双层平尾对旋翼/平尾干扰的抑制机理研究  

Analysis on the Suppression Mechanism of Biplane Tailplane toRotor/ Empennage Aerodynamic Interaction

作　　者：孙会迅 孙朋朋 林永峰[1] 曾伟[1] SUN Huixun;SUN Pengpeng;LIN Yongfeng;ZENG Wei(Science and Technology on Rotorcraft Aeromechanics Laboratory,China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所直升机旋翼动力学重点实验室,江西景德镇333001

出　　处：《直升机技术》2021年第4期1-6,12,共7页Helicopter Technique

基　　金：国防基础科研计划(JCKY2019205D002)资助。

摘　　要：为研究双层平尾对旋翼/平尾干扰的抑制机理,采用基于动量源模型的CFD方法建立了旋翼/平尾干扰计算模型,获得了不同前进比下的不同平尾构型的旋翼/平尾气动干扰计算结果,分析了旋翼干扰状态下的不同构型平尾的载荷和流场特点。结果表明:平尾干扰载荷在前进比0.05时最大,相比单层平尾,双层平尾的干扰载荷下降约43%;双层平尾的上下双层设计降低了单层平尾面积,减小了由于旋翼尾迹撞击在上层平尾上而产生的干扰载荷;由于上层平尾的遮挡作用,减弱了旋翼尾迹对下层平尾的干扰作用。In order to study the suppression mechanism of biplane tailplane to rotor/empennage interference,a numerical simulation method based on a momentum-source method was used to establish a computational model of rotor/empennage interference.The calculation results of different configurations of tailplanes under different advance ratios was obtained.The interference airloads of different configurations of tailplanes and flow characteristics were analyzed.The results show that,compared with the single tailplane,the interference load of the biplane tailplane decreased by about 43%when the advance ratio was 0.05.The upper and lower tailplane design reduced the area of the single-layer tailplane,thus reducing the interference load caused by the impact of the rotor wake on the upper tailplane.Because of the blocking effect of the upper tailplane,the interference effect of the rotor wake on the lower tailplane was weakened.

关 键 词：双层平尾 气动干扰 动量源方法 数值模拟 

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]