基于黏性涡粒子和非定常面元法耦合的倾转四旋翼飞行器气动干扰研究  

Aerodynamic interference of quad tilt-rotor aircraft based on viscous vortex particle coupling with unsteady panel method

作　　者：高杰[1] 李建波[1] 彭名华[1] GAO Jie;LI Jianbo;PENG Minghua(National Key Laboratory of Rotorcraft Aeromechanics,NUAA,Nanjing 210016,China)

机构地区：[1]南京航空航天大学、直升机旋翼动力学国家级重点实验室,江苏南京210016

出　　处：《飞行力学》2023年第2期7-13,共7页Flight Dynamics

基　　金：直升机旋翼动力学国家级重点实验室基金资助。

摘　　要：为研究倾转四旋翼飞行器复杂的气动干扰问题,首先基于黏性涡粒子和非定常面元法建立了倾转四旋翼飞行器干扰流场的数值计算方法,并验证了该方法的有效性;其次,根据建立的方法对悬停和前飞状态下的气动特性和干扰情况进行了计算和分析;最后,针对干扰情况对倾转四旋翼的气动布局进行了部分优化设计。结果表明:悬停时的干扰主要来自旋翼下洗流对机翼作用产生的向下载荷,占旋翼拉力的25.3%;前飞时的干扰主要表现为旋翼尾流对机翼“增阻”作用,致使全机升阻比降低13.2%,增加前后旋翼的横向间距能使前飞时后旋翼的拉力和效率分别提升13.5%和4.2%,全机的升阻比提高3.1%;旋翼下方机翼后缘向下偏转的布局能使悬停时机翼受到的向下载荷减小40.7%。To study the aerodynamic interference of quad tilt-rotor aircraft,a numerical method for the flow field of quad tilt-rotor aircraft was established based on the viscous vortex particle and unsteady panel method,and the effectiveness of the method was verified.Secondly,aerodynamic characteristics and interference in hovering and forward flight were calculated and analyzed according to the method.Finally,the aerodynamic layout of quad tilt-rotor was optimized for interference.The results show that the main interference during hovering was the wing's downward load due to the downwash of rotor,which is accounted for 25.3%of rotor thrust.During the forward flight,the main interference is the wing's drag increased by the rotor wake,which will reduce the lift-drag ratio of vehicle by 13.2%.By increasing the horizontal distance of the front and rear rotor,the thrust and efficiency of the rear rotor are increased by 13.5%and 4.2%respectively,and the lift-drag ratio of whole vehicle is also increased by 3.1%.The downward-tilting optimization of the trailing edge under the rotor will decrease the downward loads on wing by 40.7%during hovering.

关 键 词：倾转四旋翼飞行器 气动特性 黏性涡粒子方法 非定常面元法 布局优化 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]