振型节线角度对舵面颤振稳定性的影响  

Effect of Oblique Angle for Nodal Lines on Flutter Stability of an All-Moving Fin

作　　者：史晓鸣 侯凯宇 沈奕哲 夏鹏 李海东 SHI Xiaoming;HOU Kaiyu;SHEN Yizhe;XIA Peng;LI Haidong(Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China;Shanghai Academy of Spaceflight Technology,Shanghai 201109,China)

机构地区：[1]上海机电工程研究所,上海201109 [2]上海航天技术研究院,上海201109

出　　处：《力学季刊》2023年第2期418-426,共9页Chinese Quarterly of Mechanics

基　　金：国家重点研发计划(2022YFB3705304)。

摘　　要：针对舵机支撑刚度支持下的舵面结构,建立了广义气动力与舵面前两阶局部刚化模态振型节线角度关系的表达式,分析广义气动力随振型节线角度的变化规律,根据Routh-Hurwitz稳定性判据研究振型节线角度对颤振临界动压的影响.研究结果表明:舵面前两阶局部刚化模态振型节线处于相对“横平竖直”的状态时,前两阶模态经由广义非定常气动载荷引起的耦合较弱,舵面的颤振临界动压较高.The relationship between the generalized aerodynamic force and the oblique angle of the first two local stiffening modal nodal lines was theoretically derived to analyze the rule of the generalized aerodynamic force changing with an all-moving fin supported by control actuator.Effect of the oblique angle of nodal lines on the flutter stability was studied based on the Routh-Hurwitz stability criterion.The results show that the weaker coupling between the first two modes via generalized unsteady aerodynamic loads results in a high critical dynamic pressure,when the nodal lines of local stiffening mode shape are horizontally orverticallyoriented.

关 键 词：颤振 舵面 振型 节线 稳定性 

分 类 号：O323[理学—一般力学与力学基础]