关键词: 机动襟翼, 操纵性, 稳定性, 升阻比

Abstract: The flap deflection schedule is mainly determined through extensive wind-tunnel tests.In this paper, a simple analytical method based on linear theory and using identification technique is developed to determine the optimum flap deflection schedule for both leading-and trailing-edge flaps. The flap deflection schedule is a function of Mach number and angle of attack. The data used are the lift and drag for various flap deflection and the minimum drag envelop is no needed.So the quantum of calculalion and wind-tunnel tests is reduced. As an example this method has been used to determine the maneuver flap deflection schedule of a fighter. The results show that both leading-and-trailing-edge flap deflection angles in this schedule approximately agree with the optimum value determined through wind-tunnel tests. In this paper the simulating results indicate that the stability and control of the fighter agree with military specification when this schedule is used. Therefore , this method is useful in determing the maneuver flaps deflection schedule

Key words: maneuver flap, control, stability, lift-drag ratio