A Roe approximate Riemann solver-based scheme for calculating hypersonic multi-component chemically reacting flow is discussed. The governing equations are multi-component three-dimensional Euler equations. The spatial distribution is discretized using the Roe flux difference splitting scheme. The code is marched in time by the point implicit procedure, which is used to couple the chemical kinetics source term and fluid dynamics. The stiff problems of ordinary differential equations are solved by an implicit formulation over a characteristic time scale of fluid. To verify the current approach, the proposed method is used to simulate a decoupled shock-deflagration system. Three classic chemical kinetics models are discussed. Numerical results agree well with other experimental results or numerical results, which shows that in hypersonic reacting flow, the Roe scheme has high accuracy in shock wave or combustion front capturing capability and the chemical kinetics model plays a critical role in the simulation of multi-component reacting flow.