The high dynamic nonlinearity of the working process of the supersonic deceleration parachute brings great uncertainty to the modeling of the parachute, which affects the attitude stability analysis results of the parachute cabin combination. The influence of the front cabin on the aerodynamic force and moment coefficient of the parachute under supersonic inflow is simulated and analyzed in the paper, then the aerodynamic parameters of the single parachute based on CFD and wind tunnel test are modified. With the modified rear parachute force model as the input, the six degrees of freedom model of the front cabin under the action of deceleration parachute force is established. Based on the stability requirement of the attitude control of the front cabin, the damping control measures based on the Mach number and angular velocity threshold pneumatic roll channel are proposed. The experimental verification shows that the expected stable control of the attitude angular velocity of the forward cabin's roll channel is achieved in the initial stage of the supersonic deceleration section. At the same time, it also has a good suppression effect on the attitude angular velocity of the forward cabin's pitch and yaw channels.