A New Design of a Support Force Measuring System For Hypersonic Vehicle Aerodynamic Measurement

Abstract In order to simulate the flight state of the aerocraft better, the aerodynamic parameters are obtained by integrating the airframe and propulsion system in a highly integrated configuration and ignition of the engine during the wind tunnel test. At present, the commonly used internal balance scheme forms a system composed of the model, internal balance and the support. However, most hypersonic vehicle models are flat or slender, which makes it difficult to provide installation space for internal balance, improves the difficulty of model design. This note proposes a support force measuring system. By integrating the balance into the structure of the support, it no longer occupies functional space in the cavity of the model, and its special structure can ensure that the additional torque generated by thrust/drag cannot act on the torque measuring element. This study provides a new way of thinking for the integrated model test with propulsion system.