Abstract: The Information Preservation (DSMC-IP) method is improved by using Advection Upstream Splitting Method (AUSM) splitting scheme, to solve the problems that the Direct Simulation of Monte Carlo (DSMC) method is effected by a large statistical dissipation, and that he traditional IP method cannot simulate the strong shock wave accurately. The fluxes of correlation terms in governing equations are reconstructed by local Mach numbers as the standard, so that the calculation is more accurate in accordance with the flow characteristics on both sides of the shock wave, thus forming a new DSMC-IP method with high statistical accuracy and hypersonic flow simulation ability. This method is utilized to simulate supersonic flow around the cylinder and hypersonic flow around the nozzle with divergent angle, the results of the AUSM splitting DSMC-IP method is basically consistent with the results of DSMC method, however the former has lower statistical scatter, and the flow characteristics are clearer. The surface characteristic coefficients differences between the results and the experiment or reference values are less than 5.5%. It is proved that the AUSM splitting DSMC-IP method is accurate and effective in the hypersonic flow simulation.