分离式共轴刚性旋翼风洞试验技术研究

为在■3.2 m风洞开展高速直升机共轴刚性旋翼风洞试验,中国空气动力研究与发展中心(China Aerodynamic Research and Development Center,CARDC)开展了分离式共轴刚性旋翼风洞试验关键技术研究。解决了双旋翼共轴反向驱动、双旋翼联动和差动变距操纵、旋翼气动力分离测量、旋翼间距调整等关键技术问题,研制了■2 m直径共轴刚性旋翼试验台和旋翼天平、旋翼操纵系统,实现了旋翼共轴等速反向旋转、双旋翼联动和差动变距操纵、旋翼升力偏置调整、旋翼气动力孤立测量、旋翼间距调整等功能。通过开展风洞试验,验证了该试验技术,表明试验技术具有技术成熟度高、数据重复性精度高、可调节参数多的优点。

Separating Test Technology of Coaxial Rigid Rotor Wind Tunnel

In order to carry out the wind tunnel test of high speed helicopter coaxial rigid rotor in 3.2 m wind tunnel, CARDC conducted a research on the key technology of separating coaxial rigid rotor wind tunnel. The key technical problems were analyzed, including coaxial rotor transmission, coaxial rotor union, differential pitch control, rotor aerodynamic performance separation measurement and rotor spacing adjustment. ?2 m diameter rotor model wind tunnel test rig, the rotor balance and rotor control system were developed. The rotor coaxial reverse rotation, coaxial rotor union, differential pitch control and rotor lift offset adjustment rotor, rotor aerodynamic performance isolated measurement, rotor spacing adjustment, and other functions were realized. The wind tunnel test verified that the test technology has the advantages of high technology maturity, high accuracy of data repeatability and multiple adjustable parameters.