for balancing aircraft during short straight line landing run realized by employing split rudder and elevator as air brakes after touchdown. For standard atmospheric and runway conditions, directional and longitudinal balance equations for aircraft of conventional configuration such as Il 86 are presented. Methods depend on operational and mechanical approaches, where the first requires manual or automatic trim of shortly peaking small pitching, yawing, and rolling moments using dynamic forces while the second suggest some re design of elevator and rudder control channels to limit deflection angles. The paper describes in detail each method disadvantages and suggests the adoption of automatic operational approach due to less required system modifications and piloting skills.
Aviation