Abstract: In order to obtain the parachute axial force, normal force and pitching moment coefficients for the dynamic simulation of a Mars probe parachute-payload system, the technical research on variable angle of attack test has been carried out in the high speed wind tunnel, a variable angle of attack test device has been developed, the axial force, normal force and pitching moment coefficients of the Mars exploration parachute model with Mach numbers from 0.4 to 0.8 at angles of attack from 0° to 25° are obtained by the variable angle of attack tests in the high speed wind tunnel, the influence of the support interference and wind tunnel wall interference on the test data is corrected. The test results show that the axial force coefficient of the Mars probe parachute model does not change much with the angle of attack; the normal force coefficient of the conventional fabric permeability parachute model increases with the increase of the angle of attack, the normal force coefficient of the lower fabric permeability parachute model decreases with the increase of the angle of attack at small angle of attack at Mach numbers of 0.4 and 0.6; the conventional fabric permeability parachute model is statically stable in the Mach number range from 0.4 to 0.8, the static stability of the conventional fabric permeability parachute model is greater than that of the lower fabric permeability parachute model, the lower fabric permeability parachute model is statically unstable at the angle of attack of zero and has a nonzero statically stable trim angle of attack at Mach numbers of 0.4 and 0.6.

Key words: Parachute, High speed wind tunnel, Force measurement, Variable angle of attack, Mars exploration