Abstract: In order to study the drag characteristics, oscillation angle, and the non uniform suspension line load distribution of disk gap band (DGB) parachute under supersonic condition,the wind tunnel test of the DGB parachute drag characteristics is carried out in the FD 12 wind tunnel, and the load of suspension lines is measured by the flexible sensors. The experimental results show that under the condition of the Mach number increasing from Ma 1.50 to  Ma 2.50, the drag coefficient of the DGB parachute increases first and then decreases, and reaches the maximum of 0.60 at Ma 1.75, while the maximum oscillation angle decreases first and then increases, and the oscillation angle reaches the minimum value of  7.4° at Ma 2.00. The installation of the sensor has little effect on the wind tunnel test results of the parachute. Through the calibration and error analysis of the flexible sensor, the load data of the suspension lines is obtained, and the conclusions reflect that the ratio of load on different parachute suspension lines can reach 1.98. The total parachute load obtained from the sensor data is matched with the measurement data of the wind tunnel balance well, which further verifies the correctness of the flexible sensor results.

Key words: DGB parachute, Supersonic, Wind tunnel test, Flexible sensor, Drag coefficient