基于非线性气动力的横侧向静气动弹性分析  

AIRCRAFT LATITUDINAL STATIC AEROELASTIC RESPONSE ANALYSIS USING NONLINEAR AERODYNAMIC DATA

作　　者：严德[1] 杨超[1] 万志强[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《工程力学》2008年第9期224-228,240,共6页Engineering Mechanics

基　　金：国家自然科学基金项目(10502003;10432040);新世纪优秀人才支持计划项目(NCET-04-0170)

摘　　要：应用非线性气动力,分析了某飞机横侧向静气动弹性特性随迎角、法向过载的变化,并与基于线性气动力数据的结果进行了对比。线性气动力数据指气动力随迎角、侧滑角以及操纵面偏度呈线性变化,而非线性气动力数据呈非线性变化。通过对比可以得出:1)基于线性气动力数据时,迎角对副翼操纵导数没有影响;基于非线性气动力数据时,随着迎角的增大,副翼的刚性和弹性操纵导数均减小,且均呈现出非线性变化的趋势;2)无论是线性气动力,还是非线性气动力,机翼和垂尾载荷的展向分布以及翼根载荷随法向过载的变化趋势相同,仅存在数值上的差别。The latitudinal static aeroelastic characteristics of an aircraft varying with angle of attack and vertical n-factors are analyzed based on nonlinear aerodynamic data, and compared with those based on linear aerodynamic data. Linear aerodynamic data means the aerodynamic forces linearly vary as the angle of attack, side slip angle and the deflective of control surfaces, nonlinear aerodynamic data vary nonlinearly as those angles. After the comparison, it can be concluded that： 1） the rigid and control derivatives of aileron are not influenced by angle of attack based on linear aerodynamic data, but both reduce with the increase of angle of attack based on nonlinear aerodynamic data; 2） whether based on linear aerodynamic data or on nonlinear aerodynamic data, the loads along the span of wing and vertical tail as well as the root loads of them vary in the same trend, just have the difference on numerical values.

关 键 词：静气动弹性 横侧向 非线性气动力 飞行载荷 操纵导数 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]