双垂尾飞行器偏航力矩非线性变化分析  

Nonlinear Characteristic Analysis of the Yaw Moment of a Twin-tailed Configuration

作　　者：王延奎[1] 秦叶 黄茜 Wang Yankui;Qin Ye;Huang Xi(Ministry-of-Eduation Key Laboratory of Fluid Mechanics,Beihang University,Beijing 100083,China)

机构地区：[1]北京航空航天大学教育部流体力学重点实验室,北京100083

出　　处：《航空科学技术》2018年第7期44-47,共4页Aeronautical Science & Technology

基　　金：航空科学基金(2016ZA51007)~~

摘　　要：以典型双垂尾飞行器为研究对象,通过风洞试验研究了模型在不同侧滑角下的偏航力矩特性,计算分析了风速为30m/s、侧滑角为4°时模型随迎角变化的流场及偏航力矩变化特性。试验及计算结果表明模型在侧滑角1°及1°以上、迎角大于10°时偏航力矩出现非线性变化特性,在迎角为0°~25°时,垂尾和机头是全机偏航力矩的主要贡献部件,而垂尾是全机偏航力矩非线性变化的主要原因部件。The variation rule of yaw torque at different slip angles was calculated wilh the model of a double verlical tail as the research object, and the the flow field and yaw moment varication characteristics of the model with the angle of attack were analyzed when wind speed was 30m/s and the sideslip angle was 4°. The calculate results show that lhe yaw moment of the model starts to appear non-linear change law at slip angle of 1° and above, the angle of attack 10°, when the angle of attack is at 0° -25°, the vertical tail is the main contributing part of the yaw moment of the whole model, and the vertical fail is also the main reason of the nonlinear vadation of the yaw moment.

关 键 词：双垂尾布局 航向气动特性 涡干扰 侧滑角影响 迎角效应 

分 类 号：V211.411[航空宇航科学与技术—航空宇航推进理论与工程]