空气动力迟滞引起飞机横航向极限环振荡的一种近似解法

 本文给出近似解析公式,确定空气动力迟滞引起的飞机横航向极限环振荡特性。计算表明,它与文献1、2]中提出的数值迭代法求得的结果相当一致,并消除了该文中求出的滚转迟滞引起的滚转速率极限环振荡振幅不是最大幅值的缺陷。

AN APPROXIMATE SOLUTION OF AIRCRAFT LATERAL-DIRECTIONAL LIMIT CYCLE OSCILLATION INDUCED BY AERODYNAMIC HYSTERESIS

Wind tunnel tests on aircraft models often demonstrate that the variation of lateral-directional rolling and yawing moments with the yaw angle gives evidence of aerodynamic hysteresis occurred at high angle of attack. The non-linear additional increments of the moment due to aerodynamic hysteresis are linearized by the harmonic linear method. Then, based on the harmonic balance method, an approximate analytical formula is derived for determining the characteristics of aircraft lateral-directional limit cycle oscillation induced by aerodynamic hysteresis. Calculations by this method show that the results are in good agreement with data obtained by the numerical iterating method in references1]and2]. The method eliminates the shortcoming in the above references that the amplitude of roll rate limit cycle oscillation induced by roll hysteresis is not the maximum.