舵面型颤振特性与转换规律特性研究  

Research on Flutter Characteristics and Conversion Law ofa Wing with Trailing Rudders

作　　者：王标[1] 柏楠[1] 赵铁铭[1] 沈恩楠 于佳鑫 WANG Biao;BAI Nan;ZHAO Tieming;SHEN Ennan;YU Jiaxin(Shenyang Aircraft Design&Research Institute,Shenyang 110035,China)

机构地区：[1]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《飞机设计》2021年第4期36-42,共7页Aircraft Design

摘　　要：操纵面颤振是制约飞机性能的关键因素,对颤振设计而言,需要从总体布局、结构刚度、惯性特性等方面入手,综合权衡各种因素。针对某机翼及舵面,建立结构动力学有限元模型,在分析机翼及舵面固有特性与不可压流假设颤振特性基础上,研究带后缘舵面驼峰型颤振与经典弯扭颤振的转换规律,包括操纵刚度、舵面刚度、舵面质量分布等关键因素,总结了设计要素对舵面型颤振特性的影响规律,并对颤振模型数值计算与风洞试验进行了对比分析,结果验证了所取颤振设计参数的有效性,可以作为机翼带舵面颤振设计的重点要素。Controlling surface flutter is a key factor restricting aircraft performance.For flutter design,it is necessary to weigh various factors such as general layout,structural stiffness and inertia characteristics.A dynamic finite element model of the wing with trailing rudders is established.The characteristics including controlling stiffness,rudders stiffness and mass distribution and flutter analysis based on the incompressible flow hypothesis is conducted to reveal conversion law between“humped”and typical flutter modes.The influence factors on the rudders flutter characteristics are summarized.The calculation results are compared with the wind tunnel test model.The flutter parameters are verified effectively for the designing of wings with rudders.

关 键 词：后缘舵面 舵面颤振 有限元模型 固有特性 风洞试验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]