Φ2米旋翼模型试验台悬停和前飞试验  

Hover and Forward Flight Test of the Φ2m Rotor Model Test Stand

作　　者：黄明其[1] 兰波[1] 王天虹[1] 

机构地区：[1]中国空气动力研究与发展中心低速所,绵阳621000

出　　处：《直升机技术》2008年第3期121-124,共4页Helicopter Technique

摘　　要：为满足直升机选型试验及旋翼气动特性机理性研究的需要,中国气动研究与发展中心低速所研制了Ф2m旋翼模型试验台。试验台研制经历方案论证、分系统设计加工与研制、分系统安装调试、试验台总装及动力/传动系统联调等阶段,完成了地面调试和悬停试验,并在Φ3.2m风洞完成了配平前飞试验,已形成2m直径量级旋翼模型桨尖马赫数相似的悬停试验和前飞试验能力,提高了直升机风洞试验和研究能力。To meet the requirements of helicopter type-selection and dynamic characteristic principal research,CARDC Low Speed Institute developed Φ2m rotor model test stand.The developing of test stand experienced the four process of scheme argumentation,sub-system developing,sub-system debugging,test stand installation and dynamic system/transmission combined debugging.The ground debugging and hover test was conducted,and the forward flight was conducted in Φ3.2m wind tunnel.So the hover test and forward flight test ability of Φ2m rotor model blade tip mach number similitude was formed,and the helicopter wind tunnel test and research ability was enhanced.

关 键 词：旋翼模型 试验台 悬停试验 风洞试验 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]