悬停状态共轴刚性旋翼机身气动干扰特性  

Aerodynamic interaction characteristics of coaxial rigid rotor-fuselage in hover condition

作　　者：孙朋朋 刘平安[1] 樊枫[1] 曾伟[1] SUN Pengpeng;LIU Pingan;FAN Feng;ZENG Wei(Science and Technology on Rotorcraft Aeromechanics Laboratory,Jingdezhen 333000,China)

机构地区：[1]中国直升机设计研究所,景德镇333000

出　　处：《航空学报》2024年第9期201-210,共10页Acta Aeronautica et Astronautica Sinica

基　　金：直升机旋翼动力学国家级重点实验室基金(61422200102)。

摘　　要：对共轴刚性旋翼/机身气动干扰开展试验和计算研究,分析了悬停状态下机身气动干扰对双旋翼气动特性以及机身表面压力分布的影响。结果表明,机身气动干扰使上、下旋翼桨叶尖部高升力区域范围增大,同拉力系数下的旋翼功率系数降低,旋翼最大悬停效率(FM)增大约4.6%;受旋翼下洗流的影响,机身会产生垂直向下载荷,大小约为旋翼拉力的7%,扣除机身垂向力旋翼最大悬停效率相比孤立旋翼状态降低约6%;在旋翼气动干扰下,机身产生抬头力矩,大小与旋翼拉力系数成正比;机身表面压力呈4倍旋转频率的非定常变化。Experimental and computation studies were conducted on the aerodynamic interaction between coaxial rigid rotor-fuselage in hover.The influence of fuselage aerodynamic interference in hover on the aerodynamic charac-teristics of coaxial rigid rotor and the pressure distribution on the fuselage surface was analyzed.It is found that the range of high lift areas at the tip of the upper and lower rotor blades is increased,and the power coefficient of the ro-tors is reduced at the same tension coefficient with the aerodynamic interaction of the fuselage.The rotor maximum Figure of Merit(FM)increases by approximately 4.6%.The fuselage generates vertical down-load,which is about 7% of the rotor pull force,with the influence of rotor downwash flow.Excluding vertical down-load on the fuselage,the maximum FM of the rotor is reduced by about 6% compared to isolated rotors.Under the aerodynamic interaction of rotor,the fuselage generates an upward force moment,which is proportional to the rotor tension coefficient.The sur-face pressure of the fuselage exhibits an unsteady variation of 4 times the rotational frequency.

关 键 词：共轴刚性旋翼 气动干扰 机身 风洞试验 悬停 

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]