扑翼飞行器柔性尾翼动力学模型的建立与研究  

Establishment and Research of Flexible Tail Dynamics Model of Flapping-Wing Aircraft

作　　者：黄灿 李文彬[1] 赵卫凯 吴杰 朱攀 HUANG Can;LI Wenbin;ZHAO Weikai;WU Jie;ZHU Pan(Ministerial Key Laboratory of ZNDY, Nanjing University of Science and Technology, Nanjing 210094, China;CCDC Engineering Quality Supervision and Testing Center Co. , Ltd. , Shanghai 200232, China)

机构地区：[1]南京理工大学智能弹药技术国家重点实验室,南京210094 [2]中民防建设工程质量监督检测中心有限公司,上海200232

出　　处：《兵器装备工程学报》2020年第5期9-14,共6页Journal of Ordnance Equipment Engineering

摘　　要：建立了包含鸟类尾翼扑动和滚转的动力学模型,引入柔性变形度并给出气动特性的计算方法,分析了形状、角度和材料3个主要因素对尾翼动力学性能的影响规律,结合XFlow仿真结果进行分析。结果显示,扇形和燕尾形有更大的俯仰力矩和偏航力矩;尾翼所受力和力矩随张开角度增大而增大,随柔性变形度增大而减小;张开角度和柔性变形度的变化对燕尾形尾翼的影响大于对扇形尾翼的影响;XFlow仿真结果与模型计算结果的变化规律一致,两者的平均相对误差为17.58%。A dynamic model including bird-like tail flapping and rolling was established based on the actual bird tail.The flexible deformation degree was proposed and the calculation method of aerodynamic characteristics was given.Then the effects of three main variables were analyzed and the results of XFlow simulation were combined for comparative analysis.With the increasing the opening angle of tail plane,the force is increased and the flexible deformation degree is declined.The influences of the two variables on the dovetail tail is greater than that on the sector tail.Compared with the results of XFlow simulation,the variation rule is identical with that of the theoretical model,with an average relative error of 17.58%.

关 键 词：仿鸟扑翼飞行器 柔性变形 尾翼 俯仰力矩 偏航力矩 

分 类 号：TJ011[兵器科学与技术—兵器发射理论与技术] V211.5[航空宇航科学与技术—航空宇航推进理论与工程]