在低马赫数飞行条件下，斜爆轰发动机面临起爆与气流压损之间的矛盾。较小楔面角度难以实现稳定起爆，而较大楔面角度则会导致较大的气流压损。为平衡这一矛盾，引入能量沉积点火技术，探究单次点火对斜爆轰波的起爆与稳定燃烧的影响。考虑了壁面黏性效应，并通过基元反应模型求解非定常Navier-Stokes方程进行数值模拟。研究表明，单次点火能够有效诱导爆轰波的起爆，并在特定条件下维持自持燃烧。数值模拟不同点火源高度下斜爆轰波的演化过程，发现点火位置过高时，火焰面与前导激波无法有效耦合，导致起爆失败。进一步通过对比无黏流与黏性流的结果发现，强横波与边界层相互作用形成的回流区，是单次点火下斜爆轰波成功起爆并驻定的核心物理机制。

Under low Mach number flight conditions， oblique detonation engines face the inherent contradiction between reliable initiation and flow pressure loss. Smaller wedge angles prove insufficient to achieve stable detonation initiation， while larger wedge angles induce excessive total pressure dissipation. To address this trade-off， this study introduces energy deposition ignition technology to investigate how single-pulse ignition affects oblique detonation wave initiation and combustion stabilization. Incorporating wall viscous effects， numerical simulations are conducted through detailed chemical reaction modeling and unsteady Navier-Stokes equations resolution. The results demonstrate that single-pulse ignition effectively induces detonation wave initiation and maintains self-sustained combustion under specific conditions. Evolution analysis of oblique detonation waves under varying ignition source heights reveals that excessively elevated ignition positions prevent effective coupling between flame fronts and leading shock waves， resulting in initiation failure. Comparative analysis between inviscid and viscous flows unveils the underlying stabilization mechanism： the interaction between the strong transverse waves triggered by single-pulse ignition and the boundary layer induces a stable recirculation zone， which serves as the core physical mechanism for achieving detonation re-initiation and long-term stabilization.