Abstract: To effectively and economically investigate the performance of supersonic combustors,a new kind of direct-connect impulse combustion wind tunnel was designed and constructed.It provides a high-enthalpy flow by combusting oxygen/nitrogen and hydrogen/nitrogen provided by a Ludwieg tube and a fuel-providing device,respectively.The fuel-providing device was elaborately designed to eliminate insecurity result from residual hydrogen after a run,and maintain nearly a constant pressure in a test.Specially-designed pneumatic high-speed valves were used to control the rapid synchronized-injection of oxygen/nitrogen and hydrogen/nitrogen into a combustion heater.The operation results show that the combustion heater can provide a wide operation range with a total temperature of 1 100 to 2 200 K,a total pressure of 1.0 to 4.0 MPa and a duration of 100 to 150 ms.