机动襟翼控制规律的设计及飞机动态特性研究

 飞机机动襟翼的控制规律~般是通过大量的风洞实验确定的。本文尝试用线性理论和辨识技术给出~个简单的理论设计方法,把襟翼偏角设计成迎角和马赫数的函数,所用数据是所有襟翼偏角对应的升、阻值,无需找出最小阻力包线,从而减少了计算或实验次数。文中用该方法对某型机的机动襟翼控制规律进行了设计,结果表明,该规律的襟翼偏角与实验有利值基本吻合。同时,仿真计算表明飞机的操、稳特性符合军用规范。因此这~方法对飞机设计中确定襟翼控制规律有~定的实际意义。

DESIGN FOR CONTROL LAWS OF MANEUVER FLAPS AND A STUDY OF THE DYNAMIC CHARACTERISTICS OF THE AIRPLANE

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