Abstract: The organization of detonation using hydrocarbon fuel imposes stricter requirements on the initiation condition compared to hydrogen fuel. To ensure complete heat release within a combustion chamber of limited size, a well-designed combustion chamber is essential. To address the demand for rapid energy release from hydrocarbon fuels in hypersonic vehicle engines, This study proposes a detonation initiation scheme based on a V-shape induced surface. This approach employs a careful design of the induced surface to utilize shock wave interactions and shock wave combinations, compressing the incoming fuel and facilitating successful initiation and heat release within the combustion chamber. Numerical simulations demonstrate that, while neither the wedge surface nor the passivated wedge surface can achieve detonation, the V-shape inducted surface effectively initiates detonation and completes fuel combustion in the limited space. The main wave system in the flow field exhibits an inverted V-shaped structure, with detonation occurring near the symmetry plane of the combustion chamber. As the wave system propagates toward the sidewalls, the combustion mode transitions to a shock-induced combustion. The wave intensity is stronger in the symmetry plane and weaker near the sidewalls, which helps mitigate the risk of instability caused by shock-boundary layer interactions. Moreover, by adjusting the radius ratio of the V-shape leading edge, the interaction mode of the wave system within the leading-edge region can be modified, enabling control of the flow characteristics of the entire flow field.