A New Airframe/Propulsion-Integrated Aerodynamic Testing Technology in Hypersonic Wind Tunnel

Abstract

This article presents a new type of multicomponent force measurement system to measure lift force, drag force, and pitching moment in hypersonic wind tunnel, which called the suspension force-measuring system (SFMS). The SFMS does not occupy the installation space of the scramjet engine and other key functional components in the air-breathing hypersonic vehicle model. It solves the problem that the conventional aerodynamic force measurement technology occupies too much internal space of the hypersonic vehicle test model and dramatically reduces the design difficulty of scramjet propulsion system in the test model. The SFMS adopts the spatial multi-point distribution support mode for the test model. Therefore, it has an excellent stiffness characteristic, meeting the requirement of support rigidity of wind tunnel force measurements test for large-scale and heavy load test model. Then the designed SFMS is constructed and calibrated. The static calibration results show that each test channel of the SFMS has a good sensitivity of 0.2502 mV/N for drag force test channel, 0.1557 mV/N for lift force test channel, 0.2484 mV/Nm for pitching moment test channel, and the max interference error among the SFMS test channels is less than 2.3&#x0025;. A series of aerodynamic force experiments have been carried out in the <inline-formula> <tex-math notation="LaTeX">$\emptyset 600~mm$ </tex-math></inline-formula> impulse combustion wind tunnel, and the output data of each test channel well reflected the change process of the total pressure in the test section of wind tunnel. Hence, the proposed device can meet the force test requirements of the hypersonic wind tunnel test.