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 11^th 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 gap

interporosity 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%.