Abstract: For the fundamental studiesin hypersonic aerodynamics, the first aerospace modeling flight named MF-1 was carried out in China.The tested model is a cone-cylinder-flare configuration in the payload modules of this flight, and the main objective of this test is the investigation of the boundary layer transitionon the cone surface and the shock wave/boundary layer interaction at the compression corner.According to the measurement requirements of the boundary layer transition study, the common thin-skin calorimeter design in wind tunnel tests was employed and modified.This modification led to a novel variable-thickness thin-skin temperature measurement structure.The variable-thickness thin-skin structure depresses effectively lateral heat conduction losses due to the temperature difference between thin-skin and surrounding shell during long-time flight, therefore an effective long time measurement was obtained.Heat flux data can be obtained using an one dimensional heat flux identification method based on variable-thickness thin-skin flight data.This method improves the response time in comparison with the thin-skin calorimetric method.A pressure measurement scheme based on pneumatic tubes and an electric pressure scanner was designed for the shock wave/boundary layer interaction study at the ompression corner of the cylinder-flare modules.The fabrication process of the pneumatic tubes was modified to improve its pressure tight capability.The parameter measurement system was proved reliable by the MF-1 flight test.The thin-skin temperature and surface pressure data of the whole trajectory were obtained, which can be used for relevant analysis and CFD verification in boundary layer transition and shock wave/boundary layer interaction study.However, we need to improve some deficiencies in the test including the significant errors in 1D heat flux identification during steep drop of the heat flux, the response delay, and accuracy in low-pressure measurement.