扭曲尾翼飞行器滚转特性  

Rolling characteristics of vehicle with twist fin

作　　者：赵博博[1,2] 刘荣忠[1] 郭锐[1] 张俊[1] 刘高[1] 陈亮[1] 

机构地区：[1]南京理工大学机械工程学院 [2]中国人民解放军73917部队

出　　处：《航空动力学报》2015年第1期142-148,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(11372136);江苏省研究生培养创新计划(CXZZ12-0218)

摘　　要：为满足飞行器速度与转速匹配的要求,提出一种对斜置平板尾翼改进得到的扭曲尾翼.根据扭曲尾翼为飞行器提供滚转力矩的特性,在斜置平板尾翼模型的基础上,引入扭曲率与平均攻角来表示扭曲尾翼的几何特征,基于修正型的叶素理论建立四自由度刚体方程描述飞行器运动规律,并与数值仿真方法求解的平衡转速进行对比.计算结果表明:增大扭曲尾翼平均攻角、增加扭曲尾翼的扭曲率、减小翼展长度均能提高飞行器的转速,增加扭曲尾翼的根梢比对飞行器的平衡转速提升不大;在扭曲尾翼平均攻角不变的条件下,飞行器的平衡转速与扭曲率成线性关系.A twist fin improved from oblique plate tail was proposed to meet the requirements of vehicle speed and rotating speed matching.According to the characteristics of twist fin providing rolling moment for vehicle,the twist rate and average attack angle were introduced to represent geometric features of twist fin based on the model of oblique plate tail.Based on correction-type blade element theory,four degrees of freedom rigid body equations were established to describe the motion law of aircraft,and the results were compared with the balancing rotating speed obtained by numerical simulation method.The results show that increasing the average attack angle and the twist rate,and reducing the span length of twist fin can improve the vehicle rotating speed,while increasing the root shoot ratio of twist fin has little effect on improving the vehicle balancing rotating speed.When the average attack angle of twist fin stays unchanged,the vehicle balancing rotating speed and twist rate show a linear relationship.

关 键 词：扭曲尾翼 扭曲率 飞行动力学方程 平衡转速 滚转特性 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]