高超声速风洞铰链力矩试验技术研究进展

针对高超声速风洞铰链力矩试验比低速和高速风洞铰链力矩试验模型尺寸更小、温度效应和缝隙窜流影响更大，试验难度更大的特点，“十一五”以来，在中国空气动力研究与发展中心超高速空气动力研究所的Ф1 m高超声速风洞上开展了高超声速铰链力矩试验技术研究工作。先后发展了基于纵轴式、横轴式以及其他布局方式的天平及其试验装置设计技术，探索了适用于高超声速风洞试验条件的减小天平温度效应的措施、舵偏角变换方式和天平校准方法，并开展了多轮验证试验。试验结果表明:发展的铰链力矩试验方法、试验装置、天平结构、舵偏角变换方式和天平校准方法等能够满足不同高超声速飞行器控制舵面气动力测量的需求；采取的天平两端加装隔热套和电桥桥路补偿等措施能够有效减小天平温度效应和缝隙窜流的影响。目前，本项试验技术已成功应用于Ф1 m高超声速风洞马赫数4～8（来流总温273～740 K）的舵面气动特性测量，铰链力矩重复性精度优于1.50%。

Research progress of hinge moment test technique in hypersonic wind tunnel

Compared with hinge moment tests in the low speed and high speed wind tunnel, the hypersonic wind tunnel hinge moment test has smaller model size, larger effect of temperature and gap interporosity flow, and larger test difficulty. The research on the hypersonic hinge moment test technique is to seek the method to solve these difficulties. Since the 11th Five-Year Plan, relevant work have been done by Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center in Ф1 m Hypersonic Wind Tunnel. The design technology of the balance and test equipment based on the vertical axis, horizontal axis and other layout modes has been developed successively. The measures to reduce the temperature effect, the rudder deflection transformation method and the balance calibration method suitable for hypersonic wind tunnel test conditions were explored, and several rounds of verification tests were carried out. Experimental results show that the developed test method, test device, balance structure, rudder deflection transformation method, and balance calibration method can meet the requirements of aerodynamics measurement of the control rudder of different hypersonic flight vehicles. The temperature effect of the balance and the effect of the gapinterporosity flow can be reduced effectively by installing the heat insulation sleeve at both ends of the balance and using the electric bridge compensation. The test technology has been successfully applied to the measurement of aerodynamic characteristics of the rudder surface in Ф1 m Hypersonic Wind Tunnel with Mach number 4–8 and total temperature of 273–740 K, and the repeatability accuracy of the hinge moment is better than 1.50%.