<p>Hypervelocity projectiles consist of various components, including the projectile body and the sabot. After the projectile exits the muzzle, the sabot separates from the projectile body, resulting in complex aerodynamic interactions between the sabot and the projectile body. The present study focuses on a hypervelocity projectile with a two-segment sabot at Mach 7.2, employing an unstructured overset grid method based on polyhedral grids. By coupling and solving unsteady Navier-Stokes equations and six-degree-of-freedom equations, numerical simulations are performed to examine the unsteady flow field during sabot separation. The research evaluates the influence of initial disturbances, including pitch, roll, and yaw angular velocities, on the flow characteristics. The findings reveal that an initial pitch angular velocity disturbance (IDIPAV) of 30&#xa0;rad/s accelerates the separation of the upper sabot segment while decelerating the lower segment, resulting in a final pitch angle difference of 4.32 Deg. Conversely, initial disturbances of the same magnitude in roll and yaw angular velocities exhibit minimal effects on the separation. Further investigation on IDIPAV indicates that an increase in its amplitude to 90&#xa0;rad/s results in a pitch angle difference of 13.51 Deg between the sabot segments, an expansion in the fluctuation range of the lift coefficient of the projectile body, and a failure of both drag and lift coefficients to revert to the reference baseline within 1 ms. These results provide valuable insights into the significance of various initial disturbances, particularly those exerting the most pronounced effects on sabot separation.</p>