大攻角下有限振幅俯仰飞行的非线性动稳定性分析  

Nonlinear Dynamic Stability Analysis for the Aircraft Flying at High Angles of Attack

作　　者：陆夕云[1] 杨国伟[1] 庄礼贤[1] 李潜[2] 

机构地区：[1]中国科学技术大学 [2]北京空气动力研究所

出　　处：《空气动力学学报》1999年第2期177-182,共6页Acta Aerodynamica Sinica

摘　　要：本文介绍了一种关于大攻角飞行条件下，飞行器非线性动稳定性分析的数学方法。基于飞行器整体运动的低频特点（ｋ１），将动稳定性导数的概念推广到大攻角有限摆幅振荡飞行的稳定性分析，给出了逐次求取各阶动导数的摄动方法，导出了小参数形式的非线性动力学方程。结合常微分方程的定性理论，可以揭示大攻角飞行中的某些非线性特征，方法原则上可推广到多自由度问题。A mathematical method for the nonlinear dynamic stability analysis in the aircraft dynamics is presented in this paper. Based on the assumption of the low frequency (k1), the concept of dynamic derivatives is extended to the cases for the aircraft flying at high angles of attack.A method for predicting the dynamic derivative of various orders is given using the perturbation methods.The weak nonlinear ordinary differential equations for flight dynamics are derived,in which the unsteady aerodynamic forces are represented by the aerodynamic derivatives.In principle,this method can be employed for the dynamic stability analysis of the multi degree of freedom problems.

关 键 词：动稳定性 气动力 大攻角飞行 非线性振动 飞行器 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]